Combined Cycle Gas Turbine Power Plant Part 1Anurak Atthasit
Introduction to Combined Cycle Gas Turbine Power Plant. Describing the advantage and design limit of the CCGT. Overview of Brayton Cycle and Rankine Cycle - showing some basic thermodynamic to explain some background of CCGT.
CFD ANALYSIS OF MULTI CYLINDER SI ENGINE USING ANSYSsiva sankar
In present century, spark ignition engines have become a non-separable part of the society, and are used in many sectors of energy. They act as backbone for transportation systems, but, as a bitter truth they behave like a major source of air pollution. There are basically three types of emissions, emerged from a SI engine; exhaust emissions, evaporative emission, and crankcase emission, and the major pollutants emerged from these engines are CO, CO2, SOX, NOX.
Present project work aims at reducing emissions. It is a well-established fact that smooth combustion minimizes the emissions, and exhaust process contributes a lot in accomplishing smooth combustion process. In present project work, different designs of exhaust manifold for a multi cylinder spark ignition engine are optimized for reducing emissions, by evaluating back pressures and exhaust velocities. For this purpose four different designs, namely, short bend centre exit, short bend side exit, long bend centre exit with reducer, and long bend side exit with reducer are considered, and their performance is evaluated for different loading conditions.
Concept Study for Adaptive Gas Turbine Rotor Bladetheijes
Articulating the pitch angle of a turbine blade can improve performance by maintaining optimum design incidence and thus reduce the probability of flow separation and thermal stresses developed due to aerothermal loads for variable speed gas turbine engine applications. Potential benefits to Army Aviation are highly efficient (aerodynamically) turbine blades, possible reduction of the need for active blade cooling and thermal barrier coatings, increased fuel efficiency, power density, and the ability to fly faster and longer. The goal of this effort is to assess the benefit and feasibility of an adaptable variable pitch turbine blade for maintaining attached flow and optimal thermal design for a gas turbine engine. A technology concept study has been conducted to enable a viable adaptable turbine rotor blade that can enhance the performance and efficiency of future aircraft gas turbine engines. A typical aircraft turbine blade is used for this technology concept study. An adaptable turbine rotor blade, if made feasible, can lead to a leap ahead technology innovation in improving part-load efficiency of gas turbine engines.
Combined Cycle Gas Turbine Power Plant Part 1Anurak Atthasit
Introduction to Combined Cycle Gas Turbine Power Plant. Describing the advantage and design limit of the CCGT. Overview of Brayton Cycle and Rankine Cycle - showing some basic thermodynamic to explain some background of CCGT.
CFD ANALYSIS OF MULTI CYLINDER SI ENGINE USING ANSYSsiva sankar
In present century, spark ignition engines have become a non-separable part of the society, and are used in many sectors of energy. They act as backbone for transportation systems, but, as a bitter truth they behave like a major source of air pollution. There are basically three types of emissions, emerged from a SI engine; exhaust emissions, evaporative emission, and crankcase emission, and the major pollutants emerged from these engines are CO, CO2, SOX, NOX.
Present project work aims at reducing emissions. It is a well-established fact that smooth combustion minimizes the emissions, and exhaust process contributes a lot in accomplishing smooth combustion process. In present project work, different designs of exhaust manifold for a multi cylinder spark ignition engine are optimized for reducing emissions, by evaluating back pressures and exhaust velocities. For this purpose four different designs, namely, short bend centre exit, short bend side exit, long bend centre exit with reducer, and long bend side exit with reducer are considered, and their performance is evaluated for different loading conditions.
