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Thermodynamic Investigation of Transpiration Cooled Gas Turbine Blade

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Ergonomics for Improved Productivity (HWWE 2021)

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Abstract

Presently, gas turbines utilize sophisticated cooling techniques, such as impingement cooling, convection cooling and film cooling, to get better engine durability and enhanced cycle performance. In this paper, study is undertaken to investigate the impact of transpiration cooling of gas turbine blade on the performance of a simple gas turbine cycle. Study also evaluates the effect of the cycle pressure ratio and turbine inlet temperature on coolant requirement of three different blade cooling methods, namely convection cooling, film cooling and transpiration cooling.

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Abbreviations

f :

Fuel air ratio

h :

Enthalpy (kJ/kg)

v :

Specific volume (m3/kg)

w :

Work done (kJ/kg)

A :

Area (m2)

P :

Pressure (N/m2)

T :

Temperature (K)

\(\dot{m}\) :

Mass flow rate (kg/s)

c p :

Specific heat at constant pressure (kJ/kg K)

St:

Stanton number

λ :

Ratio of cooled blade surface area to hot gas flow area (Ab/Ag)

ε :

Cooling effectiveness

η :

Efficiency

a:

Air

b:

Blade

e:

Exit

g:

Gas

f:

Fuel

i:

Inlet

com:

Compressor

cl:

Coolant

gt:

Gas turbine

cc:

Combustion chamber

aw:

Adiabatic

pt:

Polytropic

GT:

Gas turbine

CPR:

Cycle pressure ratio

HRSG:

Heat recovery steam generator

TIT:

Turbine inlet temperature

LCV:

Lower calorific value

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Shukla, A.K., Sharma, M., Singh, O. (2022). Thermodynamic Investigation of Transpiration Cooled Gas Turbine Blade. In: Muzammil, M., Khan, A.A., Hasan, F. (eds) Ergonomics for Improved Productivity. HWWE 2021. Design Science and Innovation. Springer, Singapore. https://doi.org/10.1007/978-981-16-2229-8_6

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  • DOI: https://doi.org/10.1007/978-981-16-2229-8_6

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  • Publisher Name: Springer, Singapore

  • Print ISBN: 978-981-16-2228-1

  • Online ISBN: 978-981-16-2229-8

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