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Posted By: Nitin Bajaj - Editor Member Level: Diamond Posted Date: 24 Mar 2008
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2007 Jawaharlal Nehru Technological University B.Tech AEROSPACE PROPULSION-II - Set 2 Question paper
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III B.Tech II Semester Supplimentary Examinations, Aug/Sep 2007 AEROSPACE PROPULSION-II (Aeronautical Engineering) Time: 3 hours Max Marks: 80 Answer any FIVE Questions All Questions carry equal marks
1. Write notes on the following with respect to axial turbine stage (a) Degree of Reaction (b) Blade losses [8+8]
2. Products of combustion ?ow through an axial turbine stage with the following properties: Tt1 = 32000 R, Pt1 = 200 psia, u3 /u3 = 1, M2 = 1.05, U =? rm = 1200 ft/sec, a2 = 400 and a3 = 250 . For the gas, use ?= 1.3 and R = 53.4 ft.lbf/lbm.0 R. Determine the following: (a) V2 , u2 and v2 (b) V3 ,u3 and v3 (c) ?Tt and t s for the stage (d) ?s and Pt3 for a polytropic e?ciency of 0.9 [16]
3. De?ne and derive the relationship for gross thrust coe?cient of a ramjet engine. Explain the behavioural characteristics of gross thrust coe?cient with the related parameters with the help of plots for a ?xed geometry ramjet engine. [16]
4. What are the various components of a SCRAMJET? Explain their function with the help of suitable diagrams. [16]
5. (a) Explain the following with respect to rocket motor: i. Impulse weight ratio ii. Total impulse. (b) An ideal rocket chamber is to operate at sea level using propellant whose combustion products have a speci?c heat ratio of 1.30. Determine the required chamber pressure and nozzle area ratio between throat and exit if the nozzle exit Mach number is 2.4. The nozzle inlet Mach number may be considered to be unity. [5+5+6]
6. Write notes on the following with respect to solid rocket motor: (a) Rocket motor case (b) Igniters.
7. (a) Explain the following with respect to liquid propellants: (b) Write a note on ‘control of combustion instability’ with respect to liquid rocket motors. [5+5+6]
8. Describe the concept of solid-core reactor rocket with the help of a schematic diagram. [16]
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