Concept Study for Adaptive Gas Turbine Rotor Bladetheijes
Articulating the pitch angle of a turbine blade can improve performance by maintaining optimum design incidence and thus reduce the probability of flow separation and thermal stresses developed due to aerothermal loads for variable speed gas turbine engine applications. Potential benefits to Army Aviation are highly efficient (aerodynamically) turbine blades, possible reduction of the need for active blade cooling and thermal barrier coatings, increased fuel efficiency, power density, and the ability to fly faster and longer. The goal of this effort is to assess the benefit and feasibility of an adaptable variable pitch turbine blade for maintaining attached flow and optimal thermal design for a gas turbine engine. A technology concept study has been conducted to enable a viable adaptable turbine rotor blade that can enhance the performance and efficiency of future aircraft gas turbine engines. A typical aircraft turbine blade is used for this technology concept study. An adaptable turbine rotor blade, if made feasible, can lead to a leap ahead technology innovation in improving part-load efficiency of gas turbine engines.
Waste heat recovery system on board shipsfahrenheit
Waste heat recovery system on board ships
Marine shipping is held responsible for environmental impacts including greenhouse gas emissions, acoustic and oil pollution. The IMO estimated theses emissions to be equal to around 4.3% of the global emissions and this ratio is expected to be tripled by the year 2020. Most of the carriers used in marine transport are using diesel, steam or gas turbine propulsion power plants. Although other renewable/hybrid propulsion systems are available they still didn’t prove themselves reliable or safe to be used in variable conditions. The most common type of machinery used for propulsion is diesel and gas or steam turbine propulsion for applications where speed is critical [1] ; [2].
The internal combustion engines are one of the main sources of pollution, the recent trend to utilize the use of fuel to the maximum potential where increasing costs in energy, increase in emissions and the fear of depletion of the natural sources of fossil fuels lead to utilization of a waste heat recovery systems to improve the overall energy efficiency [3].
About 48–51% of the total heat energy of the Internal Combustion Engine is thrown back to the atmosphere without any use which considered the main source of waste heat in marine diesel engines. The waste heat recovery system can reclaim and capture the waste heat and improve the overall efficiency of the plant. The process is considered as one of the best energy saving methods to make a more efficient usage of fuels to achieve environmental improvement as shown in Fig. 1[4] ; [5].
A Compressed-air engine is a pneumatic actuator that creates usefull work by expanding compressed air. A compressed-air vehicle is powered by an air engine, using compressed air, which is stored in a tank. Instead of mixing fuel with air and burning it in the engine to drive pistons with hot expanding gases,compressed air vehicles (CAV) use the expansion of compressed air to drive their pistons.
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.
PERFORMANCE AND EMISSION CHARACTERISTICS OF BIOGAS –PETROL DUAL FUEL IN SI EN...IAEME Publication
Towards the effort of reducing the dependency on petroleum fuel, one of the solutions is to use gaseous fuel as a partial supplement of liquid petrol fuel. In this experiment, four cylinder SI engine was tested with petrol as a fuel and petrol with partial substitution of biogas as fuel. Different percentages of biogas substitution in petrol were tested like B10 (90% Petrol +10% biogas), B20(80% Petrol +20% Biogas), B40(60%Petrol +40% Biogas). Test was conducted to study and compare the performance, emission and combustion characteristic of the engine for both the modes of engine operation. Biogas production was carried out using kitchen waste as a feedstock. Results clearly revealed that performance of the engine improved with the increases in amount of the gas substitution. Bsfc and brake thermal efficiency were found to improve. However emissions increased with the increases in the amount of gas substitution.
Waste heat recovery system on board shipsfahrenheit
Waste heat recovery system on board ships
Marine shipping is held responsible for environmental impacts including greenhouse gas emissions, acoustic and oil pollution. The IMO estimated theses emissions to be equal to around 4.3% of the global emissions and this ratio is expected to be tripled by the year 2020. Most of the carriers used in marine transport are using diesel, steam or gas turbine propulsion power plants. Although other renewable/hybrid propulsion systems are available they still didn’t prove themselves reliable or safe to be used in variable conditions. The most common type of machinery used for propulsion is diesel and gas or steam turbine propulsion for applications where speed is critical [1] ; [2].
The internal combustion engines are one of the main sources of pollution, the recent trend to utilize the use of fuel to the maximum potential where increasing costs in energy, increase in emissions and the fear of depletion of the natural sources of fossil fuels lead to utilization of a waste heat recovery systems to improve the overall energy efficiency [3].
