This document discusses CFD analysis of solid fuel scramjet combustors. It begins with an introduction to scramjet engines and reasons for investigating solid fuels. It then reviews previous research on solid fuel scramjet combustor tests and numerical simulations. The computational domain and geometry of the scramjet combustor being modeled is described. Different classifications of solid propellant combustion models are discussed. Finally, the numerical method used in the CFD analysis with the FLUENT software is outlined. The analysis examines non-reacting and reacting flow fields in the combustor with a Mach 2 inlet flow and regression of the solid fuel boundary.
Conceptual Design and Structural Analysis of Solid Rocket Motor Casingijceronline
This paper is concern with theoretical design of the 100 kg solid rocket motor with predefined values of the burning rate is 100 mm/ sec, specific impulse is 240 sec and chamber pressure is 1000 psi. confined with selection of the material and basic concept of the rocket motor and its aspect during static test. Rocket motor is a highly complex aerospace component that consists of a metal casting, ablative liner and propellant grain. Also to determine the design pressure and burst pressure of a solid rocket motor casing .Preliminary design provided key propulsion outputs that would later be refined and assessed in the final design.
A group of aerospace engineering students at Cal Poly Pomona designed and built the university's first hybrid rocket. The rocket was designed to reach an altitude of 10,000 feet and have a maximum drift of 2,500 feet. After several failed launch attempts, the rocket finally launched but did not achieve its full altitude due to wind conditions. It is estimated the rocket reached between 2,500-3,000 feet before crashing due to parachute failure. The project provided valuable experience for the students in designing, building, and launching a large-scale rocket.
This document summarizes a study on using computational fluid dynamics (CFD) to simulate flow in reaction turbines. The study used CFD to model flow in an axial flow turbine and a mixed flow turbine. Simulation results for efficiency and discharge at varying operating conditions were found to compare well with experimental data. CFD allows detailed analysis of flow patterns and performance under off-design conditions in a more cost-effective manner than physical testing. The study analyzed pressure and velocity distributions within the turbines and how they vary with operating parameters like guide vane opening and rotational speed.
Wind resources vary significantly in strength from one location to another over a wide geographical region. The major turbine manufacturers offer a family/series of wind tur- bines to suit the market needs of different wind regimes. The current state of the art in wind farm design however does not provide quantitative guidelines regarding what turbine feature combinations are suitable for different wind regimes, when turbines are operating as a group in an optimized layout. This paper provides a unique exploration of the best tradeoffs between the cost and the capacity factor of wind farms (of specified nameplate capacity), provided by the currently available turbines for different wind classes. To this end, the best performing turbines for different wind resource strengths are identified by minimizing the cost of energy through wind farm layout optimization. Exploration of the “cost - capacity factor” tradeoffs are then performed for the wind resource strengths cor- responding to the wind classes defined in the 7-class system. The best tradeoff turbines are determined by searching for the non-dominated set of turbines out of the pool of best performing turbines of different rated powers. The medium priced turbines are observed to provide the most attractive tradeoffs − 15% more capacity factor than the cheapest tradeoff turbines and only 5% less capacity factor than the most expensive tradeoff turbines. It was found that although the “cost - capacity factor” tradeoff curve expectedly shifted towards higher capacity factors with increasing wind class, the trend of the tradeoff curve remained practically similar. Further analysis showed that the “rated power - rotor diameter” com- bination and the “rotor diameter/hub height” ratios are very important considerations in the current selection and further evolution of turbine designs. We found that larger rotor diameters are not preferred for mid-range turbines with rated powers between 1.5 - 2.5 MW, and “rotor diameter/hub height” ratios greater than 1.1 are not preferred by any of the wind classes.
Pulse Detonation Engine - A Next Gen PropulsionIJMER
The document discusses pulse detonation engines (PDEs) as a potential next generation propulsion system. PDEs use detonation combustion rather than deflagration, providing higher efficiency. They have no moving parts and simplicity. PDEs are well-suited for hypersonic and space applications due to their compact size and high performance. Hybrid PDE designs that combine with turbofans promise higher efficiency commercial air travel. Pulse detonation rocket engines could also power rockets with lower fuel needs than conventional engines. Further development is needed to address challenges from detonation shocks and controls.
This document summarizes the design of a 10 kN liquid rocket engine called Balerion that uses additive manufacturing. It was designed by students at USC to power a reusable rocket called WIRES #13 being developed in Japan. The engine uses LOX and kerosene propellants with Inconel 718 for its materials. Computational models were developed to analyze the regenerative cooling and film cooling capabilities. Additive manufacturing benefits and challenges are discussed. Testing will be conducted to validate the engine performance.
Design and Additive Manufacturing Considerations for Liquid Rocket Engine Dev...Nihar Patel
This document discusses the design and additive manufacturing considerations for developing a liquid rocket engine using 3D printing. It covers how initial engine design was constrained by the 3D printing process and requirements. Unexpected challenges during manufacturing required developing custom tools to machine parts and allow testing. The student team was ultimately able to complete a hot-fire testing campaign for their bi-propellant, 3D printed rocket engine.
Comparison of Two Dispersion Models_A Bulk Petroleum Storage Terminal Case St...BREEZE Software
"This study presents a comparison of the pollutant concentration predictions from the
AERMOD and ISC air dispersion models in the context of
fugitive storage tank emissions at a bulk petroleum storage terminal."
Conceptual Design and Structural Analysis of Solid Rocket Motor Casingijceronline
This paper is concern with theoretical design of the 100 kg solid rocket motor with predefined values of the burning rate is 100 mm/ sec, specific impulse is 240 sec and chamber pressure is 1000 psi. confined with selection of the material and basic concept of the rocket motor and its aspect during static test. Rocket motor is a highly complex aerospace component that consists of a metal casting, ablative liner and propellant grain. Also to determine the design pressure and burst pressure of a solid rocket motor casing .Preliminary design provided key propulsion outputs that would later be refined and assessed in the final design.
