The Gas turbine combustion chamber is the highest thermally loaded component where the temperature of the combustion gases is higher than the melting point of the liner that confines the gases. Combustor liner temperatures have to be evaluated at all the operating conditions in the operating envelope to ensure a satisfactory liner life and structural integrity. On experimental side the combustion chamber rig testing involves a lot of time and is very expensive, while the numerical computations and simulations has to be validated with the experimental results. This paper is mainly based on the work carried out in validating the liner temperatures of a straight flow annular combustion chamber for an aero engine application. Limited experiments have been carried out by measuring the liner wall temperatures using k-type thermocouples along the liner axial length. The experiments on the combustion chamber testing are carried out at the engine level testing. The liner temperature which is numerically computed by CHT investigations using CFX code is verified with the experimental data. This helped in better understanding the flow characterization around and along the liner wall. The main flow variables used are the mass flow rate, temperature and the pressure at the combustor inlet. Initially, the fuel air ratio is used accordingly to maintain the same T4/T3 ratio. The effect of liner temperature with T3 is studied. Since T4 is constant, the liner temperature is only dependent on T3 and follows a specific temperature distribution for the given combustor geometry. Hence this approach will be very useful in estimating the liner temperatures at any given T3 for a given combustor geometry. Further the liner temperature is also estimated at other fuel air ratios (different T4/T3 ratios) by using the verified CHT numerical computations and found that TL/T3 remains almost constant for any air fuel ratio that is encountered in the operating envelope of the aero engine.
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ASME 2017 Gas Turbine India Conference
December 7–8, 2017
Bangalore, India
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5850-9
PROCEEDINGS PAPER
Numerical and Experimental Investigations on Liner Heat Transfer in an Aero Engine Combustion Chamber
Korukonda Venkata Lakshmi Narayana Rao,
Korukonda Venkata Lakshmi Narayana Rao
Hindustan Aeronautics Ltd., Bangalore, India
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B. V. S. S. S. Prasad,
B. V. S. S. S. Prasad
IIT Madras, Chennai, India
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Ch. Kanna Babu,
Ch. Kanna Babu
Hindustan Aeronautics Ltd., Bangalore, India
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Girish K. Degaonkar
Girish K. Degaonkar
Hindustan Aeronautics Ltd., Bangalore, India
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Korukonda Venkata Lakshmi Narayana Rao
Hindustan Aeronautics Ltd., Bangalore, India
B. V. S. S. S. Prasad
IIT Madras, Chennai, India
Ch. Kanna Babu
Hindustan Aeronautics Ltd., Bangalore, India
Girish K. Degaonkar
Hindustan Aeronautics Ltd., Bangalore, India
Paper No:
GTINDIA2017-4776, V001T03A014; 7 pages
Published Online:
February 2, 2018
Citation
Narayana Rao, KVL, Prasad, BVSSS, Kanna Babu, C, & K. Degaonkar, G. "Numerical and Experimental Investigations on Liner Heat Transfer in an Aero Engine Combustion Chamber." Proceedings of the ASME 2017 Gas Turbine India Conference. Volume 1: Compressors, Fans and Pumps; Turbines; Heat Transfer; Combustion, Fuels and Emissions. Bangalore, India. December 7–8, 2017. V001T03A014. ASME. https://doi.org/10.1115/GTINDIA2017-4776
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