Presentation is loading. Please wait.

Presentation is loading. Please wait.

Gas Turbine Combustion and Power Generation

Published byJustin Robinson Modified over 9 years ago

Similar presentations

Presentation on theme: "Gas Turbine Combustion and Power Generation"— Presentation transcript:

1 Gas Turbine Combustion and Power Generation
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Gas Turbine Combustion and Power Generation Dr. A. Kushari Department of Aerospace Engineering

2 Outline Introduction Advantages and Disadvantages Future Requirements
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Outline Introduction Advantages and Disadvantages Future Requirements Gas Turbine Combustors Ongoing Research Conclusions Acknowledgement

3 TURBINES: Machines to extract fluid power from flowing fluids
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. TURBINES: Machines to extract fluid power from flowing fluids Steam Turbine Water Turbines Wind Turbines Gas Turbines High Pressure, High Temperature gas Generated inside the engine Expands through a specially designed TURBINE Aircraft Engines Power Generation

4 GAS TURBINES Invented in 1930 by Frank Whittle Patented in 1934
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. GAS TURBINES Invented in 1930 by Frank Whittle Patented in 1934 First used for aircraft propulsion in 1942 on Me262 by Germans during second world war Currently most of the aircrafts and ships use GT engines Used for power generation Manufacturers: General Electric, Pratt &Whitney, SNECMA, Rolls Royce, Honeywell, Siemens – Westinghouse, Alstom Indian take: Kaveri Engine by GTRE (DRDO)

5 PRINCIPLE OF OPERATION
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. PRINCIPLE OF OPERATION Intake Slow down incoming air Remove distortions Compressor Dynamically Compress air Combustor Heat addition through chemical reaction Turbine Run the compressor Nozzle/ Free Turbine Generation of thrust power/shaft power

6 Advantages and Disadvantages
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Advantages and Disadvantages Great power-to-weight ratio compared to reciprocating engines. Smaller than their reciprocating counterparts of the same power. Lower emission levels Expensive: high speeds and high operating temperatures designing and manufacturing gas turbines is a tough problem from both the engineering and materials standpoint Tend to use more fuel when they are idling They prefer a constant rather than a fluctuating load. That makes gas turbines great for things like transcontinental jet aircraft and power plants, but explains why we don't have one under the hood of our car.

7 Emission in Gas Turbines
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Emission in Gas Turbines Lower emission compared to all conventional methods (except nuclear) Regulations require further reduction in emission levels

8 Needs for Future Gas Turbines
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Needs for Future Gas Turbines Power Generation Fuel Economy Low Emissions Alternative fuels Military Aircrafts High Thrust Low Weight Commercial Aircrafts Low emissions Half the size and twice the thrust Double the size of the Aircraft and double the distance traveled with 50% NOx

9 Gas Turbine Combustion
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Gas Turbine Combustion F/A – 0.01 Combustion efficiency : 98%

10 Ongoing Research Effect of inlet disturbances
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Ongoing Research Effect of inlet disturbances Combustion in recirculating flows Spray Combustion

11 Effect of Inlet Disturbance
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Effect of Inlet Disturbance Tunable inlet to create weak disturbance of varying frequency Bluff body stabilized flame Unsteady pressure and heat release measurement

12 Pressure Amplitude variation
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG.  = L = 20 cm Pressure oscillations increases with decreasing length Dominant frequency 27 Hz Acoustic frequency 827 Hz

13 Pressure and Heat Release
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Pressure and Heat Release Less damping with increasing length Causes the rise is pressure fluctuations

14 Low Frequency Variation with Inlet Length
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Low Frequency Variation with Inlet Length ,  =

15 PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG.
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Variation of Dominant Frequency with Inlet Velocity St = (60 deg cone) Dominant Frequency governed by vortex dynamics Feed back locking of flow instability and combustion process Phase relationship leads to enhancement of combustion oscillations

