The compressor of a jet engine tested at sea level on a stationary test bed on a day when the atmospheric temperature and pressure is 298 K and 101kPa, respectively. When running at its design operating point, the masss flow rate through the compressor is measured as 15 kg/s and the rational speed is 6200 rpm. Determine the mass flow rate and the rational speed when the compressor is operating at the design operating point during high altitude cruise with an onlet stagnation temperature of 236 K and an inlet stagnation pressure of 10.2 kpa. The design pressure ratio of compressor is 20. If the compressor isentropic efficiency is determined from the test to be 85=, calculate the power input at the cruise condition. Assume for air that y=1. 4 and Cp=1005 kJ/kg-K throughout.
The compressor of a jet engine tested at sea level on a stationary test bed on a day when the atmospheric temperature and pressure is 298 K and 101kPa, respectively. When running at its design operating point, the masss flow rate through the compressor is measured as 15 kg/s and the rational speed is 6200 rpm. Determine the mass flow rate and the rational speed when the compressor is operating at the design operating point during high altitude cruise with an onlet stagnation temperature of 236 K and an inlet stagnation pressure of 10.2 kpa. The design pressure ratio of compressor is 20. If the compressor isentropic efficiency is determined from the test to be 85=, calculate the power input at the cruise condition. Assume for air that y=1. 4 and Cp=1005 kJ/kg-K throughout.
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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The compressor of a jet engine tested at sea level on a stationary test bed on a day when the atmospheric temperature and pressure is 298 K and 101kPa, respectively. When running at its design operating point, the masss flow rate through the compressor is measured as 15 kg/s and the rational speed is 6200 rpm. Determine the mass flow rate and the rational speed when the compressor is operating at the design operating point during high altitude cruise with an onlet stagnation temperature of 236 K and an inlet stagnation pressure of 10.2 kpa. The design pressure ratio of compressor is 20. If the compressor isentropic efficiency is determined from the test to be 85=, calculate the power input at the cruise condition. Assume for air that y=1. 4 and Cp=1005 kJ/kg-K throughout.
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