A group of aerospace engineering students at Cal Poly Pomona designed and built the university's first hybrid rocket. The rocket was designed to reach an altitude of 10,000 feet and have a maximum drift of 2,500 feet. After several failed launch attempts, the rocket finally launched but did not achieve its full altitude due to wind conditions. It is estimated the rocket reached between 2,500-3,000 feet before crashing due to parachute failure. The project provided valuable experience for the students in designing, building, and launching a large-scale rocket.
This document summarizes a study on using computational fluid dynamics (CFD) to simulate flow in reaction turbines. The study used CFD to model flow in an axial flow turbine and a mixed flow turbine. Simulation results for efficiency and discharge at varying operating conditions were found to compare well with experimental data. CFD allows detailed analysis of flow patterns and performance under off-design conditions in a more cost-effective manner than physical testing. The study analyzed pressure and velocity distributions within the turbines and how they vary with operating parameters like guide vane opening and rotational speed.
Wind resources vary significantly in strength from one location to another over a wide geographical region. The major turbine manufacturers offer a family/series of wind tur- bines to suit the market needs of different wind regimes. The current state of the art in wind farm design however does not provide quantitative guidelines regarding what turbine feature combinations are suitable for different wind regimes, when turbines are operating as a group in an optimized layout. This paper provides a unique exploration of the best tradeoffs between the cost and the capacity factor of wind farms (of specified nameplate capacity), provided by the currently available turbines for different wind classes. To this end, the best performing turbines for different wind resource strengths are identified by minimizing the cost of energy through wind farm layout optimization. Exploration of the “cost - capacity factor” tradeoffs are then performed for the wind resource strengths cor- responding to the wind classes defined in the 7-class system. The best tradeoff turbines are determined by searching for the non-dominated set of turbines out of the pool of best performing turbines of different rated powers. The medium priced turbines are observed to provide the most attractive tradeoffs − 15% more capacity factor than the cheapest tradeoff turbines and only 5% less capacity factor than the most expensive tradeoff turbines. It was found that although the “cost - capacity factor” tradeoff curve expectedly shifted towards higher capacity factors with increasing wind class, the trend of the tradeoff curve remained practically similar. Further analysis showed that the “rated power - rotor diameter” com- bination and the “rotor diameter/hub height” ratios are very important considerations in the current selection and further evolution of turbine designs. We found that larger rotor diameters are not preferred for mid-range turbines with rated powers between 1.5 - 2.5 MW, and “rotor diameter/hub height” ratios greater than 1.1 are not preferred by any of the wind classes.
Pulse Detonation Engine - A Next Gen PropulsionIJMER
The document discusses pulse detonation engines (PDEs) as a potential next generation propulsion system. PDEs use detonation combustion rather than deflagration, providing higher efficiency. They have no moving parts and simplicity. PDEs are well-suited for hypersonic and space applications due to their compact size and high performance. Hybrid PDE designs that combine with turbofans promise higher efficiency commercial air travel. Pulse detonation rocket engines could also power rockets with lower fuel needs than conventional engines. Further development is needed to address challenges from detonation shocks and controls.
This document summarizes the design of a 10 kN liquid rocket engine called Balerion that uses additive manufacturing. It was designed by students at USC to power a reusable rocket called WIRES #13 being developed in Japan. The engine uses LOX and kerosene propellants with Inconel 718 for its materials. Computational models were developed to analyze the regenerative cooling and film cooling capabilities. Additive manufacturing benefits and challenges are discussed. Testing will be conducted to validate the engine performance.
Design and Additive Manufacturing Considerations for Liquid Rocket Engine Dev...Nihar Patel
This document discusses the design and additive manufacturing considerations for developing a liquid rocket engine using 3D printing. It covers how initial engine design was constrained by the 3D printing process and requirements. Unexpected challenges during manufacturing required developing custom tools to machine parts and allow testing. The student team was ultimately able to complete a hot-fire testing campaign for their bi-propellant, 3D printed rocket engine.
Comparison of Two Dispersion Models_A Bulk Petroleum Storage Terminal Case St...BREEZE Software
"This study presents a comparison of the pollutant concentration predictions from the
AERMOD and ISC air dispersion models in the context of
fugitive storage tank emissions at a bulk petroleum storage terminal."
This document provides a progress briefing on research contract 07600-041 to develop cost-effective production and use of fuels and oxidizers from Mars' atmosphere. It summarizes testing of solid carbon monoxide and solid methane hybrid rocket engines, which showed promising performance. The document outlines the study approach of identifying fuel/oxidizer scenarios and missions, developing traffic models, and analyzing costs and benefits. The goal is to recommend technologies for Mars exploration and exploitation using in-situ resource utilization.
This document describes a model developed to predict the optimal reaction temperature of an industrial fluid catalytic cracking (FCC) unit riser. A pseudo-homogeneous two-dimensional model was developed using a five-lump reaction scheme. Mass transfer resistance was incorporated to improve accuracy over previous one-dimensional plug flow models. Finite difference methods were used to discretize the governing equations which were then solved using MATLAB. Simulation results identified three temperature regimes for catalyst coking. An optimum temperature range of 786K-788K and catalyst-to-oil ratio range of 4.60-4.71 were predicted to minimize coke on catalyst without reducing gasoline yield.
This document presents a thermal stresses based fragmentation model for pulverized coal particles during low temperature air plasma gasification. The model tracks temperature distributions within particles using a 1D radial approach and calculates thermal stresses to predict crack initiation and particle fragmentation. It was implemented using user-defined functions in ANSYS Fluent. Results show increased volatile release, CO production, and conversion rates when fragmentation is included. Future work will refine kinetic parameters, test different particle properties, and validate with experimental pilot plant data.
