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Homework answers / question archive / The turbine for a gas turbine engine is required to drive a compressor operating with the following conditions: Compressor conditions Pressure ratio, 7, = 11

The turbine for a gas turbine engine is required to drive a compressor operating with the following conditions: Compressor conditions Pressure ratio, 7, = 11

Chemistry

The turbine for a gas turbine engine is required to drive a compressor operating with
the following conditions:
Compressor conditions
Pressure ratio, 7, = 11.9
Inlet (ambient) temperature, Tampient = 290 K
Inlet (ambient) pressure, Pampient = 105 kPa
Inlet axial Mach number, M,, = 0.37
Maximum relative Mach number at the compressor tip inlet, M;,.; = 1.05
Compressor polytropic efficiency, e¢ = 90.5%
Compressor mass flow, mc: = 340 kg/s
Working fluid in compressor is ambient air:
Cp = 1.005 kJ/kgK; R = 0.287 kJ/kgkK; y = 1.4
The stagnation temperature at turbine entry is 1625 K, and there is a 5% stagnation
pressure loss across the combustion chamber. The axial Mach number at turbine inlet
is Mri, = 0.3 and the polytropic efficiency of the turbine is 91.7%. The HP system
has a mechanical efficiency of 98% and a work done factor of 2 = 0.98 is assumed for
the turbine. Working fluid is post combustion gas :
Cpg = 1.251 kJ/kgK; R = 0.287 kJ/kgK; y = 1.298
The calorific value (heating value) of the fuel is Qzg = 52,100 kJ/kg.
Using the above data, design a turbine, with the following limitations
* HP turbine inlet annulus height > 0.1 m.
* Absolute exit angle at mid-height for exit of final turbine
stage must be < 12°.
¢ Number of stages to be selected as appropriate.
* Constant mean radius design
* Constant axial velocity through the stage
For the design, the following parameters should be determined for each turbine stage
(note — the design process will require appropriate choice of some parameters at key
parts of the design process, and choices should be justified clearly).
* Hub-tip radius ratio at stage inlet and exit
¢ Inlet and exit area
¢ Hub and tip radius at inlet and exit
¢ Mean-height blade speed
* Stage loading
* Flow coefficient
* Mid-height Reaction
* Absolute and relative blade angles and velocities.

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