About 48–51% of the total heat energy of the Internal Combustion Engine is thrown back to the atmosphere without any use which considered the main source of waste heat in marine diesel engines. The waste heat recovery system can reclaim and capture the waste heat and improve the overall efficiency of the plant. The process is considered as one of the best energy saving methods to make a more efficient usage of fuels to achieve environmental improvement as shown in Fig. 1[4] ; [5].
A Compressed-air engine is a pneumatic actuator that creates usefull work by expanding compressed air. A compressed-air vehicle is powered by an air engine, using compressed air, which is stored in a tank. Instead of mixing fuel with air and burning it in the engine to drive pistons with hot expanding gases,compressed air vehicles (CAV) use the expansion of compressed air to drive their pistons.
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.
PERFORMANCE AND EMISSION CHARACTERISTICS OF BIOGAS –PETROL DUAL FUEL IN SI EN...IAEME Publication
Towards the effort of reducing the dependency on petroleum fuel, one of the solutions is to use gaseous fuel as a partial supplement of liquid petrol fuel. In this experiment, four cylinder SI engine was tested with petrol as a fuel and petrol with partial substitution of biogas as fuel. Different percentages of biogas substitution in petrol were tested like B10 (90% Petrol +10% biogas), B20(80% Petrol +20% Biogas), B40(60%Petrol +40% Biogas). Test was conducted to study and compare the performance, emission and combustion characteristic of the engine for both the modes of engine operation. Biogas production was carried out using kitchen waste as a feedstock. Results clearly revealed that performance of the engine improved with the increases in amount of the gas substitution. Bsfc and brake thermal efficiency were found to improve. However emissions increased with the increases in the amount of gas substitution.
Introduction to AI for Nonprofits with Tapp NetworkTechSoup
Dive into the world of AI! Experts Jon Hill and Tareq Monaur will guide you through AI's role in enhancing nonprofit websites and basic marketing strategies, making it easy to understand and apply.
The French Revolution, which began in 1789, was a period of radical social and political upheaval in France. It marked the decline of absolute monarchies, the rise of secular and democratic republics, and the eventual rise of Napoleon Bonaparte. This revolutionary period is crucial in understanding the transition from feudalism to modernity in Europe.
For more information, visit-www.vavaclasses.com
Model Attribute Check Company Auto PropertyCeline George
In Odoo, the multi-company feature allows you to manage multiple companies within a single Odoo database instance. Each company can have its own configurations while still sharing common resources such as products, customers, and suppliers.
Acetabularia Information For Class 9 .docxvaibhavrinwa19
Acetabularia acetabulum is a single-celled green alga that in its vegetative state is morphologically differentiated into a basal rhizoid and an axially elongated stalk, which bears whorls of branching hairs. The single diploid nucleus resides in the rhizoid.
The Roman Empire A Historical Colossus.pdfkaushalkr1407
The Roman Empire, a vast and enduring power, stands as one of history's most remarkable civilizations, leaving an indelible imprint on the world. It emerged from the Roman Republic, transitioning into an imperial powerhouse under the leadership of Augustus Caesar in 27 BCE. This transformation marked the beginning of an era defined by unprecedented territorial expansion, architectural marvels, and profound cultural influence.
The empire's roots lie in the city of Rome, founded, according to legend, by Romulus in 753 BCE. Over centuries, Rome evolved from a small settlement to a formidable republic, characterized by a complex political system with elected officials and checks on power. However, internal strife, class conflicts, and military ambitions paved the way for the end of the Republic. Julius Caesar’s dictatorship and subsequent assassination in 44 BCE created a power vacuum, leading to a civil war. Octavian, later Augustus, emerged victorious, heralding the Roman Empire’s birth.