This document summarizes research presented at the 2016 ANSYS Convergence Conference. It describes simulations of two-phase evaporating reacting flows in micro-scale applications, such as fluidized beds and FCC industry processes. The research models droplet-particle collisions using a volume of fluid method to track interfaces and evaporation/reaction models. Parameters like temperature, velocity and geometry are varied. Hotter and slower collisions promote cracking reactions and gasoline production. Small droplets evaporate faster than large ones. Future work includes experiments to validate models and optimize conditions to minimize coke deposits.
This paper discusses the processes involved in the additive manufacturing of a regenerative and film-cooled liquid rocket engine with a thrust of 10 kN using Inconel 718, while detailing validation techniques. A description of the objectives and design constraints provide the context and motivations. Computational Fluid Dynamics (CFD) models were developed and provided the expected pressure and thermal regimes under regenerative and film cooling. Additionally, Finite Element (FE) models were used to predict the capabilities of the engine structure. A description of 3D printing methods highlights the benefits and limitations of the technology, specifically the influence the design of liquid rocket engines. A pintle injector is used, printed as a separate, easily removable and replaceable component. Issues related to overhangs, surface roughness, and shrinkage; aspects related to post-print processing and the need to minimize machining are discussed. Results from the CT scans of the engine and its components are presented. The paper also outlines the series of tests that will be performed on this engine to verify its performance and provide design basis for future works. This engine will be used to power the reusable flight vehicle that is under development at the Kyushu Institute of Technology in Japan. The student-led Liquid Propulsion Laboratory at the University of Southern California is responsible for the work detailed below.
This document summarizes the identification of a lower order transfer function model of an Alstom gasifier system using input-output data. The gasifier is a nonlinear, multivariable process. Prediction error algorithms were used to identify a linear MIMO transfer function model using input-output data from simulations of the gasifier at 100% load conditions. A pseudo-random binary signal was used to perturb the five inputs, and 10,000 samples of input-output data were recorded and divided into training and validation data. The identified linear MIMO transfer function model can be used for control system design and analysis of the gasifier system.
The document summarizes an experimental investigation of a vortex tube refrigeration system based on compressed air. The vortex tube produces cold and hot air streams from a single source of compressed air without moving parts or environmental impact. Key parameters that affect vortex tube operation are classified as geometrical (dimensions) or thermo-physical (pressure, gas type). An experimental setup is designed to investigate the effect of varying the diameter and length of the main tube, outlet orifice shape and diameter, and inlet pressure, gas, cold gas ratio, and moisture. Results show temperature difference increases with inlet pressure and more nozzles. Insulation also increases temperature separation.
Ijri te-03-011 performance testing of vortex tubes with variable parametersIjripublishers Ijri
Conventional refrigeration system is a type of refrigeration systems which are costly; noisy, harmful gases released from a machine based on application of this type of system and it is required more maintenance. So, we need to go for unconventional refrigeration systems like vortex tube refrigeration system, which produce less vibrations and which require less maintenance and which are noiseless. It is required for our mechanical engineers to look for enhancing the performance of such vortex tubes. So as a part of my project work, I have chosen various sizes of vortex tubes and test their performances for finding out optimum performance. We will be testing the performance of vortex tubes with different ‘l/d’ ratios and different cold fractions, with different pressures and different nozzle sizes.
The vortex tube is a device that separates a gas flow into hot and cold exits without moving parts. High pressure gas enters tangentially through nozzles, creating a swirling vortex. There are two types - uniform and counter flow - which differ in exit placement. In operation, the gas separates into inner and outer layers with different temperatures due to centrifugal forces. The inner layer exits cold and the outer layer exits hot. Vortex tubes provide simple cooling with no refrigerants but have low efficiency. Potential applications include industries needing simultaneous hot and cold air.
This document is a project synopsis for designing and fabricating a vortex tube to cool a high-speed motorized spindle. It was created by four project associates and is under the guidance of Dr. K C Devendrappa. The synopsis includes sections on literature survey, objectives, methodology, advantages and disadvantages, and applications. It discusses using a vortex tube, which has no moving parts, to separate compressed air into hot and cold streams in order to cool a motorized spindle shaft.
This document presents the design and analysis of a scramjet engine. The author uses quasi-one-dimensional equations to model the compressible flow and combustion within the engine. Performance is estimated using computational modeling of the inlet, combustor, and nozzle. Initial results show a thrust of nearly 405 kN and specific impulse of 174 seconds. Further analysis of the combustion chamber and boundary layers is recommended.
This document summarizes the design of a scramjet engine for Mach 5 flight. It outlines the benefits and challenges of scramjet technology, including that it is air-breathing and has no moving parts but requires special heat-resistant materials. The document then details the design process, which used a quasi-1D flow analysis method to model the inlet, combustor, and nozzle for Mach 5 flight at 15 km altitude. The results showed thrust of 405 kN, specific impulse of 174 seconds, and efficiencies around 0.8-0.9. However, the engine would only be viable installed on a large vehicle and requires improved combustion modeling for higher supersonic speeds.
about scramjets, its components, function, its advantages and advantages, its applications with many references by reshmi.r , dinesh kumar and sandeep.
The document presents information about scramjet engines. It discusses the history of scramjet development from World War II to recent test flights reaching Mach 10 speeds. The key components of a scramjet engine are described as a converging inlet to compress incoming air, a combustor where fuel is burned, and a diverging nozzle to accelerate the heated air and produce thrust. Scramjets differ from other jet engines by not using rotating components for compression and relying on high flight speeds to compress air before combustion. Potential applications include hypersonic aircraft that could reduce intercontinental flight times to under 90 minutes.
1) The document discusses scramjet engines, which use supersonic combustion of fuel and air to produce thrust without needing liquid oxygen tanks.
2) Scramjets have components like converging inlets, combustors, and diverging nozzles. They work by compressing incoming supersonic air and injecting fuel for combustion.
3) Potential applications include hypersonic passenger planes traveling at 15 times the speed of sound and scramjet-powered missiles. Recent programs demonstrate scramjet flights up to Mach 9.6. Scramjets could enable cheaper access to space.
