Curioustab
Aptitude
General Knowledge
Verbal Reasoning
Computer Science
Interview
Aptitude
General Knowledge
Verbal Reasoning
Computer Science
Interview
Home
»
Mechanical Engineering
»
Compressors, Gas Dynamics and Gas Turbines
Which of the following statement is correct relating to rocket engines?
The combustion chamber in a rocket engine is directly analogous to the reservoir of a super sonic wind tunnel
The stagnation conditions exist at the combustion chamber
The exit velocities of exhaust gases are much higher than those in jet engine
all of the above
Correct Answer:
all of the above
← Previous Question
Next Question→
More Questions from
Compressors, Gas Dynamics and Gas Turbines
In a single stage, single acting reciprocating air compressor, without clearance, the workdone on the air during isentropic compression is __________ the heat required to raise the temperature of air from T1 to T2 at a constant pressure.
The pressure of air at the beginning of the compression stroke is __________ the atmospheric pressure.
The process, which causes the air to enter the impeller blades of a centrifugal compressor at __________ velocity (without effecting the mass of air to flow and velocity of flow) is known as prewhirl.
The axial flow compressor is preferred in air-craft gas turbines because of
Which of the following statement is correct as regard to centrifugal compressors?
The mass of gas turbine per kW developed is about __________ as that of an I.C. engine.
In a turbo jet engine, subsequent to heat addition to compressed air, to get the power output, the working substance is expanded in
The performance of air compressor at high altitudes will be __________ as compared to that at sea level.
The intercooler pressure, for minimum work required, for a two stage reciprocating air compressor, is given by (where p1 = Intake pressure of air, p2 = Intercooler pressure, and p3 = Delivery pressure of air)
In a centrifugal compressor, the air enters the impeller axially and leaves the vane radially.
Discussion & Comments
No comments yet. Be the first to comment!
Name:
Comment:
Post Comment
Join Discussion
Discussion & Comments