Under Augustus, the empire experienced the Pax Romana, a 200-year period of relative peace and stability. Augustus reformed the military, established efficient administrative systems, and initiated grand construction projects. The empire's borders expanded, encompassing territories from Britain to Egypt and from Spain to the Euphrates. Roman legions, renowned for their discipline and engineering prowess, secured and maintained these vast territories, building roads, fortifications, and cities that facilitated control and integration.
The Roman Empire’s society was hierarchical, with a rigid class system. At the top were the patricians, wealthy elites who held significant political power. Below them were the plebeians, free citizens with limited political influence, and the vast numbers of slaves who formed the backbone of the economy. The family unit was central, governed by the paterfamilias, the male head who held absolute authority.
Culturally, the Romans were eclectic, absorbing and adapting elements from the civilizations they encountered, particularly the Greeks. Roman art, literature, and philosophy reflected this synthesis, creating a rich cultural tapestry. Latin, the Roman language, became the lingua franca of the Western world, influencing numerous modern languages.
Roman architecture and engineering achievements were monumental. They perfected the arch, vault, and dome, constructing enduring structures like the Colosseum, Pantheon, and aqueducts. These engineering marvels not only showcased Roman ingenuity but also served practical purposes, from public entertainment to water supply.
Synthetic Fiber Construction in lab .pptxPavel ( NSTU)
Synthetic fiber production is a fascinating and complex field that blends chemistry, engineering, and environmental science. By understanding these aspects, students can gain a comprehensive view of synthetic fiber production, its impact on society and the environment, and the potential for future innovations. Synthetic fibers play a crucial role in modern society, impacting various aspects of daily life, industry, and the environment. ynthetic fibers are integral to modern life, offering a range of benefits from cost-effectiveness and versatility to innovative applications and performance characteristics. While they pose environmental challenges, ongoing research and development aim to create more sustainable and eco-friendly alternatives. Understanding the importance of synthetic fibers helps in appreciating their role in the economy, industry, and daily life, while also emphasizing the need for sustainable practices and innovation.
Read| The latest issue of The Challenger is here! We are thrilled to announce that our school paper has qualified for the NATIONAL SCHOOLS PRESS CONFERENCE (NSPC) 2024. Thank you for your unwavering support and trust. Dive into the stories that made us stand out!
Embracing GenAI - A Strategic ImperativePeter Windle
Artificial Intelligence (AI) technologies such as Generative AI, Image Generators and Large Language Models have had a dramatic impact on teaching, learning and assessment over the past 18 months. The most immediate threat AI posed was to Academic Integrity with Higher Education Institutes (HEIs) focusing their efforts on combating the use of GenAI in assessment. Guidelines were developed for staff and students, policies put in place too. Innovative educators have forged paths in the use of Generative AI for teaching, learning and assessments leading to pockets of transformation springing up across HEIs, often with little or no top-down guidance, support or direction.
This Gasta posits a strategic approach to integrating AI into HEIs to prepare staff, students and the curriculum for an evolving world and workplace. We will highlight the advantages of working with these technologies beyond the realm of teaching, learning and assessment by considering prompt engineering skills, industry impact, curriculum changes, and the need for staff upskilling. In contrast, not engaging strategically with Generative AI poses risks, including falling behind peers, missed opportunities and failing to ensure our graduates remain employable. The rapid evolution of AI technologies necessitates a proactive and strategic approach if we are to remain relevant.
How to Make a Field invisible in Odoo 17Celine George
It is possible to hide or invisible some fields in odoo. Commonly using “invisible” attribute in the field definition to invisible the fields. This slide will show how to make a field invisible in odoo 17.
Operation “Blue Star” is the only event in the history of Independent India where the state went into war with its own people. Even after about 40 years it is not clear if it was culmination of states anger over people of the region, a political game of power or start of dictatorial chapter in the democratic setup.
The people of Punjab felt alienated from main stream due to denial of their just demands during a long democratic struggle since independence. As it happen all over the word, it led to militant struggle with great loss of lives of military, police and civilian personnel. Killing of Indira Gandhi and massacre of innocent Sikhs in Delhi and other India cities was also associated with this movement.
