It is not possible to use closed gas turbine cycle in aeronautical engines because_________________ ?

Related Mcqs:

The overall isothermal eiffciency of compressor is defined as the ratio of_______________?

A. isothermal h.p. to the BHP of motor B. isothermal h.p. to adiabatic h.p. C. power to drive compressor to isothermal h.p. D. work to compress air isothermally to work for actual compression E. isothermal work to ideal work...

Ratio of indicated H.P. and brake H.P. is known as_________________?

A. mechanical efficiency B. volumetric efficiency C. isothermal efficiency D. adiabatic efficiency E. relative efficiency...

The volumetirc efficiency of a compressor is calculated on the basis of __________________?

A. volume of air inhaled at working conditions B. volume of air inhaled at N.T.P. conditions C. volume at 0°C and 1 kg/cm2 D. volume at 20°C and 1 kg/cm2 E. none of the above...

The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in pressure ratio_____________________?

A. increases B. decreases C. first increases and then decreases D. first decreases and then increases E. remains same...

Air-fuel ratio in a jet engine will be of the order of__________________?

A. 10: 1 B. 15: 1 C. 20 : 1 D. 60 : 1 E. 100 :...