16 Ongoing Research Effect of inlet disturbances
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Ongoing Research Effect of inlet disturbances Combustion in recirculating flows Spray Combustion

17 Recirculating Flow Dynamics
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Recirculating Flow Dynamics Primary zone Fuel air mixing Intense combustion Short combustion length High turbulence Fuel rich combustion Understanding recirculating flow dynamics Time scales Pressure transients Energy cascading Combustion in recirculating flows Droplet Flow interaction

18 Image Processing IIT, Kanpur
PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Image Processing Filtered out image from the noises Grayscale image Intensity image Simulation results

19 Vortex Dynamics IIT, Kanpur
PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG.

20 Transient Analysis IIT, Kanpur
PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Transient Analysis Identification of signatures of re-circulation, turbulence and acoustics through frequency domain analysis of pressure transients Turbulence energy cascading due to re-circulation

21 Combustion in Recirculating Flow
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Combustion in Recirculating Flow Time scale reduces, complete combustion, Good pattern factor

22 Ongoing Research Effect of inlet disturbances
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Ongoing Research Effect of inlet disturbances Combustion in recirculating flows Spray Combustion Needs and Challenges Controlled atomization Emissions in spray combustion

23 Spray Combustion: Issues
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Spray Combustion: Issues Non-symmetrical spray flames and hot streaks Serious damage to combustor liner Combustor exit temperature (pattern factor) Flame location, shape and pattern Emission Levels

24 Need for controlled atomization
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Need for controlled atomization Big Drops => Longer Evaporation Time => Incomplete Combustion => Unburned Hydrocarbons & Soot, Reduced Efficiency Small Drops => Faster Evaporation and Mixing => Elongated Combustion Zone => More NOx Uniform size distribution for favorable pattern factor Reduced thermal loading on liner and turbine Reduced feedline coupling

25 Ongoing Research Effect of inlet disturbances
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Ongoing Research Effect of inlet disturbances Combustion in recirculating flows Spray Combustion Needs and Challenges Controlled atomization Emissions in spray combustion

26 Internally Mixed Swirl Atomizer
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Internally Mixed Swirl Atomizer Good atomization with small pressure drop Both hollow-cone and solid cone spray from same atomizer (wide range of applications) Possible to atomize very viscous liquid Self cleaning Finer atomization at low flow rates Less sensitive to manufacturing defects The liquid flow rate and atomization quality can be controlled Atomization of engine oil

27 IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Performance

28 Multi-head internally mixed atomizer
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Multi-head internally mixed atomizer Build to provide a throughput rate in excess to 0.5 LPM with a droplet size in the range of mm Flow rate independent of pressure difference Reduced feedline coupling

29 Ongoing Research Effect of inlet disturbances
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Ongoing Research Effect of inlet disturbances Combustion in recirculating flows Spray Combustion Needs and Challenges Controlled atomization Emissions in spray combustion

30 Emissions in spray flames
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Emissions in spray flames Measured values quite less compared to the theoretical predictions Inherent fuel staging reduces the NOx Longer flame => less NOx

31 Conclusions Disturbances can lead to combustion oscillations
IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Conclusions Disturbances can lead to combustion oscillations Recirculating flow helps in reducing disturbances Controlled Atomization can be achieved through air-assisting Spray combustion reduces NOx emissions through fuel staging

32 Acknowledgements IIT, Kanpur
PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. Acknowledgements M. S. Rawat S. K. Gupta S. Pandey P. Berman J. Karnawat S. Karmakar N. P. Yadav S. Nigam R. Sailaja M. Madanmohan Dr. K. Ramamurthi LPSC (ISRO) CFEES (DRDO)

33 IIT, Kanpur PROPULSION LAB, DEPARTMENT OF AEROSPACE ENGG. THANK YOU

Download ppt "Gas Turbine Combustion and Power Generation"

Similar presentations

AEROSPACE PROPULSION AEROSPACE 410 ENGINE INTAKE AND NOZZLE SYSTEM

AEROSPACE PROPULSION AEROSPACE 410 ENGINE INTAKE AND NOZZLE SYSTEM
Aerospace Engineering Laboratory II

Aerospace Engineering Laboratory II
MAE 4261: AIR-BREATHING ENGINES

MAE 4261: AIR-BREATHING ENGINES
A novel IGCC system with steam injected H2/O2 cycle and CO2 recovery P M V Subbarao Professor Mechanical Engineering Department Low Quality Fuel but High.

