The document describes a student project to develop a pulsejet-rotor engine. A pulsejet engine uses combustion pulses for propulsion and has simplicity, low cost, and high thrust-to-weight. The students designed a prototype engine with 3 pulsejets arranged circularly to drive cups and create rotational motion. Testing showed the design was feasible but would require fuel control and cooling to optimize performance. While pulsejets are more efficient than other jets, challenges include low average pressure and high temperatures.
Design and Optimization of Valveless Pulsejet EngineIJERA Editor
Simple design and efficiency make pulsejet engines attractive for aeronautical short-term operation applications.
An active control system extends the operating range and reduces the fuel consumption considerably so that this
old technology might gain a new interest. During the operations of these pulsejet engines the surfaces of engine
will get more heated. In order to cool the engine surface and to get more thrust we have attached an additional
component called secondary inlet in that valve less pulsejet engine. The pulsejet is the only jet engine combustor
that shows a net pressure gain between the intake and the exhaust. The pulsejet is the only jet engine combustor
that shows a net pressure gain between the intake and the exhaust. We choose the LOCKWOOD’s design of
pulsejet engine. By using the CFD analysis we have analysed the modified design of valveless pulsejet engine.
This project provides an overview of this unique process and the results of these design modifications are
reported.
Design and Optimization of Valveless Pulsejet EngineIJERA Editor
Simple design and efficiency make pulsejet engines attractive for aeronautical short-term operation applications.
An active control system extends the operating range and reduces the fuel consumption considerably so that this
old technology might gain a new interest. During the operations of these pulsejet engines the surfaces of engine
will get more heated. In order to cool the engine surface and to get more thrust we have attached an additional
component called secondary inlet in that valve less pulsejet engine. The pulsejet is the only jet engine combustor
that shows a net pressure gain between the intake and the exhaust. The pulsejet is the only jet engine combustor
that shows a net pressure gain between the intake and the exhaust. We choose the LOCKWOOD’s design of
pulsejet engine. By using the CFD analysis we have analysed the modified design of valveless pulsejet engine.
This project provides an overview of this unique process and the results of these design modifications are
reported.
This presentation was prepared by Mechanical Engineering students during their Internal Combustion Course. Students belong to a very prestigious Engineering institute of Pakistan "University of Engineering and Technology Lahore"
Technological advancements in IC enginesSyed Yaseen
This presentation is a part of IC engines online course where you will learn about the Technological advancements in IC engines. All the slides are filled with related graphics to help you understand the concept easily.
A gas turbine, also called a combustion turbine, is a type of internal combustion engine. It has an upstream rotating compressor coupled toa downstream turbine, and a combustion chamber in-between. Energy is added to the gas stream in the combustor, where fuel is mixed with air and ignited. In the high-pressure environment of the combustor, combustion of the fuel increases the temperature. The products of the combustion are forced into the turbine section
Visit https://www.topicsforseminar.com to Download
The gas turbine is an internal combustion engine that uses air as the working fluid. The engine extracts chemical energy from fuel and converts it to mechanical energy using the gaseous energy of the working fluid (air) to drive the engine and propeller, which, in turn, propel the airplane.
study of jet engines & how they works
1.History of jet engine 2. Introduction 3. Parts of jet engine 4. How a get engine works 5. Types of jet engine (i) Ramjet (ii) Turbojet (iii) Turbofan (iv) Turboprop (v) Turbo shaft 6.Comparison of Turbo Jet 7.Jet engines Vs Rockets 8.Difficulties 9.Suggestion for improvement 10. Merit and Demerits 11. Jet engine uses 12.Conclusion 13.Future vision
PPT describes the engine performance parameters of the I.C. engine.
Engine performance is an indication of the degree of success of the engine performs its assigned task, i.e. the conversion of the chemical energy contained in the fuel into the useful mechanical work. The engine performance is indicated by the term efficiency, η. Five important engine efficiencies and other related engine performance parameters are:
Power
Indicated Thermal Efficiency (ηith)
Brake Thermal Efficiency (ηbth)
Mechanical Efficiency (ηm)
Volumetric Efficiency (ηv)
Relative Efficiency or Efficiency Ratio (ηrel)
Mean Effective Pressure (Pm)
Specific Fuel Consumption (sfc)
Fuel-Air or Air-Fuel Ratio (F/A or A/F)
Calorific Value (CV)
Power:-
The main purpose of running an engine is to obtain mechanical power.
Brake Power (B.P.)
The power developed by an Engine at the output shaft is called the brake power.
Brake Power= Brake Workdone/Time
B.P.=BWD/sec.
Indicated power (I.P.)
