A single stage gas turbine operates at its design condition with an axial absolute flow entry and exit from the stage. The absolute flow angle at nozzle exit is 70 degree. At stage entry the total pressure and temperature are 311 kPa and 850 oC respectively. The exhaust static pressure is 100 kPa, the total to static efficiency is 0.87 and the mean blade speed is 500 m/s. Assuming the constant axial velocity through the stage, determine the specific work done; the Mach number leaving the nozzle; the axial velocity; the total to total efficiency; the stage reaction. Take C, = 1.148 k]/(kg°C) and y = 1.33 for the gas.
A single stage gas turbine operates at its design condition with an axial absolute flow entry and exit from the stage. The absolute flow angle at nozzle exit is 70 degree. At stage entry the total pressure and temperature are 311 kPa and 850 oC respectively. The exhaust static pressure is 100 kPa, the total to static efficiency is 0.87 and the mean blade speed is 500 m/s. Assuming the constant axial velocity through the stage, determine the specific work done; the Mach number leaving the nozzle; the axial velocity; the total to total efficiency; the stage reaction. Take C, = 1.148 k]/(kg°C) and y = 1.33 for the gas.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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![A single stage gas turbine operates at its design condition with an axial absolute flow entry and
exit from the stage. The absolute flow angle at nozzle exit is 70 degree. At stage entry the total
pressure and temperature are 311 kPa and 850 oC respectively. The exhaust static pressure is 100
kPa, the total to static efficiency is 0.87 and the mean blade speed is 500 m/s. Assuming the
constant axial velocity through the stage, determine
the specific work done;
the Mach number leaving the nozzle;
the axial velocity;
the total to total efficiency;
the stage reaction.
Take Cp = 1.148 k]/(kg°C) and y = 1.33 for the gas.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fd215f58d-3820-491d-9813-299c2de86889%2Fe0325204-e310-4cc3-8035-101481350319%2Fnmc4k37_processed.jpeg&w=3840&q=75)
Transcribed Image Text:A single stage gas turbine operates at its design condition with an axial absolute flow entry and
exit from the stage. The absolute flow angle at nozzle exit is 70 degree. At stage entry the total
pressure and temperature are 311 kPa and 850 oC respectively. The exhaust static pressure is 100
kPa, the total to static efficiency is 0.87 and the mean blade speed is 500 m/s. Assuming the
constant axial velocity through the stage, determine
the specific work done;
the Mach number leaving the nozzle;
the axial velocity;
the total to total efficiency;
the stage reaction.
Take Cp = 1.148 k]/(kg°C) and y = 1.33 for the gas.
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