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Posted By: Sra1 Member Level: Diamond Posted Date: 27 May 2008
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2007 Jawaharlal Nehru Technological University B.Tech Aeronautical AEROSPACE PROPULSION-II (Supplimentary Examinations, Aug/Sep 2007) Question paper
Set No 1
------------------
Time: 3 hours Max Marks: 80
Answer any FIVE Questions
All Questions carry equal marks
1. Explain the vortex theory with respect to constant nozzle angle design and derive
the following relationship
CW2.r(sin 2)(sin 2) = constant [16]
2. The following particulars relate to a single-stage turbine of free vortex design:
Inlet stagnation temperature = 10000K
Inlet stagnation pressure = 3.8 kgf/cm2
Static head efficiency = 0.88
Nozzle efficiency = 0.96
Outlet static pressure = 1.2 kgf/cm2
Outlet velocity = 280 m/s
Blade speed at root = 277 m/s
If there is outlet swirl and the turbine is designed for impulse conditions at the root
radius, find the work output?
Also find the nozzle angle and degree of reaction at the tip radius if the radius ratio at the turbine annulus at exit from nozzle is 1.4. Neglecting disc friction and tip leakage loss, find nozzle angle and blade angle at root. Assume Cp = 0.276 and ? = 1.333. [16]
3. (a) Define ‘effective jet Mach number’ for a ramjet engine and derive the relationship for it.
(b) Write a short note on ‘external drag’ of a ramjet engine. [8+8]
4. Explain the preliminary concepts in supersonic combustion. [16]
5. A rocket projectile has the following characteristics:
Initial weight = 200 lb
Weight after rocket operation = 130 lb
Payload, non-propulsive structure etc. = 110 lb
Rocket operating duration = 3 sec
Average specific impulse of propellant = 240 sec
Determine mass ratio, propellant mass fraction, propellant flow rate, thrust, specific propellant consumption, acceleration of vehicle, effective exhaust velocity, total impulse, specific power and impulse to weight ratio. [16]
6. (a) Explain the salient features of a solid rocket motor with the help of a suitable diagram.
(b) Explain the following with respect to solid propellant rocket motor:
i. Relationship between burning rate and chamber pressure
ii. Relationship between burning rate and temperature. [8+4+4]
7. Explain the salient features of a liquid propellant rocket motor with turbo-pump feed system with the help of a schematic diagram. Write down its advantages and disadvantages. [16]
8. (a) Differentiate between chemical and nuclear rockets.
(b) Write a note on ‘meta-stable propellant ingredients’ with respect to chemical rockets. [8+8]
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