Download GTU (Gujarat Technological University) BE/BTech (Bachelor of Engineering / Bachelor of Technology) 2019 Winter 6th Sem New 2160102 Fundamentals Of Jet Propulsion Previous Question Paper
Seat No.: ________ Enrolment No.___________
GUJARAT TECHNOLOGICAL UNIVERSITY
BE - SEMESTER ? VI (New) EXAMINATION ? WINTER 2019
Subject Code: 2160102 Date: 06/12/2019
Subject Name: Fundamentals of Jet Propulsion
Time: 02:30 PM TO 05:00 PM Total Marks: 70
Instructions:
1. Attempt all questions.
2. Make suitable assumptions wherever necessary.
3. Figures to the right indicate full marks.
Q.1 (a) Classify jet engines. 03
(b) Define: thrust, propulsive efficiency, thermal efficiency, and
,specific impulse
04
(c) Explain the need of thrust augmentation and the methods of
thrust
augmentation in brief.
07
Q.2 (a) The exit velocity from a jet unit is 700 m/s for an air flow of 45
kg/s through the unit. The aircraft is flying at 300 km/h. calculate
the thrust developed, the thrust power and the propulsion
efficiency. Neglect mass of fuel.
03
(b) With neat sketches explain the effect of compressor pressure
ratio and temperature ratio on the performance of turbojet
engine.
04
(c) In a gas turbine engine the compressor is driven by high pressure
stage of a two stage turbine and compresses 5 kg of air per
second from 1 bar to 5 bar with an efficiency of 80%. High
pressure turbine stage has an efficiency of 89% and its inlet
temperature is 980K. the low pressure turbine stage is having
efficiency of 82% and both the turbines has different pressure
ratios. Exhaust from low pressure turbine is preheated in heat
exchanger having an effectiveness of 70%. Neglect the mass of
fuel and pressure losses. Estimate the intermediate pressures and
temperatures for the cycle. Also calculate the power output of
the cycle and overall efficiency. Ambient temperature and
pressure 288K and 1 bar.
07
OR
(c) In a turbojet engine with forward facing ram intake, the jet
velocity relative to the propelling nozzle at exit is twice the flight
velocity. Determine the rate of fuel consumption in kg/s, when
developing a thrust of 25000N under the following conditions.
Ambient pressure and temperature 0.7 bar and 274K,
compression pressure ratio 4:1, flight 810Km/h, turbine pressure
ratio 2.23, efficiency of compressor, turbine and nozzle are 85%,
90% and 95%,
07
Q.3 (a) Draw h-s diagram representing nozzle operation and diffuser
operation separately.
03
(b) Explain zones of combustion chamber. 04
(c) Derive Area Velocity relation for nozzles. 07
OR
Q.3 (a) What is the primary function of the inlet of an aircraft engine? 03
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Seat No.: ________ Enrolment No.___________
GUJARAT TECHNOLOGICAL UNIVERSITY
BE - SEMESTER ? VI (New) EXAMINATION ? WINTER 2019
Subject Code: 2160102 Date: 06/12/2019
Subject Name: Fundamentals of Jet Propulsion
Time: 02:30 PM TO 05:00 PM Total Marks: 70
Instructions:
1. Attempt all questions.
2. Make suitable assumptions wherever necessary.
3. Figures to the right indicate full marks.
Q.1 (a) Classify jet engines. 03
(b) Define: thrust, propulsive efficiency, thermal efficiency, and
,specific impulse
04
(c) Explain the need of thrust augmentation and the methods of
thrust
augmentation in brief.
07
Q.2 (a) The exit velocity from a jet unit is 700 m/s for an air flow of 45
kg/s through the unit. The aircraft is flying at 300 km/h. calculate
the thrust developed, the thrust power and the propulsion
efficiency. Neglect mass of fuel.
03
(b) With neat sketches explain the effect of compressor pressure
ratio and temperature ratio on the performance of turbojet
engine.
04
(c) In a gas turbine engine the compressor is driven by high pressure
stage of a two stage turbine and compresses 5 kg of air per
second from 1 bar to 5 bar with an efficiency of 80%. High
pressure turbine stage has an efficiency of 89% and its inlet
temperature is 980K. the low pressure turbine stage is having
efficiency of 82% and both the turbines has different pressure
ratios. Exhaust from low pressure turbine is preheated in heat
exchanger having an effectiveness of 70%. Neglect the mass of
fuel and pressure losses. Estimate the intermediate pressures and
temperatures for the cycle. Also calculate the power output of
the cycle and overall efficiency. Ambient temperature and
pressure 288K and 1 bar.
07
OR
(c) In a turbojet engine with forward facing ram intake, the jet
velocity relative to the propelling nozzle at exit is twice the flight
velocity. Determine the rate of fuel consumption in kg/s, when
developing a thrust of 25000N under the following conditions.
Ambient pressure and temperature 0.7 bar and 274K,
compression pressure ratio 4:1, flight 810Km/h, turbine pressure
ratio 2.23, efficiency of compressor, turbine and nozzle are 85%,
90% and 95%,
07
Q.3 (a) Draw h-s diagram representing nozzle operation and diffuser
operation separately.
03
(b) Explain zones of combustion chamber. 04
(c) Derive Area Velocity relation for nozzles. 07
OR
Q.3 (a) What is the primary function of the inlet of an aircraft engine? 03
2
(b) Explain inlets for ramjet engine diffuser operations. 04
(c) Write a note on factors affecting the performance of combustion
chamber.
07
Q.4 (a) Write in brief about rocket engines. 03
(b) Differentiate between turbojet, turboprop & turbofan engine
with diagram.
04
(c) Write a short note on effect of back pressure for flow through C-
D nozzle.
07
OR
Q.4 (a) Why jet engine with afterburner is used for military airplanes..? 03
(b) Discuss Supersonic Inlets. 04
(c) Differentiate between critical, subcritical and supercritical
operations of ramjet diffuser.
07
Q.5 (a) What is chocking ? 03
(b) Explain with sketch : Can Type combustion chamber with
advantages and disadvantages
04
(c) Write a short note on solid propellant rocket engines with neat
sketch.
07
OR
Q.5 (a) Explain pulse jet engine with neat sketch. 03
(b) What is effect of total pressure lose on combustion ? 04
(c) Write a short note on liquid propellant rocket engines with neat
sketch.
07
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This post was last modified on 20 February 2020