Discussion
Home ‣ Mechanical Engineering ‣ Compressors, Gas Dynamics and Gas Turbines Comments
- Question
The temperature of air at the beginning of the compression stroke is __________ the atmospheric temperature.
Options- A. equal to
- B. less than
- C. more than
- Correct Answer
- more than
- 1. Euler's equation can be used for
Options- A. radial flow compressors
- B. axial flow compressors
- C. pumps
- D. all of these Discuss
- 2. The compressor efficiency is defined as the ratio of volume of free air delivery per stroke to the swept volume of the piston.
Options- A. Correct
- B. Incorrect Discuss
- 3. In a compressed air system, the temperature of air discharged from the air motor is __________ than the initial compressor intake temperature.
Options- A. more
- B. less Discuss
- 4. A jet engine has
Options- A. no propeller
- B. propeller in front
- C. propeller at back
- D. propeller on the top Discuss
- 5. A gas turbine used in air-craft should have low weight and small frontal area.
Options- A. Correct
- B. Incorrect Discuss
- 6. The overall efficiency of the compressed air system is the
Options- A. ratio of shaft output of the air motor to the shaft input to the compressor
- B. ratio of shaft input to the compressor to the shaft output of air motor
- C. product of shaft output of air motor and shaft input to the compressor
- D. none of the above Discuss
- 7. In a centrifugal compressor, the ratio of the __________ to the blade velocity is called slip factor.
Options- A. inlet whirl velocity
- B. outlet whirl velocity
- C. inlet velocity of flow
- D. outlet velocity of flow Discuss
- 8. Free air is the air at atmospheric conditions at any specific location.
Options- A. True
- B. False Discuss
- 9. For maximum work, the reheating should be done to an intermediate pressure of (where p1 = Maximum pressure, and p2 = Minimum pressure)
Options- A.
- B.
- C.
- D. p1p2 Discuss
- 10. Which of the following statement is correct relating to rocket engines?
Options- A. The combustion chamber in a rocket engine is directly analogous to the reservoir of a super sonic wind tunnel
- B. The stagnation conditions exist at the combustion chamber
- C. The exit velocities of exhaust gases are much higher than those in jet engine
- D. all of the above Discuss
Compressors, Gas Dynamics and Gas Turbines problems
Search Results
Correct Answer: all of these
Correct Answer: Incorrect
Correct Answer: less
Correct Answer: no propeller
Correct Answer: Correct
Correct Answer: ratio of shaft output of the air motor to the shaft input to the compressor
Correct Answer: outlet velocity of flow
Correct Answer: True
Correct Answer: p1p2
Correct Answer: all of the above
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