A novel IGCC system with steam injected H2/O2 cycle and CO2 recovery P M V Subbarao Professor Mechanical Engineering Department Low Quality Fuel but High.
Indian Institute of Technology Bombay Why you should study a course on “Combustion” Introduction of the Combustion.

Indian Institute of Technology Bombay Why you should study a course on “Combustion” Introduction of the Combustion.
Turbojets.

Turbojets.
JET PROPULSION Part 1 The Compressor.

JET PROPULSION Part 1 The Compressor.
Jet Engine Design Idealized air-standard Brayton cycle

Jet Engine Design Idealized air-standard Brayton cycle
Department of Mechanical Engineering ME 322 – Mechanical Engineering Thermodynamics Lect 27b Jet Aircraft Propulsion.

Department of Mechanical Engineering ME 322 – Mechanical Engineering Thermodynamics Lect 27b Jet Aircraft Propulsion.
Jet Engine Design 1 23 4 5 6 diffuser compressor combustion chamber turbine nozzle 1 2 3 4 5 6 P=constant q out q in T s 1-2 Isentropic compression in.

Jet Engine Design diffuser compressor combustion chamber turbine nozzle P=constant q out q in T s 1-2 Isentropic compression in.
Introduction to Propulsion

Introduction to Propulsion
“Energy Efficiency Guide for Industry in Asia”

“Energy Efficiency Guide for Industry in Asia”
Analysis of In-Cylinder Process in Diesel Engines P M V Subbarao Professor Mechanical Engineering Department Sudden Creation of Young Flame & Gradual.

Analysis of In-Cylinder Process in Diesel Engines P M V Subbarao Professor Mechanical Engineering Department Sudden Creation of Young Flame & Gradual.
Gas turbine cycles for aircraft propulsion In shaft power cycles, power is in form of generated power. In air craft cycles, whole power is in the form.

Gas turbine cycles for aircraft propulsion In shaft power cycles, power is in form of generated power. In air craft cycles, whole power is in the form.
PACCON 2013 PREDICTION OF NITROGEN OXIDE GENERATED FROM GAS TURBINE ENGINE Global Chemical Sciences for Green Community NATCHANON CHAIPRASERT / AMORNCHAI.

PACCON 2013 PREDICTION OF NITROGEN OXIDE GENERATED FROM GAS TURBINE ENGINE Global Chemical Sciences for Green Community NATCHANON CHAIPRASERT / AMORNCHAI.
How do aircraft jet engines work?

How do aircraft jet engines work?
Combined_Cycle_Power_Plant Prepared by: Nimesh Gajjar.

Combined_Cycle_Power_Plant Prepared by: Nimesh Gajjar.
EGR 334 Thermodynamics Chapter 9: Sections 7-8

EGR 334 Thermodynamics Chapter 9: Sections 7-8
Combustion AND Emissions Performance of syngas fuels derived from palm shell and POLYETHYLENE (PE) WASTE VIA CATALYTIC STEAM GASIFICATION Chaouki Ghenai.

Combustion AND Emissions Performance of syngas fuels derived from palm shell and POLYETHYLENE (PE) WASTE VIA CATALYTIC STEAM GASIFICATION Chaouki Ghenai.
Gas Turbines By: Katie Steddenbenz.

Gas Turbines By: Katie Steddenbenz.

Similar presentations

Ads by Google