Compressors, Gas Dynamics and Gas Turbines MCQ Questions with Answers

⚙️ Compressors, Gas Dynamics & Gas Turbines MCQs with Live Score

Practice 100+ important MCQs from compressors, gas dynamics, and gas turbines with answers and detailed explanations

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Compressors, Gas Dynamics and Gas Turbines MCQ Questions (1–100)

These MCQ questions cover key concepts of compressors, gas dynamics, and gas turbines including compressible flow, Mach number, shock waves, nozzles, Brayton cycle, and turbine performance. These questions are highly important for GATE, IES, SSC JE, RRB, and other mechanical engineering exams.

Question 1: In a single-stage reciprocating compressor, why does the volumetric efficiency decrease with increase in pressure ratio even when clearance volume remains constant?

Question 2: For isentropic flow of a perfect gas through a convergent nozzle, the maximum mass flow rate occurs when:

Question 3: In multistage compression with perfect intercooling, the work done is minimized when:

Question 4: In compressible flow through a convergent-divergent nozzle, under what condition does the flow become supersonic in the divergent section?

Question 5: In a gas turbine operating on Brayton cycle with regeneration, the thermal efficiency improves because:

Question 6: In a normal shock wave, the Mach number downstream of the shock is always:

Question 7: In compressors, isothermal efficiency is always higher than adiabatic efficiency because:

Question 8: In Fanno flow, the flow is characterized by:

Question 9: In gas turbines, work ratio is defined as:

Question 10: In compressible flow, stagnation temperature remains constant in:

Question 11: In a convergent-divergent nozzle, supersonic flow is achieved in:

Question 12: In compressors, clearance volume affects:

Question 13: In Rayleigh flow, maximum entropy occurs at:

Question 14: In Brayton cycle, increasing pressure ratio beyond optimum leads to:

Question 15: In a compressor, intercooling reduces work input because:

Question 16: In compressible flow, choking occurs when:

Question 17: In gas turbines, regeneration is most effective when:

Question 18: In oblique shock, flow deflection leads to:

Question 19: In compressors, polytropic efficiency is preferred because:

Question 20: In gas dynamics, sonic velocity depends on:

Question 21: In gas turbines, reheating increases:

Question 22: In Fanno flow, choking occurs due to:

Question 23: In compressors, isentropic efficiency is defined as:

Question 24: In gas turbines, back work ratio increases with:

Question 25: In compressible flow, stagnation pressure decreases across:

Question 26: In compressors, volumetric efficiency is improved by:

Question 27: In gas turbines, intercooling leads to:

Question 28: In gas dynamics, critical pressure ratio corresponds to:

Question 29: In compressors, mechanical efficiency accounts for:

Question 30: In Brayton cycle, thermal efficiency depends mainly on:

Question 31: In a multistage reciprocating compressor with perfect intercooling, why does the total work approach isothermal compression work?

Question 32: In compressible flow through a constant area duct with friction (Fanno flow), what happens to Mach number when the flow is initially subsonic?

Question 33: In a normal shock wave, why is there an increase in entropy across the shock?

Question 34: In a Brayton cycle with regeneration, why does increasing pressure ratio beyond a certain limit reduce effectiveness?

Question 35: In gas dynamics, why is stagnation pressure not conserved across a shock wave?

Question 36: In a centrifugal compressor, slip factor accounts for:

Question 37: In Rayleigh flow, what is the effect of heat addition on subsonic flow?

Question 38: In axial flow compressors, why are multiple stages required?

Question 39: In gas turbines, why does intercooling alone not improve efficiency?

Question 40: In compressible flow, why does area decrease accelerate subsonic flow but decelerate supersonic flow?

Question 41: In gas turbines, why is turbine inlet temperature limited?

Question 42: In normal shock relations, why does static pressure increase?

Question 43: Why is polytropic efficiency preferred?

Question 44: In Fanno flow, why does entropy increase?

Question 45: Why is regeneration ineffective at high pressure ratio?

Question 46: In a CD nozzle, high back pressure causes:

Question 47: Why does clearance volume reduce efficiency?

Question 48: Why does Rayleigh flow choke?

Question 49: Why reheating reduces efficiency?

Question 50: Why Mach number is important?

Question 51: In axial compressors, blade angle variation along radius is necessary to:

Question 52: In shock waves, why is total temperature constant despite pressure rise?

Question 53: In compressors, why is multistaging preferred?

Question 54: In gas turbines, why is back work ratio important?

Question 55: In compressible flow, why is density variation important?

Question 56: In Fanno flow, what happens to temperature in subsonic flow?

Question 57: In gas turbines, why are multiple shafts used?

Question 58: In compressible flow, why does temperature decrease in supersonic expansion?

Question 59: In compressors, why is cooling important?

Question 60: In gas dynamics, why are shock waves irreversible?

Question 61: Over-expanded nozzle leads to:

Question 62: In axial compressors, efficiency drops at high flow rates due to:

Question 63: In Fanno flow (supersonic), friction causes Mach number to:

Question 64: In Brayton cycle with intercooling & reheating, drawback is:

Question 65: Across normal shock, which decreases?

Question 66: Why polytropic compression is realistic?

Question 67: In Rayleigh flow, at which condition does the entropy of the flow reach its maximum value?

Question 68: Blade cooling is required because:

Question 69: Critical area is defined where:

Question 70: Temperature rise increases compressor work because:

Question 71: For supersonic flow, increasing area causes:

Question 72: Surge in compressor is:

Question 73: Shock causes velocity to:

Question 74: Regeneration best works at:

Question 75: Fanno flow max length limited by:

Question 76: Work ratio indicates:

Question 77: Stagnation temperature constant when:

Question 78: Intercooling drawback is:

Question 79: In Rayleigh flow (supersonic), heat addition causes:

Question 80: Regeneration + intercooling used to:

Question 81: Choking limits mass flow because:

Question 82: Blade stall causes:

Question 83: Mach number across shock:

Question 84: Higher TIT improves efficiency because:

Question 85: In Fanno flow (subsonic), pressure:

Question 86: Reheating is used to:

Question 87: Speed of sound defines:

Question 88: Volumetric efficiency defines:

Question 89: Rayleigh max heat at:

Question 90: Gas turbine efficiency lower due to:

Question 91: Stagnation pressure drops due to:

Question 92: Pressure rise per stage limited due to:

Question 93: Temperature across shock:

Question 94: Optimum pressure ratio ensures:

Question 95: Friction causes entropy:

Question 96: Intercooling + reheating gives:

Question 97: Mach number important because:

Question 98: High speed reduces efficiency due to:

Question 99: Shock unavoidable because:

Question 100: Combined cycle efficiency high because:

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Compressors, Gas Dynamics and Gas Turbines MCQ Questions with Answers

⚙️ Compressors, Gas Dynamics & Gas Turbines MCQs with Live Score

Compressors, Gas Dynamics and Gas Turbines MCQ Questions (1–100)

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