Compressors, Gas Turbines and Jet Engines A closed gas turbine in which fuel is burnt directly in the air is not possible because of High friction losses Paucity of O2 Increasing gas temperature High specific volume High friction losses Paucity of O2 Increasing gas temperature High specific volume ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For an irreversible gas turbine cycle, the efficiency and work ratio both depend on Minimum cycle temperature alone Maximum cycle temperature alone Both pressure ratio and maximum cycle temperature Pressure ratio alone Minimum cycle temperature alone Maximum cycle temperature alone Both pressure ratio and maximum cycle temperature Pressure ratio alone ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For slow speed large capacity compressor, following type of valve will be best suited Disc or feather type Mechanical valve of the Corliss, sleeve, rotary or semi rotary type Poppet valve Any of the above Disc or feather type Mechanical valve of the Corliss, sleeve, rotary or semi rotary type Poppet valve Any of the above ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Clearance volume in actual reciprocating compressors is essential To provide cushioning effect and also to avoid mechanical bang of piston with cylinder head To attain high volumetric efficiency To provide cushioning effect To accommodate Valves in the cylinder head To provide cushioning effect and also to avoid mechanical bang of piston with cylinder head To attain high volumetric efficiency To provide cushioning effect To accommodate Valves in the cylinder head ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For a two stage reciprocating compressor, compression from p₁ to p₃ is with perfect intercooling and no pressure losses. If compression in both the cylinders follows the same polytropic process and the atmospheric pressure is pa, then the intermediate pressure p₂ is given by p₂ = p₁. p₃ p₂ = (p₁ + p₃)/2 p₂ = Pa p₃/p₁ P₂ = Pa × p₃/p₁ p₂ = p₁. p₃ p₂ = (p₁ + p₃)/2 p₂ = Pa p₃/p₁ P₂ = Pa × p₃/p₁ ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio) 1 - (1/r) ɣ-1/ɣ 1 - (1/r) ɣ/ɣ-1 r ɣ-1 1 - r ɣ-1 1 - (1/r) ɣ-1/ɣ 1 - (1/r) ɣ/ɣ-1 r ɣ-1 1 - r ɣ-1 ANSWER DOWNLOAD EXAMIANS APP
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