This document discusses scramjet inlets, which are a critical component of scramjet engines suitable for sustained hypersonic flight. Scramjet inlets must compress supersonic incoming air for combustion while minimizing losses. Different inlet designs achieve varying levels of compression efficiency. The document examines inlet types, desired compression levels, and presents a design example of a 3D scramjet inlet intended to operate between Mach 6-12 for access to space. Key challenges for scramjet inlets include achieving sufficient compression while minimizing shock losses and heating at high flight speeds.
IJERA (International journal of Engineering Research and Applications) is International online, ... peer reviewed journal. For more detail or submit your article, please visit www.ijera.com
Combustion and Mixing Analysis of a Scramjet Combustor Using CFDijsrd.com
This document summarizes a computational fluid dynamics (CFD) study of combustion and mixing in a scramjet combustor. The study uses ANSYS Fluent software to model flow inside a scramjet combustor geometry for hydrogen, diesel, and methane fuels. The objectives are to determine the flow field and maximize thrust at a Mach number of 2. Key findings include that combustion increases recirculation behind the flameholder strut compared to mixing alone, and shockwaves from the strut facilitate combustion ignition in regions with fuel-air mixing. Meshing of the combustor geometry and strut are discussed.
COMPUTATIONAL ANALYSIS OF FLAME STABILIZATION IN RAMJET ENGINE COMBUSTION CHA...IRJET Journal
This document discusses a computational analysis of flame stabilization in a ramjet engine combustion chamber. It summarizes a study that uses computational fluid dynamics (CFD) to quantitatively predict the combustion characteristics of a ramjet engine. The study analyzes cold flow and heat addition in the combustion chamber and nozzle. It examines two examples of combustor layouts for a 15:1 air-fuel ratio with kerosene fuel. While combustion efficiency and performance remain the same, the first case with a lower blockage ratio results in about a 2% pressure loss. The second case with a lower blockage ratio and 80% combustion efficiency is recommended for ramjet combustor design.
This document describes the design and testing of a hybrid rocket motor. It discusses the background of hybrid motors, including their advantages over solid and liquid motors. The document then outlines the objectives, constraints, and selection of the HTPB/aluminum fuel for the project. Thermodynamic calculations were performed to analyze the fuel combination and determine combustion properties. A one-dimensional model was developed using regression rate correlations from literature to predict and optimize the motor's performance over time. The model will be used to design the fuel grain and nozzle geometry before manufacturing and testing the motor.
This document provides a progress briefing on research contract 07600-041 to develop cost-effective production and use of fuels and oxidizers from Mars' atmosphere. It summarizes testing of solid carbon monoxide and solid methane hybrid rocket engines, which showed promising performance. The document outlines the study approach of identifying fuel/oxidizer scenarios and missions, developing traffic models, and analyzing costs and benefits. The goal is to recommend technologies for Mars exploration and exploitation using in-situ resource utilization.
This document describes a model developed to predict the optimal reaction temperature of an industrial fluid catalytic cracking (FCC) unit riser. A pseudo-homogeneous two-dimensional model was developed using a five-lump reaction scheme. Mass transfer resistance was incorporated to improve accuracy over previous one-dimensional plug flow models. Finite difference methods were used to discretize the governing equations which were then solved using MATLAB. Simulation results identified three temperature regimes for catalyst coking. An optimum temperature range of 786K-788K and catalyst-to-oil ratio range of 4.60-4.71 were predicted to minimize coke on catalyst without reducing gasoline yield.
This document presents a thermal stresses based fragmentation model for pulverized coal particles during low temperature air plasma gasification. The model tracks temperature distributions within particles using a 1D radial approach and calculates thermal stresses to predict crack initiation and particle fragmentation. It was implemented using user-defined functions in ANSYS Fluent. Results show increased volatile release, CO production, and conversion rates when fragmentation is included. Future work will refine kinetic parameters, test different particle properties, and validate with experimental pilot plant data.
This document summarizes research presented at the 2016 ANSYS Convergence Conference. It describes simulations of two-phase evaporating reacting flows in micro-scale applications, such as fluidized beds and FCC industry processes. The research models droplet-particle collisions using a volume of fluid method to track interfaces and evaporation/reaction models. Parameters like temperature, velocity and geometry are varied. Hotter and slower collisions promote cracking reactions and gasoline production. Small droplets evaporate faster than large ones. Future work includes experiments to validate models and optimize conditions to minimize coke deposits.
This paper discusses the processes involved in the additive manufacturing of a regenerative and film-cooled liquid rocket engine with a thrust of 10 kN using Inconel 718, while detailing validation techniques. A description of the objectives and design constraints provide the context and motivations. Computational Fluid Dynamics (CFD) models were developed and provided the expected pressure and thermal regimes under regenerative and film cooling. Additionally, Finite Element (FE) models were used to predict the capabilities of the engine structure. A description of 3D printing methods highlights the benefits and limitations of the technology, specifically the influence the design of liquid rocket engines. A pintle injector is used, printed as a separate, easily removable and replaceable component. Issues related to overhangs, surface roughness, and shrinkage; aspects related to post-print processing and the need to minimize machining are discussed. Results from the CT scans of the engine and its components are presented. The paper also outlines the series of tests that will be performed on this engine to verify its performance and provide design basis for future works. This engine will be used to power the reusable flight vehicle that is under development at the Kyushu Institute of Technology in Japan. The student-led Liquid Propulsion Laboratory at the University of Southern California is responsible for the work detailed below.
This document summarizes the identification of a lower order transfer function model of an Alstom gasifier system using input-output data. The gasifier is a nonlinear, multivariable process. Prediction error algorithms were used to identify a linear MIMO transfer function model using input-output data from simulations of the gasifier at 100% load conditions. A pseudo-random binary signal was used to perturb the five inputs, and 10,000 samples of input-output data were recorded and divided into training and validation data. The identified linear MIMO transfer function model can be used for control system design and analysis of the gasifier system.