The total power developed by Combustion of fuel in the combustion chamber is called indicated power.
Indicated Power= Indicated Workdone/Time
I.P.=IWD/sec.
Frictional Power (F.P.)
The difference between I.P. and B.P. is called frictional power (f.p.).
FP = IP – BP
Thermal Efficiency (ηth)
Thermal efficiency is the ratio of Power to energy supplied by the fuel.
ηth= Power/ Energy
In I.C. Engine, thermal efficiency can be classified into two categories i.e.
Indicated Thermal Efficiency (ηith)
Indicated thermal efficiency is the ratio of indicated power to the heat supplied or added.
ηith= IP/Qs
2. Brake Thermal Efficiency (ηith)
Brake Thermal Efficiency is the ratio of brake power to the heat supplied or added.
ηbth= BP/Qs
Volumetric Efficiency (ηv)
This is one of the most important parameters which decide the performance of four-stroke engines. Four stoke engines have distinct suction stoke, volumetric efficiency indicates the breathing ability of the engine.
Volumetric efficiency is defined as the ratio of actual flow rate of air into the intake system to rate at which the volume is displaced by the system.
ηv= (푚 ̇"a/a" )/(푉푑푖푠푝푎푐푒푑 푋 푁/2)
"a"= Inlet density is taken atmospheric air density
N= Number of the cylinder in use
This presentation was prepared by Mechanical Engineering students during their Internal Combustion Course. Students belong to a very prestigious Engineering institute of Pakistan "University of Engineering and Technology Lahore"
Technological advancements in IC enginesSyed Yaseen
This presentation is a part of IC engines online course where you will learn about the Technological advancements in IC engines. All the slides are filled with related graphics to help you understand the concept easily.
A gas turbine, also called a combustion turbine, is a type of internal combustion engine. It has an upstream rotating compressor coupled toa downstream turbine, and a combustion chamber in-between. Energy is added to the gas stream in the combustor, where fuel is mixed with air and ignited. In the high-pressure environment of the combustor, combustion of the fuel increases the temperature. The products of the combustion are forced into the turbine section
Visit https://www.topicsforseminar.com to Download
The gas turbine is an internal combustion engine that uses air as the working fluid. The engine extracts chemical energy from fuel and converts it to mechanical energy using the gaseous energy of the working fluid (air) to drive the engine and propeller, which, in turn, propel the airplane.
study of jet engines & how they works
1.History of jet engine 2. Introduction 3. Parts of jet engine 4. How a get engine works 5. Types of jet engine (i) Ramjet (ii) Turbojet (iii) Turbofan (iv) Turboprop (v) Turbo shaft 6.Comparison of Turbo Jet 7.Jet engines Vs Rockets 8.Difficulties 9.Suggestion for improvement 10. Merit and Demerits 11. Jet engine uses 12.Conclusion 13.Future vision
PPT describes the engine performance parameters of the I.C. engine.
Engine performance is an indication of the degree of success of the engine performs its assigned task, i.e. the conversion of the chemical energy contained in the fuel into the useful mechanical work. The engine performance is indicated by the term efficiency, η. Five important engine efficiencies and other related engine performance parameters are:
Power
Indicated Thermal Efficiency (ηith)
Brake Thermal Efficiency (ηbth)
Mechanical Efficiency (ηm)
Volumetric Efficiency (ηv)
Relative Efficiency or Efficiency Ratio (ηrel)
Mean Effective Pressure (Pm)
Specific Fuel Consumption (sfc)
Fuel-Air or Air-Fuel Ratio (F/A or A/F)
Calorific Value (CV)
Power:-
The main purpose of running an engine is to obtain mechanical power.
Brake Power (B.P.)
The power developed by an Engine at the output shaft is called the brake power.
Brake Power= Brake Workdone/Time
B.P.=BWD/sec.
Indicated power (I.P.)
The total power developed by Combustion of fuel in the combustion chamber is called indicated power.
Indicated Power= Indicated Workdone/Time
I.P.=IWD/sec.
Frictional Power (F.P.)
The difference between I.P. and B.P. is called frictional power (f.p.).
FP = IP – BP
Thermal Efficiency (ηth)
Thermal efficiency is the ratio of Power to energy supplied by the fuel.
ηth= Power/ Energy
In I.C. Engine, thermal efficiency can be classified into two categories i.e.
Indicated Thermal Efficiency (ηith)
Indicated thermal efficiency is the ratio of indicated power to the heat supplied or added.
ηith= IP/Qs
2. Brake Thermal Efficiency (ηith)
Brake Thermal Efficiency is the ratio of brake power to the heat supplied or added.