Assessing Alternative Fuels For Helicopter Operation
1. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Assessing Alternative Fuels For Helicopter
Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Presented by
A. Alexiou
Laboratory of Thermal Turbomachines
National Technical University of Athens
2. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Collaborative & Robust Engineering using
Simulation Capability Enabling Next Design Optimisation
Environmentally Compatible
Air Transport System
2
Acknowledgements
3. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
3
INTRODUCTION
MODELLING ASPECTS
o Mission Fuel Calculation
o Simulation Environment
o Helicopter-Engine Integrated Performance Model
o Alternative Fuels
CASE STUDY
o Engine Performance for Jet-A
o Helicopter Performance for Jet-A
o Effects of Alternative Fuels on Performance
SUMMARY & CONCLUSIONS
Contents
4. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
4
Introduction
Fuel Impact On Operating Costs
Year 2003 2005 2007 2009 2011
% of operating costs 14 22 28 26 30
Average price / barrel of crude ($) 28.8 54.5 73.0 62.0 110.0
Break even price / barrel ($) 23.4 51.8 82.2 55.4 112.5
Total fuel cost (bn $) 44 91 135 125 176
(http://www.iata.org/pressroom/facts_figures/fact_sheets/pages/fuel.aspx)
5. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
5
Introduction
(ACARE Beyond Vision 2020)
Global Man-Made CO2 Emissions
6. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Introduction
6
World Annual Traffic
(Airbus GMF 2010-2029)
7. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
7
Introduction
IATA VISION 2050
Build a zero-emissions commercial aircraft within 50 years
Targets
• Carbon neutral growth from 2020
• 1.5% average annual improvement of fuel efficiency
• 50% reduction of CO2 emissions by 2050 relative to 2005 levels
Four-Pillar Strategy
• Technology (IATA target is for 10% of the fuel
used will be an alternative fuel by 2017)
• Operations
• Infrastructure
• Economic measures
8. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Introduction
8
Research is mainly focused on second or new generation
bio-fuels (e.g. algae, jatropha and camelina).
Sustainable bio-fuels can reduce aviation’s net carbon
contribution on a full life-cycle basis (60-85%).
Tests demonstrated that the use of bio-fuels as ‘drop-in’
fuels is technically sound and doesn’t require any major
adaptation of the aircraft.
To date, aviation industry is cleared to use blends with up
to 50% ‘synthetic’ kerosene derived from coal, gas or biomass
and conventional jet fuel.
9. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Introduction
9
Objective
Study the effect of alternative fuels on the
performance of a medium utility helicopter
Requirement
A helicopter mission analysis tool with the capability
to use different fuels
10. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
10
INTRODUCTION
MODELLING ASPECTS
o Mission Fuel Calculation
o Simulation Environment
o Helicopter-Engine Integrated Performance Model
o Alternative Fuels
CASE STUDY
o Engine Performance for Jet-A
o Helicopter Performance for Jet-A
o Effects of Alternative Fuels on Performance
SUMMARY & CONCLUSIONS
Contents
11. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
11
H/C new
weight
6
Mission Fuel
7
H/C Specification
• Take-Off weight
• air bleed/power off-take
Air Intake losses
Exhaust losses
Mission definition
e.g. velocity, time for each
segment
Oil & Gas
SAR
Mission Fuel Calculation
ENGINE PERFORMANCE
MODEL
Fuel Flow
Rate 5
FUEL
MODEL
1
MISSION PROFILE
3
H/C operating
conditions
H/C requirements
(power, air cabin off
take, Nrotor)
2
H/C PERFORMANCE MODEL