The document summarizes an experimental investigation of a vortex tube refrigeration system based on compressed air. The vortex tube produces cold and hot air streams from a single source of compressed air without moving parts or environmental impact. Key parameters that affect vortex tube operation are classified as geometrical (dimensions) or thermo-physical (pressure, gas type). An experimental setup is designed to investigate the effect of varying the diameter and length of the main tube, outlet orifice shape and diameter, and inlet pressure, gas, cold gas ratio, and moisture. Results show temperature difference increases with inlet pressure and more nozzles. Insulation also increases temperature separation.
Ijri te-03-011 performance testing of vortex tubes with variable parametersIjripublishers Ijri
Conventional refrigeration system is a type of refrigeration systems which are costly; noisy, harmful gases released from a machine based on application of this type of system and it is required more maintenance. So, we need to go for unconventional refrigeration systems like vortex tube refrigeration system, which produce less vibrations and which require less maintenance and which are noiseless. It is required for our mechanical engineers to look for enhancing the performance of such vortex tubes. So as a part of my project work, I have chosen various sizes of vortex tubes and test their performances for finding out optimum performance. We will be testing the performance of vortex tubes with different ‘l/d’ ratios and different cold fractions, with different pressures and different nozzle sizes.
The vortex tube is a device that separates a gas flow into hot and cold exits without moving parts. High pressure gas enters tangentially through nozzles, creating a swirling vortex. There are two types - uniform and counter flow - which differ in exit placement. In operation, the gas separates into inner and outer layers with different temperatures due to centrifugal forces. The inner layer exits cold and the outer layer exits hot. Vortex tubes provide simple cooling with no refrigerants but have low efficiency. Potential applications include industries needing simultaneous hot and cold air.
This document is a project synopsis for designing and fabricating a vortex tube to cool a high-speed motorized spindle. It was created by four project associates and is under the guidance of Dr. K C Devendrappa. The synopsis includes sections on literature survey, objectives, methodology, advantages and disadvantages, and applications. It discusses using a vortex tube, which has no moving parts, to separate compressed air into hot and cold streams in order to cool a motorized spindle shaft.
This document presents the design and analysis of a scramjet engine. The author uses quasi-one-dimensional equations to model the compressible flow and combustion within the engine. Performance is estimated using computational modeling of the inlet, combustor, and nozzle. Initial results show a thrust of nearly 405 kN and specific impulse of 174 seconds. Further analysis of the combustion chamber and boundary layers is recommended.
This document summarizes the design of a scramjet engine for Mach 5 flight. It outlines the benefits and challenges of scramjet technology, including that it is air-breathing and has no moving parts but requires special heat-resistant materials. The document then details the design process, which used a quasi-1D flow analysis method to model the inlet, combustor, and nozzle for Mach 5 flight at 15 km altitude. The results showed thrust of 405 kN, specific impulse of 174 seconds, and efficiencies around 0.8-0.9. However, the engine would only be viable installed on a large vehicle and requires improved combustion modeling for higher supersonic speeds.
about scramjets, its components, function, its advantages and advantages, its applications with many references by reshmi.r , dinesh kumar and sandeep.
The document presents information about scramjet engines. It discusses the history of scramjet development from World War II to recent test flights reaching Mach 10 speeds. The key components of a scramjet engine are described as a converging inlet to compress incoming air, a combustor where fuel is burned, and a diverging nozzle to accelerate the heated air and produce thrust. Scramjets differ from other jet engines by not using rotating components for compression and relying on high flight speeds to compress air before combustion. Potential applications include hypersonic aircraft that could reduce intercontinental flight times to under 90 minutes.
1) The document discusses scramjet engines, which use supersonic combustion of fuel and air to produce thrust without needing liquid oxygen tanks.
2) Scramjets have components like converging inlets, combustors, and diverging nozzles. They work by compressing incoming supersonic air and injecting fuel for combustion.
3) Potential applications include hypersonic passenger planes traveling at 15 times the speed of sound and scramjet-powered missiles. Recent programs demonstrate scramjet flights up to Mach 9.6. Scramjets could enable cheaper access to space.
This document discusses scramjet inlets, which are a critical component of scramjet engines suitable for sustained hypersonic flight. Scramjet inlets must compress supersonic incoming air for combustion while minimizing losses. Different inlet designs achieve varying levels of compression efficiency. The document examines inlet types, desired compression levels, and presents a design example of a 3D scramjet inlet intended to operate between Mach 6-12 for access to space. Key challenges for scramjet inlets include achieving sufficient compression while minimizing shock losses and heating at high flight speeds.
IJERA (International journal of Engineering Research and Applications) is International online, ... peer reviewed journal. For more detail or submit your article, please visit www.ijera.com
Combustion and Mixing Analysis of a Scramjet Combustor Using CFDijsrd.com
This document summarizes a computational fluid dynamics (CFD) study of combustion and mixing in a scramjet combustor. The study uses ANSYS Fluent software to model flow inside a scramjet combustor geometry for hydrogen, diesel, and methane fuels. The objectives are to determine the flow field and maximize thrust at a Mach number of 2. Key findings include that combustion increases recirculation behind the flameholder strut compared to mixing alone, and shockwaves from the strut facilitate combustion ignition in regions with fuel-air mixing. Meshing of the combustor geometry and strut are discussed.
COMPUTATIONAL ANALYSIS OF FLAME STABILIZATION IN RAMJET ENGINE COMBUSTION CHA...IRJET Journal
This document discusses a computational analysis of flame stabilization in a ramjet engine combustion chamber. It summarizes a study that uses computational fluid dynamics (CFD) to quantitatively predict the combustion characteristics of a ramjet engine. The study analyzes cold flow and heat addition in the combustion chamber and nozzle. It examines two examples of combustor layouts for a 15:1 air-fuel ratio with kerosene fuel. While combustion efficiency and performance remain the same, the first case with a lower blockage ratio results in about a 2% pressure loss. The second case with a lower blockage ratio and 80% combustion efficiency is recommended for ramjet combustor design.