ηbth= BP/Qs
Volumetric Efficiency (ηv)
This is one of the most important parameters which decide the performance of four-stroke engines. Four stoke engines have distinct suction stoke, volumetric efficiency indicates the breathing ability of the engine.
Volumetric efficiency is defined as the ratio of actual flow rate of air into the intake system to rate at which the volume is displaced by the system.
ηv= (푚 ̇"a/a" )/(푉푑푖푠푝푎푐푒푑 푋 푁/2)
"a"= Inlet density is taken atmospheric air density
N= Number of the cylinder in use
There are 5 types of jet propulsion engine such as turbojet, turbofan, turboprop, turbo-shaft, and ramjet.Some types of jet propulsive engine are not cover in this slide such as pulse engine and rocket.
This presentation had been prepared for the aircraft propulsion class to my undergraduate and graduate students at Kasetsart University and Chulalongkorn University - Bangkok, Thailand.
this presentation is very easy to understand the main difference between nano robots and fractal robots...
i have prepared this for to understand the actual topic easily..more over i added a beautiful and stylish pictures to attract the people's attention....
Thermodynamic design of a Turbojet engine for the given conditions of altitude and speed. Blade geometry was taken into consideration for this project. A Matlab program was written to calculate the best compressor ratio, temperatures and geometry to obtain maximum thrust. Inlet and Nozzle were drafted using CREO Parametric.
Presentation on Power Saving from Two – Wheeler Bike SilencerMd Anzar Aman
I have installed a mechanism with an axial high pressure reaction
turbines including a backward curved reaction turbine (Exhaust
Fan Blade) in a single shaft with an electrical generator which will
convert the kinematic energy into mechanical work and by
mechanical work we can generate electricity, when the pressure
energy of hot gases flows
GEOMETRIC OPTIMIZATION OF CRANK SHAFT FOR OPTIMUM DESIGN AND IMPROVEMENT OF LIFEIjripublishers Ijri
Crankshaft is a component in an engine which converts the reciprocating motion of the piston to the rotary motion. Design
of a crankshaft of Honda engine, it is assembled by the connecting rod and piston components in Pro engineering.
The designed model of engine crankshaft is analyzed in pro engineering by using its mechanism. Piston generates the
forces due to the combustion. These forces acting on the piston are analyzed by using their mechanisms with respect
to crank angle.
DYNAMIC ANALYSIS OF ENGINE BLOCK FOR SELECTION OF SUITABLE MATERIAL FOR COST ...Ijripublishers Ijri
The Aim of this project is to design a combustion chamber using Pro-E and perform analysis using ANSYS software.
The analysis of the combustion chamber is done by using different materials. By conducting the above analysis on the
combustion chamber combustion rate, pressure and temperature gradient conditions are found and the best material
for the combustion chamber is suggested.
Thermal analysis is conducted to find heat dissipation rate in engine block with the variation of materials Structural
and fatigue analysis(dynamic) is conduct on engine block at working load conditions to evaluate and compare stress,
strain, deformation and fatigue life with the variation of materials.
Frequency analysis is conducted on engine block with the variation of materials to evaluate frequency,
Using these values material selection will be done, the value should be nearby previous one (cast iron) maximum accepted
variation value 65HZ.
The aim of this project is to design a positive displacement rotary pump for small scale applications. The design is in such a way that it combines the advantages of both rotodynamic and positive displacement pumps. Currently available centrifugal pumps cannot attain high heads, and reciprocating pumps are less efficient and requires much space. When centrifugal pump is used as a jet pump, it delivers fluids at a high head, but in the expense of efficiency.
To overcome these negatives of currently available pumps, a new design of a rotary type positive displacement pump is developed. This design imitates the working of a normal reciprocating pump, but in a rotary action. This consumes less space compared to a reciprocating pump of same capacity. The main part of the pump is a cam which is mounted on a rotating shaft that rotates in a cylindrical casing. The cam is designed in such a way that it always maintains contact with the walls of the casing as it rotates. A spring loaded blade acts as the cam follower and moves in an accurately machined slot in the casing. The blade and the slot are of rectangular cross section. This blade separates suction and delivery sides of the pump. Inlet and outlet ports are placed on either sides of this blade. This pump does not require inlet and outlet valves. The discharge from the pump is continuous. It also eliminates the crank and connecting-rod mechanisms and delivers a smooth operation.
Diesel Injectors are one of the changing parameters in engine design. Piezoelectric Diesel Injectors are one of the changing designs adopted in engine systems especially CRDi engines. It enables better fuel economy and emission control. This paper provides with an overview, design and constructional features, working and applications of piezoelectric diesel Injectors.
