Compressors, Gas Turbines and Jet Engines The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio) 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 r ɣ-1 1 - (1/r) ɣ-1/ɣ 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 r ɣ-1 1 - (1/r) ɣ-1/ɣ ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines It is not possible to use closed gas turbine cycle in aeronautical engines because It is inefficient None of these It is bulky It requires cooling water for its operation It is inefficient None of these It is bulky It requires cooling water for its operation ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The maximum propulsion efficiency of a turbojet is attained at around following speed 1700 km/hr 550 km/hr 1050 km/hr 2400 km/hr 1700 km/hr 550 km/hr 1050 km/hr 2400 km/hr ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In jet engines, paraffin is usually used as the fuel because of its Low freezing point High calorific value Ease of atomisation Both (A) and (C) above Low freezing point High calorific value Ease of atomisation Both (A) and (C) above ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Maximum temperature in a gas turbine is of the order of 2000°C 1000°C 700°C 1500°C 2000°C 1000°C 700°C 1500°C ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Intercooling in gas turbines Increases net output but decreases thermal efficiency Increases net output and thermal efficiency both Decreases net output and thermal efficiency both Decreases net output but increases thermal efficiency Increases net output but decreases thermal efficiency Increases net output and thermal efficiency both Decreases net output and thermal efficiency both Decreases net output but increases thermal efficiency ANSWER DOWNLOAD EXAMIANS APP
EXAMIANS