This document describes the design and testing of a hybrid rocket motor. It discusses the background of hybrid motors, including their advantages over solid and liquid motors. The document then outlines the objectives, constraints, and selection of the HTPB/aluminum fuel for the project. Thermodynamic calculations were performed to analyze the fuel combination and determine combustion properties. A one-dimensional model was developed using regression rate correlations from literature to predict and optimize the motor's performance over time. The model will be used to design the fuel grain and nozzle geometry before manufacturing and testing the motor.
Cfd Studies of Two Stroke Petrol Engine ScavengingIJERA Editor
This project deals with the numerical analysis of 2 stroke engine scavenging in two cases. One with an existing condition (Flat headed pistons) and another with a new design (Dome headed piston) .The numerical analysis is done with help of CFD software ANSYS FLUENT 14.5. Here, the modeling of engine piston with flat headed type and with dome headed types was done in workbench. In ANSYS FLUENT after the geometrical design, for the dynamic motion meshing is used and set up species transport model also. At first the scavenging effect of flat headed piston is analyzed. Later the simulation of piston with dome headed type was also checked. Analyzing the variations from each and selected the best method for scavenging. Finally the scavenging efficiency is calculated for both type arrangements.
1) This study characterized the aerodynamic and structural performance of a micro scale axial turbine for use in a solar powered Brayton cycle.
2) Computational fluid dynamics and finite element analysis were used to examine the turbine's performance under various conditions and loading.
3) The results showed that rotor geometry and operating parameters significantly affected stresses and fatigue life, opening doors for further research to make this system applicable on the ground.
A general interest to reduce fossil fuel consumption and to limit combustion
emissions, increase the efficiency of combustion chambers. One of the most important
processes in a gas turbine combustor, influencing to a large extent the efficiency of the
entire combustion process is the mixing between a swirling annular jet (primary air) and
the non-swirling inner jet (fuel).In normal swirling combustor, primary swirling air is
only supplied to the chamber and is mixed with the fuel but we here introduce a small
duct in the chamber containing a small amount of air without swirl and make it to mix
with the fuel and the primary swirling air. We have modified the design of the swirl
combustor by introducing a bluff body over the flow of the turbulent jet through which the
turbulent air will pass causing the axial velocity. For the purpose of simulation of the
required model of swirl combustor we are using the recent tools like ANSYS, ICEM, CFD
and FLUENT software’s. Using these tools the numerical investigation has been done.
The various values that are obtained are compared with the previous results of the swirl
combustor and the increase in the efficiency of the combustion has been noted
This document provides a literature review of hybrid rocket propulsion. It begins with definitions of key terms related to hybrid rockets. The main advantages of hybrid rockets over solid and liquid rockets are safety during handling and storage, reliability due to fewer complex components, and flexibility for throttling and restarting. Challenges include understanding the complex chemical combustion processes. Overall, the document examines the potential for hybrid rockets as a safer and lower-cost alternative to traditional rocket designs.
IRJET- Review on Methodology of Furnace Burner Design for Thermal Power Plant...IRJET Journal
This document discusses the design optimization of furnace burners in thermal power plants using computational fluid dynamics (CFD). It begins by introducing thermal power plants and the importance of designing efficient, clean and economical combustion systems. It then discusses using CFD to analyze key burner parameters like velocity, angle, size and configuration to maximize mixing efficiency and combustion. The goal is to determine the most cost-effective combination of parameters. CFD analysis can provide insights to improve flame stability and reduce emissions and losses compared to experimental testing alone.
The CFD Analysis of Turbulence Characteristics in Combustion Chamber with Non...IOSR Journals
Abstract : Co-Axial jets have applications in areas where the mixing of two fluid jets are necessary, the two
fluid jets can be effectively mixed by producing the turbulence flow. Turbulence is a chaotic behavior of the fluid
particles that comes in to picture when the inertia force of the flow dominates the viscous force and it is
characterized by the Reynolds Number. Co-axial jets are effective in producing the turbulence. In the present
study the free compressible turbulent coaxial jet problem will be computed using CFD, and compare with
different non circular coaxial jets based on constant hydraulic diameter and mass flow rate. Turbulence
characteristics of combustion chamber with circular coaxial and non circular coaxial jets are determined and
compared.
Keywords: Coaxial Jet, Turbulence Modeling, Fuel injector, Combustion chamber.
Cooling of a truck cabin by vapour absorption refrigeration system using engi...eSAT Publishing House
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology
This document reviews hydrogen and hydrocarbon fuels for hypersonic engine applications. Hydrogen fuels are generally used for high-speed space entry due to their high specific impulse, allowing flight up to Mach 15. However, hydrogen has low density, requiring larger fuel tanks. Hydrocarbon fuels have lower performance but higher density, making them suitable for hypersonic missiles up to Mach 10. Future research may blur the lines, with active cooling extending hydrocarbon engine operation and supplementing hydrogen fuels to increase thrust.
Iaetsd computer simulation of compression ignition engine through matlabIaetsd Iaetsd
This document discusses a computer simulation of a compression ignition engine using MATLAB. The simulation models the engine cycle in two zones - a burned zone and unburned zone. It uses a Wiebe function to determine the mass fraction burned and calculates parameters like pressure, temperature, heat release and emissions over the engine cycle. The simulation is first validated against experimental engine test data. Sensitivity studies are then conducted by varying combustion model constants to better understand their impact on predictions and combustion mechanisms. The simulation calculates performance parameters like brake power, fuel consumption and efficiencies over the engine's operating range. It aims to provide insights into combustion and pollutant formation at different loads and injection timings.
Analysis of turbocharger performance for jet assisted vertical takeoff and la...Ijrdt Journal
This paper gives a brief analysis on the performance parameters of a Turbocharger, by fabricating a separate combustion chamber and mocking the working of a jet engine. Parameters such as variation of specific heat, dimensionless flow parameters, variation of turbulence, conductivity, thrust developed etc are studied using simulation of the model, and compared with the actual working of the prototype. It can be conveniently proposed from the experiment that turbocharger can be used effectively for developing vertical take-off assist.
