Hall Ticket No Question Paper Code: AAE007
INSTITUTE OF AERONAUTICAL ENGINEERING
(Autonomous)
B.Tech V Semester End Examinations (Regular) November, 2018
Regulation: IARE R16
AIRCRAFT PROPULSION
Time: 3 Hours Max Marks: 70
Answer ONE Question from each Unit
All Questions Carry Equal Marks
All parts of the question must be answered in one place only
UNIT I
1. Describe the working principle of gas turbine engine with the help of neat diagram
A closed cycle regenerative gas turbine is operating with air as the working medium. Assume the
following data: P1=1.4 bar, T1=310 Tmax =1050 Effectiveness of regenerator
is net output 3000 kW. Assuming the compression and expansion to be isentropic,
Calculate Thermal Efficiency and Mass flow rate of air.
2. Derive thrust equation for ideal turbojet engine.
Illustrate RAMJET engine and explain the operation principle along with its operating cycle.

UNIT II
3. What are the important factors that affect the combustion chamber design?
Briefly classify the combustion chambers of gas turbine engines with neat sketches.
4. What are different types of air intakes for subsonic airplanes powered by turbo jets? Illustrate
each of these categories with sketches and aerodynamic characteristics.
Write short notes on need for flame stabilization and various techniques adopted in combustion
chamber.
UNIT III
5. Write short notes on thrust vectoring and different techniques used to achieve thrust vectoring.

Explain in detail about variable aera nozzle and different techniques adopted to achieve it.[7M]
Page 1 of 2
6. Explain theory of flow through convergent divergent nozzle and factors effecting their performance.

Write short notes on operating conditions of convergent divergent nozzle with a neat sketch.[7M]
UNIT IV
7. Construct a centrifugal compressor and explain principle of operation with neat diagrams?
What are the advantages of the axial flow compressor over the centrifugal flow compressor?
8. What are different types of flow losses in the compressor? Explain in detail?
Define degree of reaction. Explain the conditions of dor 0.5, dor 1 and dor 0 and Justify
for dor= 0.5, blades are symmetrical.
UNIT V
9. Illustrate and explain the concept of integral ram rocket and its advantages.
Write a brief note on operating principle of axial flow turbine with a neat sketch.
10. What do u understand by blade and stage efficiency. Derive the expression for blade efficiency?

Write short notes on work done and pressure rise by axial flow turbine and derive the equations?