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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