This document summarizes an experimental investigation into the regression rate behavior of hydroxyl-terminated polybutadiene (HTPB) solid fuel burning with oxygen in a hybrid rocket motor. Key findings include:
1) Real-time x-ray radiography was used to obtain instantaneous solid fuel regression rate data at many axial locations in the motor. Regression rates had a strong dependence on axial location near the head-end of the motor.
2) Thermocouple measurements indicated fuel surface temperatures between 930 and 1190 K. The estimated activation energy of 11.5 kcal/mole suggests the overall regression process is governed by physical desorption of high-molecular weight fragments from the fuel surface.
Comparative Assessment of Two Thermodynamic Cycles of an aero-derivative Mari...IOSR Journals
Abstract: This paper explores the gas turbine potentials that are fully enhanced by the use of intercooling and
thermal recuperation as an engineering option available in the design of gas turbines and offered for marine
applications. It examines the off-design performance of two different cycle designs of a 25MW aero-derivative
engine by modelling and simulating each of them to operate under conditions other than those of their design
point. The simple cycle model consists of a single-spool dual shaft layout while the advanced model is
represented by an intercooled-recuperated cycle that runs on a dual-spool and is driven through a three shaft
configuration. In each case, the output shaft is coupled to a power turbine through which the propulsion power
may be transmitted to the propeller of the vessel to operate in a virtual marine environment. An off-design
performance simulation of both engines has been conducted in order to investigate and compare the effect of
ambient temperature variation during their part-load operation and particularly when subjected to a variety of
marine operating conditions. The study assesses the techno-economic impact of the complex design of the
advanced cycle over its simple cycle counterpart and demonstrates its potential for improved operating cost
through reduced fuel consumption as a significant step in the current drive for establishing the marine gas
turbine engine as a viable alternative to traditional prime movers in the ship propulsion industry.
The document discusses research on developing a high-efficiency electrical generator using an internal combustion engine that can operate on hydrogen and hydrogen-containing fuels. The objective is to provide renewable energy utilization with high efficiency and low emissions. A full-scale prototype generator is being developed in collaboration with industrial partners. It will use a free piston linear alternator design capable of high compression ratios and fast, constant volume combustion for improved efficiency compared to traditional engines.
1. The document discusses research on developing a high-efficiency, low-emissions electrical generator that can operate on hydrogen fuels using internal combustion engine technology.
2. Experimental results showed that hydrogen combustion in a rapid compression machine approached constant volume combustion, indicating high efficiency. Combustion occurred very rapidly.
3. The generator design uses a free piston linear alternator configuration to enable high compression ratios and rapid combustion through homogeneous charge compression ignition combustion of hydrogen, with the goal of approaching ideal Otto cycle performance and efficiency.
Aero-acoustic investigation over a 3-dimensional open sunroof using CFDIRJET Journal
This document describes a computational fluid dynamics (CFD) study of buffeting noise from an open sunroof on a simplified 3D car model. The researchers will use the detached eddy simulation (DES) method in ANSYS Fluent to analyze pressure characteristics at different vehicle speeds. They will create a 3D virtual wind tunnel domain around the car model and assign appropriate boundary conditions. Pressure distributions obtained from simulations of closed and open sunroof cases will help establish an efficient design for a sunroof deflector to reduce buffeting noise.
Cfd analysis of lean premixed prevapourised combustion chamberIAEME Publication
This document summarizes a computational fluid dynamics (CFD) analysis of a lean premixed prevaporized combustion chamber. It begins with an introduction to the combustion chamber design and an overview of the CFD methodology. It then provides details on the specific CFD model geometry, mesh, boundary conditions, and results. The key findings from the CFD analysis show a strong swirling flow inside the combustion liner and a hotter temperature distribution near the liner walls that is slightly cooler at the centerline.
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Batteries -Introduction – Types of Batteries – discharging and charging of battery - characteristics of battery –battery rating- various tests on battery- – Primary battery: silver button cell- Secondary battery :Ni-Cd battery-modern battery: lithium ion battery-maintenance of batteries-choices of batteries for electric vehicle applications.
Fuel Cells: Introduction- importance and classification of fuel cells - description, principle, components, applications of fuel cells: H2-O2 fuel cell, alkaline fuel cell, molten carbonate fuel cell and direct methanol fuel cells.
Harnessing WebAssembly for Real-time Stateless Streaming PipelinesChristina Lin
Traditionally, dealing with real-time data pipelines has involved significant overhead, even for straightforward tasks like data transformation or masking. However, in this talk, we’ll venture into the dynamic realm of WebAssembly (WASM) and discover how it can revolutionize the creation of stateless streaming pipelines within a Kafka (Redpanda) broker. These pipelines are adept at managing low-latency, high-data-volume scenarios.
A SYSTEMATIC RISK ASSESSMENT APPROACH FOR SECURING THE SMART IRRIGATION SYSTEMSIJNSA Journal
The smart irrigation system represents an innovative approach to optimize water usage in agricultural and landscaping practices. The integration of cutting-edge technologies, including sensors, actuators, and data analysis, empowers this system to provide accurate monitoring and control of irrigation processes by leveraging real-time environmental conditions. The main objective of a smart irrigation system is to optimize water efficiency, minimize expenses, and foster the adoption of sustainable water management methods. This paper conducts a systematic risk assessment by exploring the key components/assets and their functionalities in the smart irrigation system. The crucial role of sensors in gathering data on soil moisture, weather patterns, and plant well-being is emphasized in this system. These sensors enable intelligent decision-making in irrigation scheduling and water distribution, leading to enhanced water efficiency and sustainable water management practices. Actuators enable automated control of irrigation devices, ensuring precise and targeted water delivery to plants. Additionally, the paper addresses the potential threat and vulnerabilities associated with smart irrigation systems. It discusses limitations of the system, such as power constraints and computational capabilities, and calculates the potential security risks. The paper suggests possible risk treatment methods for effective secure system operation. In conclusion, the paper emphasizes the significant benefits of implementing smart irrigation systems, including improved water conservation, increased crop yield, and reduced environmental impact. Additionally, based on the security analysis conducted, the paper recommends the implementation of countermeasures and security approaches to address vulnerabilities and ensure the integrity and reliability of the system. By incorporating these measures, smart irrigation technology can revolutionize water management practices in agriculture, promoting sustainability, resource efficiency, and safeguarding against potential security threats.
