GATE_AE_2027_MOCK_04_Q57
GATE 2027 Aerospace Engineering All-India Master Mock 04 (Aerospace Structures, Thin-Walled Beams & Aeroelasticity)
MCQ · 2 Marks
Propulsion • Inlets, Combustors & Nozzles • Combustion Chambers & Total Pressure Loss
Total pressure loss in an aircraft gas turbine combustor consists primarily of:
(A) Fundamental Rayleigh pressure loss due to heat addition and cold friction pressure loss across liner passages
(B) Shock wave total pressure losses only
(C) Loss of total energy to nuclear radiation
(D) Electromagnetic dissipation
Answer Key:
A
Step-by-Step Verified Solution
### Solution: Combustor total pressure drop \Delta P_0 / P_0 comprises two parts: thermal/Rayleigh pressure loss due to heat release and viscous friction loss across swirlers and liner cooling holes. Correct: A.