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Posted By: Sra1 Member Level: Gold 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
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Set No 3
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Time: 3 hours Max Marks: 80
Answer any FIVE Questions
All Questions carry equal marks
1. What do you understand by free vortex turbine stage design?
Derive the following relationship
Cw.r = constant [16]
2. The following data apply to a single stage turbine of free vortex design:
Inlet temperature T01 = 1050 K
Inlet pressure p01 = 3.8 bar
Pressure ratio (p01/p03) = 2.0
Outlet velocity C3 = 275 m/s
Blade speed at root radius = 300 m/s
Isentropic efficiency ?t = 0.88
Nozzle efflux angle a2 at root radius = 6109’
Blade inlet gas angle ß2 at the root radius = 40014’
The turbine is designed for zero reaction (^ =0) at root radius and the velocities at inlet and outlet (C1& C3) are both equal and axial.
If the tip/root radius ratio of the annulus at the exit from the nozzle blade is 1.5, determine the nozzle efflux angle and degree of reaction at the tip radius. Assuming a nozzle loss coefficient of 0.05, calculate the static pressure at inlet and outlet of the rotor blades at the root radius and thereby show that even at the root
there is some expansion in the rotor blade passage under these conditions. [16]
3. (a) What are the various problems coming across while designing a supersonic diffuser for a ramjet engine and how these problems can be reduced / eliminated?
(b) Write a note on ‘variable geometry ramjet engine’. [10+6]
4. A preliminary performance analysis is to be made of a two dimensional ramjet engine which is to be installed in the wing of a supersonic airplane. The engine is operating at supercritical Mach number M0 = 3.3 at 50000 ft altitude and the maximum total temperature due to combustion is 40000R. The ramjet engine is to be equipped with a diverging diffuser. Calculate
(a) M2,
(b) P2/P0,
(c) P6/P0,
(d) The gross thrust coefficient CFg,
(e) the weight ratio of air flow into the engine and
(f) the TSFC.
Assume that the Mach number M2 at the entrance to the constant area combustion chamber is 0.2, k=1.4=constant, the lower heating value of the fuel is 19300 Btu/lb, A1 = 10ft2 and the flow is frictionless and neglect the effect of the fuel flow on the thrust. [16]
5. (a) Derive the equation for thrust of a rocket motor.
(b) Differentiate between a rocket and a missile. [9+7]
6. Explain the following with respect to solid propellants:
(a) Fuels
(b) Formulations and Ingredients
(c) Toxicity
(d) Particle-size parameters. [4x4=16]
7. What are the various types of propellant tanks in case of liquid rocket motors? Explain the role, desirable characteristics, advantages and disadvantages of propellant tanks. [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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