A review on techniques and modelling methodologies used for checking electrom...nooriasukmaningtyas
The proper function of the integrated circuit (IC) in an inhibiting electromagnetic environment has always been a serious concern throughout the decades of revolution in the world of electronics, from disjunct devices to today’s integrated circuit technology, where billions of transistors are combined on a single chip. The automotive industry and smart vehicles in particular, are confronting design issues such as being prone to electromagnetic interference (EMI). Electronic control devices calculate incorrect outputs because of EMI and sensors give misleading values which can prove fatal in case of automotives. In this paper, the authors have non exhaustively tried to review research work concerned with the investigation of EMI in ICs and prediction of this EMI using various modelling methodologies and measurement setups.
Advanced control scheme of doubly fed induction generator for wind turbine us...IJECEIAES
This paper describes a speed control device for generating electrical energy on an electricity network based on the doubly fed induction generator (DFIG) used for wind power conversion systems. At first, a double-fed induction generator model was constructed. A control law is formulated to govern the flow of energy between the stator of a DFIG and the energy network using three types of controllers: proportional integral (PI), sliding mode controller (SMC) and second order sliding mode controller (SOSMC). Their different results in terms of power reference tracking, reaction to unexpected speed fluctuations, sensitivity to perturbations, and resilience against machine parameter alterations are compared. MATLAB/Simulink was used to conduct the simulations for the preceding study. Multiple simulations have shown very satisfying results, and the investigations demonstrate the efficacy and power-enhancing capabilities of the suggested control system.
Understanding Inductive Bias in Machine LearningSUTEJAS
This presentation explores the concept of inductive bias in machine learning. It explains how algorithms come with built-in assumptions and preferences that guide the learning process. You'll learn about the different types of inductive bias and how they can impact the performance and generalizability of machine learning models.
The presentation also covers the positive and negative aspects of inductive bias, along with strategies for mitigating potential drawbacks. We'll explore examples of how bias manifests in algorithms like neural networks and decision trees.
By understanding inductive bias, you can gain valuable insights into how machine learning models work and make informed decisions when building and deploying them.
International Conference on NLP, Artificial Intelligence, Machine Learning an...gerogepatton
International Conference on NLP, Artificial Intelligence, Machine Learning and Applications (NLAIM 2024) offers a premier global platform for exchanging insights and findings in the theory, methodology, and applications of NLP, Artificial Intelligence, Machine Learning, and their applications. The conference seeks substantial contributions across all key domains of NLP, Artificial Intelligence, Machine Learning, and their practical applications, aiming to foster both theoretical advancements and real-world implementations. With a focus on facilitating collaboration between researchers and practitioners from academia and industry, the conference serves as a nexus for sharing the latest developments in the field.
Optimizing Gradle Builds - Gradle DPE Tour Berlin 2024Sinan KOZAK
Sinan from the Delivery Hero mobile infrastructure engineering team shares a deep dive into performance acceleration with Gradle build cache optimizations. Sinan shares their journey into solving complex build-cache problems that affect Gradle builds. By understanding the challenges and solutions found in our journey, we aim to demonstrate the possibilities for faster builds. The case study reveals how overlapping outputs and cache misconfigurations led to significant increases in build times, especially as the project scaled up with numerous modules using Paparazzi tests. The journey from diagnosing to defeating cache issues offers invaluable lessons on maintaining cache integrity without sacrificing functionality.
DEEP LEARNING FOR SMART GRID INTRUSION DETECTION: A HYBRID CNN-LSTM-BASED MODELgerogepatton
As digital technology becomes more deeply embedded in power systems, protecting the communication
networks of Smart Grids (SG) has emerged as a critical concern. Distributed Network Protocol 3 (DNP3)
represents a multi-tiered application layer protocol extensively utilized in Supervisory Control and Data
Acquisition (SCADA)-based smart grids to facilitate real-time data gathering and control functionalities.
Robust Intrusion Detection Systems (IDS) are necessary for early threat detection and mitigation because
of the interconnection of these networks, which makes them vulnerable to a variety of cyberattacks. To
solve this issue, this paper develops a hybrid Deep Learning (DL) model specifically designed for intrusion
detection in smart grids. The proposed approach is a combination of the Convolutional Neural Network
(CNN) and the Long-Short-Term Memory algorithms (LSTM). We employed a recent intrusion detection
dataset (DNP3), which focuses on unauthorized commands and Denial of Service (DoS) cyberattacks, to
train and test our model. The results of our experiments show that our CNN-LSTM method is much better
at finding smart grid intrusions than other deep learning algorithms used for classification. In addition,
our proposed approach improves accuracy, precision, recall, and F1 score, achieving a high detection
accuracy rate of 99.50%.
Presentation of IEEE Slovenia CIS (Computational Intelligence Society) Chapte...University of Maribor
Slides from talk presenting:
Aleš Zamuda: Presentation of IEEE Slovenia CIS (Computational Intelligence Society) Chapter and Networking.
Presentation at IcETRAN 2024 session:
"Inter-Society Networking Panel GRSS/MTT-S/CIS
Panel Session: Promoting Connection and Cooperation"
IEEE Slovenia GRSS
IEEE Serbia and Montenegro MTT-S
IEEE Slovenia CIS
11TH INTERNATIONAL CONFERENCE ON ELECTRICAL, ELECTRONIC AND COMPUTING ENGINEERING
3-6 June 2024, Niš, Serbia