4 -200
0
200
400
600
800
1000
1200
1400
1600
1800
0 10 20 30 40 50
Time (min)
Altitude
[m]
12. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Object-Oriented
Steady State
Transient
Mixed-Fidelity
Multi-Disciplinary
Distributed
Multi-point Design
Off-Design
Test Analysis
Diagnostics
Sensitivity
Optimisation
Deck Generation
12
Simulation Platform
PROOSIS (PRopulsion Object-Oriented SImulation Software)
13. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
13
Simulation Platform
TURBO library
of gas turbine
components
Industry-
accepted
performance
modelling
techniques
Respects
international
standards in
nomenclature,
interface & OO
programming
14. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
14
Simulation Platform
15. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
15
Simulation Platform
Total helicopter power
Main rotor power
Induced
Profile
Fuselage
Potential energy change
Tail rotor power
Customer power extraction
Gearbox power losses
16. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
16
Integrated Model
17. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
17
Integrated Model
Engine Component
18. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
18
Integrated Model
Engine Component
Helicopter Component (black box or PROOSIS model)
19. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Integrated
Helicopter-Engine
Component
19
Integrated Model
Engine Component
Helicopter Component (black box or PROOSIS model)
20. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
20
Alternative Fuels
FUEL H:C RATIO LHV (MJ/kg) DENSITY (kg/m3)
Jet-A 1.917 43.12 Ref. 801.0 Ref
Synjet (FT) 2.166 43.94 1.9% 762.4 -4.8%
S8 (FT-GTL) 2.169 43.90 1.8% 756.0 -5.6%
Jatropha Algae (HRJ) 2.119 44.20 2.5% 748.0 -6.6%
Blend
50% Jet-A + 50% Jatr.
2.017 43.70 1.34% 780.0 -2.6%
FT: Fischer-Tropsch
HRJ: Hydrotreated Renewable Jet
GTL: Gas-to-Liquid
Low aromatics content
Absence of natural anti-oxidants
Low electrical conductivity
Poor lubrication properties
Erroneous fuel metering
Accelerated wear of fuel system O-rings/seals
Fuel degradation in long-term storage
High pressure fuel pump wear
Increased fire hazard
Biodiesel (Soybean) 1.855 38.00 -11.9% 880.0 9.9%
21. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
21
Alternative Fuels
FUEL H:C RATIO LHV (MJ/kg) DENSITY (kg/m3)
Jet-A 1.917 43.12 Ref. 801.0 Ref
Synjet (FT) 2.166 43.94 1.9% 762.4 -4.8%
S8 (FT-GTL) 2.169 43.90 1.8% 756.0 -5.6%
Jatropha Algae (HRJ) 2.119 44.20 2.5% 748.0 -6.6%
Blend
50% Jet-A + 50% Jatr.
2.017 43.70 1.34% 780.0 -2.6%
PROOSIS TURBO library uses 3-D tables to
calculate the caloric properties of the working fluid in
the engine model generated with the NASA CEA
software (no dissociation)
Biodiesel (Soybean) 1.855 38.00 -11.9% 880.0 9.9%
22. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
22
INTRODUCTION
MODELLING ASPECTS
o Mission Fuel Calculation
o Simulation Environment
o Helicopter-Engine Integrated Performance Model
o Alternative Fuels
CASE STUDY
o Engine Performance for Jet-A
o Helicopter Performance for Jet-A
o Effects of Alternative Fuels on Performance
SUMMARY & CONCLUSIONS
Contents
23. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
23
Engine Performance
PARAMETER MCP TOP OEI30
Power Delivered [kW] 1056 1252 1437
Torque Delivered [Nm] 1681 1992 2287
Overall Pressure Ratio 11.6 12.6 13.3
Power Turbine Inlet Temperature [K] 977 1034 1108
Inlet Air Mass Flow Rate [kg/s] 4.6 4.8 4.94
Gas Generator Speed [rpm] 38946 40205 41700
Specific Fuel Consumption [kg/kWh] 0.280 0.271 0.269
Sea-level standard conditions
24. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
24
Engine Performance