A Comparative Performance Analysis DCR and DAR Squirrel Cage 3-Phase Inductio...paperpublications3
Abstract: The importance of energy saving in induction motor was emphasized about 15 years ago, in academic area, but the motor manufacturer’s interest is focussed only on maximum benefit. As a customer, it is better to take into account not only the motor price, but also the cost of the used energy during the whole lifetime of the motor. The new requirement to improve the motor efficiency is a serious research subject, which must be about the possibility of loss minimization in the induction motor.
On an average the cost of energy consumed by the motor is nearly 80 – 100 times the initial cost of the initial manufacturing cost of the motor. So the efficiency of motor is of great importance whether during the selection or during the operation. Small increase in motor efficiency can make an overall significant difference in total energy consumption.
The slightly higher initial cost of DCR motors is often misunderstood as a demerit. It is not all true. The increase in initial cost is offset by the energy saving.
This paper presents the comparative analysis of performance of a DCR motor and DAR motor. The method of analysis is based upon testing results. The only change in design is that the Die cast aluminium rotor is replaced by die cast copper rotor. The other design parameters like stator core, winding, air gap length etc are remains same.
Ceiling fan is mostly driven by the single induction motor with an efficiency of 30%.
The BLDC motor is popular now a days for a high efficiency, compactness and controllability.
International Journal of Engineering and Science Invention (IJESI)inventionjournals
International Journal of Engineering and Science Invention (IJESI) is an international journal intended for professionals and researchers in all fields of computer science and electronics. IJESI publishes research articles and reviews within the whole field Engineering Science and Technology, new teaching methods, assessment, validation and the impact of new technologies and it will continue to provide information on the latest trends and developments in this ever-expanding subject. The publications of papers are selected through double peer reviewed to ensure originality, relevance, and readability. The articles published in our journal can be accessed online.
Ijri te-03-010 cfd analysis on ejector cooling system with variable throat ge...Ijripublishers Ijri
The vapor jet ejector cooling cycle driven by waste heat. It is a very auspicious approach of producing ‘free cooling’ by
utilizing low-grade energy sources. The mechanism behind the ejector-based on waste heat cooling is very unique, when
compared to absorption or adsorption cooling technologies. They are also aimed at producing heat driven cooling. This
type of ejector cooling system is actually more closely related to vapor compression technology.
In this paper simulations of a vapor-jet ejector operating with refregerent R134a as the working fluid by using CFD
(computational fluid dynamics). The impact of varying geometry parameters on ejector performance will be considered.
Different mixing section radii will be considered for the analysis.
3D modeling is done by using Catia V5 and analysis is done by Ansys fluent14.5.
Design and Analysis of Inlet and Exhaust Valve Springs for High Speed Engines...
pulsejet
1. “PULSEJET–ROTOR ENGINE”
Report of the 8th Semester Project Work
SUBMITTED BY:
NAVEEN. S (3VC09ME060)
K.V.MANJUNATHA (3VC10ME037)
SUNDEEP KUMAR.T (3VC09ME102)
RAVI TEJ REDDY.H (3VC09ME085)
Under the guidance of
MANJUNATH SWAMY
Assistant Professor
Department of Mechanical Engineering
2. Introduction
A pulse jet engine (or pulsejet) is a type of jet engine in
which combustion occurs in pulses.
Pulsejet engines are characterized by simplicity, low cost
of construction, high noise levels and thrust-to-weight
ratio is excellent.
They are mechanically very simple and have very less
moving parts.
Theoretically the pulsejet engine has higher efficiency
than the normal jet engine.
Another key factor is that, as the combustion occurs in
pulses, constant combustion of fuel is achieved.
3. Literature Survey
• The experiments conducted by THE HILLER AIRCRAFT
CORPORATION is specifically important to the current study.
• Hiller worked on scaling down the valveless pulsejets. The
smallest pulsejet they were able to operate, had a
combustion chamber of dia 19cm & an overall length of
31cm
• This configuration was quite temperamental & hard to
operate on consistent basis.
• It operated more as pulsed rocket rather than a pulsed jet.
• However this study was very beneficial in having a base line
with which to compare.
4. • MICHAEL SCHOEN’s research was directed
towards the miniaturization of valveless
pulsejets.
• His efforts were to understand the physical
effects on engine performance subject to the
changes in jet geometry.
• ADAM KIKER’s work focused on the development
of micro-scale pulsejets.
• He was able to design and operate a record 8cm
long, air breathing, hydrogen fueled pulsejet.
5. • ODON contributed for the development of 5cm
pulsejet by the application of platinum coating on
the combustion chamber walls.
• Odon was able to run it in both valved and valve
less configurations.
