A gas turbine having single stage rotates at 10000 tpm. At entry to the nozzles the total head to the temperature and pressure of the gas i8 700°C and 4.5 bar respectively and at outlet, from the nozle the static pressurc is 2.6 bar. At the turbine outlet annulus the static pressure is 1.5 bar. Mach number at outlet is limited to 0.5 and gas leaves in an axial direction. The outlet nozzle angle is 70° to the axial direction and the nozzle friction loss may be assurfied to be 3% of the isentropic temperature drop from total head at entry to static conditions at outlet nozzle pressure. Calculate (i) the gas angles at entry and outlet from the wheel showing them on velocity diagrams for mean blade section, (ii) output power developed by the turbine shaft. Assume the mean blades diameter as 64 cm, gas mass flow rate as 22.5 kg/s, turbine mechanical efficiency = 99%, C; = 1147 kJ /ke K and v = 1.33. A gas turbine having single stage rotates at 10000 rpm. At entryto the nozzles the total head temperature and pressure of the gasis 700°C and 4.5 bar respectively and at outlet from the nozzle thestatic pressure is 2.6 bar. At the turbine outlet annulus the staticpressure is 1.5 bar. Mach number at outlet is limited to 0.5 and gasleaves in an axial direction. The outlet nozzle angle is 70° to theaxial direction and the nozzle friction loss may be assumed to be 3%of the isentropic temperature drop from total head at entry to staticconditions at outlet nozzle pressure. Calculate(i) the gas angles at entry and outlet from the wheel showing themon velocity diagrams for mean blade section,(ii) output power developed by the turbine shaft.Assume the mean blades diameter as 64 cm, gas mass flow rate as22.5 kg/s, turbine mechanical efficiency = 99%, C, = 1.147 kJ/kg Kand y = 1.33.%3D

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Answered: A gas turbine having single stage…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

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A gas turbine having single stage rotates at 10000 tpm. At entry to the nozzles the total head to the temperature and pressure of the gas i8 700°C and 4.5 bar respectively and at outlet, from the nozle the static pressurc is 2.6 bar. At the turbine outlet annulus the static pressure is 1.5 bar. Mach number at outlet is limited to 0.5 and gas leaves in an axial direction. The outlet nozzle angle is 70° to the axial direction and the nozzle friction loss may be assurfied to be 3% of the isentropic temperature drop from total head at entry to static conditions at outlet nozzle pressure. Calculate (i) the gas angles at entry and outlet from the wheel showing them on velocity diagrams for mean blade section, (ii) output power developed by the turbine shaft. Assume the mean blades diameter as 64 cm, gas mass flow rate as 22.5 kg/s, turbine mechanical efficiency = 99%, C; = 1147 kJ /ke K and v = 1.33.

A gas turbine having single stage rotates at 10000 rpm. At entry
to the nozzles the total head temperature and pressure of the gas
is 700°C and 4.5 bar respectively and at outlet from the nozzle the
static pressure is 2.6 bar. At the turbine outlet annulus the static
pressure is 1.5 bar. Mach number at outlet is limited to 0.5 and gas
leaves in an axial direction. The outlet nozzle angle is 70° to the
axial direction and the nozzle friction loss may be assumed to be 3%
of the isentropic temperature drop from total head at entry to static
conditions at outlet nozzle pressure. Calculate
(i) the gas angles at entry and outlet from the wheel showing them
on velocity diagrams for mean blade section,
(ii) output power developed by the turbine shaft.
Assume the mean blades diameter as 64 cm, gas mass flow rate as
22.5 kg/s, turbine mechanical efficiency = 99%, C, = 1.147 kJ/kg K
and y = 1.33.
%3D

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