It is not possible to use closed gas turbine cycle in aeronautical engines because_________________ ?
A. it is inefficient
B. it is bulky
C. it requires cooling water for its operation
D. non of theses
A. it is inefficient
B. it is bulky
C. it requires cooling water for its operation
D. non of theses
A. compressor pressure ratio
B. highest pressure to exhaust pressure
C. inlet pressure to exhaust pressure
D. pressures across the turbine
E. none of the above
[B].
Answer: Option A
Explanation:
No answer description available for this question.
A. using mulit-stage compressor with mfercooler
B. adding heat exchanger
C. injecting water in/around combustion chamber
D. reheating the air after partial expansion in the turbine
E. all of the above
A. equal to zero
B. in the direction of motion of blades
C. opposite to the direction of motion of blades
D. depending on the velocity
E. none of the above
A. h.p. compressor L connected to h.p. turbine and l.p. compressor ot l.p. tur-bine
B. h.p. compressor is connected to l.p. turbine and l.p. compressor is con-nected to h.p. turbine
C. both the arrangements can be employed
D. all are connected in series
E. none of the above
A. 3 m3/mt
B. 1.5 m3/mt
C. 18 m3/mt
D. 6 m3/mt
E. 0.75 m3/mt