• Odon made a formulation of an analytical model
to predict the operating frequency of any valve
less pulsejet.
• DANIEL PAXON at NASA Glenn research center used
a 50 cm hobby scale pulsejet similar to that used
by Odon.
7. Our pulsejet resembles to the pulsejet of Daniel Paxon but
differs in the dimensions of tail pipe.
Out of various types of pulsejets, the pulsejet we used fall
under the class of the SIDEWINDERS.
8. Reasons for developing this idea
Efficiency of pulsejet is high compared to IC engines.
It has simple and low cost construction and can be
scaled to any size.
They have very less moving parts, and hence
mechanical efficiency is high.
So the basic concept of “pulse jet rotary engine” is
to combine the effectiveness of pulse jet with
purpose and practicality of IC engine.
9. Working:
The LENOIR CYCLE is an idealized thermodynamic
cycle often used to model a pulsejet engine.
In this cycle, an ideal gas undergoes
1-2: Constant volume heat addition
2-3: Isentropic expansion
3-1: Constant pressure heat rejection.
The expansion process is isentropic and hence
involves no heat interaction. Energy is absorbed as
heat during the isochoric heating and rejected as
work during the isentropic expansion. Waste heat
is rejected during the isobaric cooling.
12. The working is based on KADENACY EFFECT
The expanding gas out of the engine all the way until the
pressure in the chamber falls below atmospheric. The
opposite thing happens in the next part of the cycle, when
the outside air pushes its way in to fill the vacuum. The
combined momentum of the gases rushing in through the
two opposed ports causes the chamber briefly to be
pressurized above atmospheric before ignition.
Thus there is an oscillation of pressure in the engine
caused by inertia. The gases involved in the process are
stretched and compressed between the inside and outside
pressures like an elastic medium. This kind of effect is
called the KADENACY EFFECT.
14. Construction
As shown below, 3 pulse jets are arranged in a
circular fashion (120 degrees apart)
Due to the impulse of pulse output from pulsejets
tangential force is impacted on cups. Due to this
tangential force couple is formed thus rotary motion is
obtained.
Thrust from the pulses are thus converted to
rotary motion.
19. Materials used
Stainless Steel (commercial name-SS 304) for
pulsejet body.
1 cm copper tubes for fuel supply.
Mild steel cover plates.
20 mm hollow MS shaft.
22 mm Bosch bearings with its housing.
Two wheeler sparkplug.
1” square pipes for engine mount.
20. Engine fabrication
Stainless steel tubes of 1”,12 and 8 mm dia are
cut according to requirement and welded.
Blades are shaped and modified based on
requirement. They are mounted on a circular
frame which in turn welded onto bearings.
21. Fuel Used
Liquid petroleum gas (C3H8) is used as
pulsejet fuel but pulse jets works on
variety of fuels such as gasoline,
kerosene, liquid propane , natural gas
etc..,
22. Plan of action proposed
1.Final assembly
All the sub-assembly parts are assembled
and engine will be enclosed by cover
plates.
2.Testing
The pulsejet is tested for its functionality.
23. Progress done in the project
so far
As per the plan of action we have successfully
developed and fabricated a complete working
model of pulse jet.
This helped us understand the fabrication
difficulties and the design considerations that
we will have to make in the final model. Further
we tested this model by considering various
aspects of design as to develop more efficient
final model.
24. Results
By directing the output thrust from 3 pulsejets on to the
rotary blades, it is possible to convert the thrust energy to
rotary motion.
As 3 pulsejets have to be synchronized to have optimum
power, computer controlled fuel supply is required.
This also requires cooling system to cool down the pulsejets
since its working temperature is generally well above 800oc.
It is simple and attractive, but it also has its disadvantages.
The promise of pulsejets on its own, outside a turbojet, is
less significant.
The average pressure in working cycle is low.
25. Conclusion
As it is generally known that pulsejets are more efficient
than any other jet engines, they can be used to derive
power from the fuel more efficiently.
Thus it is possible to replace the current combustion
chamber of an IC engine to a pulsejets because of design
simplicity, no moving parts and power to weight ratio.
Finally, a simple light weight pulsejet seems much
appropriate for both flying and general purpose engines.
26. References
"A historical review of valve less pulsejet"
designs by Bruno Ogorelec
http://www.frenchgeek.com/pulsejet.php - A
detailed guide documenting all the steps
required to build one's own Pulsejet.
PETA (Pulse-Ejector-Thrust-Augmentors) article
www.becktechnologies.com
www.xjet/pulsejet-argusV1.com
Aviastar information on Hiller rotor-tips
“Dave Brill” has give us a lot of information
about the pulsejet theory