PARAMETER MCP TOP OEI30
Power Delivered [kW] 1056 1252 1437
Torque Delivered [Nm] 1681 1992 2287
Overall Pressure Ratio 11.6 12.6 13.3
Power Turbine Inlet Temperature [K] 977 1034 1108
Inlet Air Mass Flow Rate [kg/s] 4.6 4.8 4.94
Gas Generator Speed [rpm] 38946 40205 41700
Specific Fuel Consumption [kg/kWh] 0.280 0.271 0.269
Sea-level standard conditions
25. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
0
200
400
600
800
1000
1200
220 230 240 250 260 270 280 290 300 310 320 330
PWSD
[kW]
Tamb [K]
0
1000
2000
3000
4000
5000
6000
7000
Altitude
Maximum Continuous Power (MCP) Rating
Engine Performance
25
26. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Engine Performance
26
0
100
200
300
400
500
600
700
500 1000 1500 2000 2500
WF/(δ*θ
1/2
)
(kg/h)
PWSD/(δ*θ1/2) (kW)
MCP
TOP
OEI30
27. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Engine Performance
27
0.25
0.35
0.45
0.55
0.65
0.75
0.85
0.95
50 250 450 650 850 1050 1250 1450
SFC
(kg/kW.h)
PWSD (kW)
MCP TOP OEI30
28. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Helicopter Performance
28
PARAMETER SYMBOL VALUE UNITS
Maximum Take-off Weight MTOW 7400 kg
Weight Empty WE 4105 kg
Fixed Useful Load FUL 200 kg
Fuel Capacity VFu 1.45 m3
Number of Engines Neng 2 -
Number of Rotor Blades Nb 4 -
Main Rotor Diameter D 15.2 m
Main Rotor Blade Chord c 0.49 m
Main Rotor Solidity σ 0.08 -
Rotor Blade Tip Speed U 223 m/sec
Rotor Speed NR 280 rpm
Equivalent Flat Plate Area SCx 3.0 m2
Power Extraction Pex 10 kW
29. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
0
500
1000
1500
2000
2500
0 20 40 60 80 100
Power
Required
[kW]
True Airspeed [m/s]
5000 m
4000 m
3000 m
2000 m
1000 m
SL
MCP at SL
MCP at 5000 m
Helicopter Performance
29
Jet-A / MTOW / STD
30. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Helicopter Performance
30
3500
4000
4500
5000
5500
6000
6500
7000
7500
0
2
4
6
8
10
12
14
16
18
20
0 20 40 60 80 100
Max
Altitude
[m]
Max
Rate
of
Climb
[m/s]
True Airspeed [m/s]
Max Rate of Climb at 0 m
Max Rate of Climb at 2000 m
Max Altitude
Jet-A / MTOW / STD
31. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Helicopter Performance
31
0
0.05
0.1
0.15
0.2
0
100
200
300
400
500
600
700
0 20 40 60 80 100
Fuel
Flow
[kg/s]
Specific
Range
[m/kg]
True Airspeed [m/s]
Specific Range
Fuel Flow
Vbe Vbr
SR = Vx / Wfuel
Jet-A / MTOW / SL / STD
32. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Helicopter Performance
32
0
500
1000
1500
2000
2500
3000
3500
0 200000 400000 600000 800000
PAYLOAD
[kg]
RANGE [m]
Full Fuel Line
Jet-A
33. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Effects of Alternative Fuels
33
Fixed PWSD (TOP for Jet-A)
Fixed XNH (TOP rating)
34. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Effects of Alternative Fuels
34
-4
-2
0
2
4
6
8
10
12
14
Synjet S8 (GTL) Jatropha/Algae
(HRJ)
50% JetA+50%
Jatr/Alg
Biodiesel
(Soybean)
WFu
%
Difference
from
JetA
PWSD at MCP for JetA
PWSD at TOP for JetA
PWSD at OEI30 for JetA
35. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
0
500
1000
1500
2000
2500
0 10 20 30 40 50 60
Altitude
[m]
Time [min]
Effects of Alternative Fuels
35
Warm up at MCP [2’]
Take-Off [2’]
Climb at Vbe & Vz,max [2’]
Cruise at Vbr [40’]
Descent [4’]
Land [2’]
36. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Effects of Alternative Fuels
36
6800
6900
7000
7100
7200
7300
7400
7500
0 10 20 30 40 50 60
Helicopter
Weight
[kg]
Time [min]
JetA Synjet
S8 (GTL) Jatropha Algea
50% JetA + 50% JA Biodiesel
CRUISE
CLIMB
DESCENT
LAND
T/O
37. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Effects of Alternative Fuels
37
-4
-2
0
2
4
6
8
10
12
14
16
Synjet S8 (GTL) Jatropha Algea
(HRJ)
50% JetA + 50%
Jatr/Alg
Biodiesel
(Soybean)
%
Change
in
Mission
Fuel
38. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
-4
-2
0
2
4
6
8
10
12
14
16
Synjet S8 (GTL) Jatropha Algea
(HRJ)
50% JetA + 50%
Jatr/Alg
Biodiesel
(Soybean)
%
Change
in
Mission
Fuel
Full Tanks
Same GTOW
Effects of Alternative Fuels
38
39. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Effects of Alternative Fuels
39
530
550
570
590
610
630
650
670
690
710
730
4400 4900 5400 5900 6400 6900 7400
Specific
Range
[m/kg]
Helicopter Weight [kg]
Jet-A Synjet
S8 (GTL) Jatropha Algea
50% JetA +50% JA Biodiesel
40. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
0
500
1000
1500
2000
2500
500000 600000 700000
PAYLOAD
[kg]
RANGE [m]
JetA Synjet
S8 (GTL) Jatropha Algea
50% JetA - 50% JA Biodiesel
Effects of Alternative Fuels
40
41. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
41
INTRODUCTION
MODELLING ASPECTS
o Mission Fuel Calculation
o Simulation Environment
o Helicopter-Engine Integrated Performance Model
o Alternative Fuels
CASE STUDY
o Engine Performance for Jet-A
o Helicopter Performance for Jet-A
o Effects of Alternative Fuels on Performance
SUMMARY & CONCLUSIONS
Contents
42. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Summary & Conclusions
42
An integrated performance model of a helicopter and its turboshaft
engine has been created in an object-oriented simulation environment to
study the effects of alternative fuels on helicopter operation.
For the fuels considered in this study there are no significant effects
on the engine cycle compared to Jet-A except for the fuel flow rate that
changes according to the difference of each fuel’s lower heating value
from the reference one.
Considering the helicopter in a mission, there is an added effect from
the differences in density between the fuels that modifies the helicopter’s
payload-range capability.
Based on the modelling assumptions, the blended fuel appears at the
moment as the most suitable choice for the aspects considered in the
presented analysis (e.g. taking into account its effects on engine cycle
parameters and helicopter operational characteristics) but other
parameters should also be taken into account to allow for a more
complete assessment (e.g. economics of fuel production, emissions, etc.).
43. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Summary & Conclusions
43
The method presented herein can be further extended by including
models of other disciplines in the existing integrated model (e.g.
economics, noise and particulate emissions, etc.). This would allow the
required multi-disciplinary calculations (including design and
optimisation) to be performed in a single simulation environment with all
the associated benefits that such an approach offers (configuration
management control, transparent exchange of information between
modules, common modelling standards, flexible mathematical model
handling, etc.).
44. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Summary & Conclusions
44
ATLAS
Aero-TooLs for Advanced Simulations
45. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
Summary & Conclusions
45
Finally, by creating a library of specific aircrafts (rotary or fixed wing)
and a corresponding one with engines (turboshafts, turbofans, etc.) one
can perform such studies for various combinations of current and
future aircraft-engine models.
Library of Gas Turbine Engines
46. Assessing Alternative Fuels For Helicopter Operation
Alexiou, Tsalavoutas, Pons, Aretakis, Roumeliotis, Mathioudakis
Click to edit Master title style
46
THANK YOU
Laboratory of Thermal Turbomachines
National Technical University of Athens