A. polytropic compression

C. isothermal compression

D. any one of the above

E. none of the above

A. bled gas from turbine is heated and readmitted for complete expansion

C. exhaust gases drive the compressor

D. heated

E. part of exhaust gases are heated and mixed up with atmospheric air to utilise exhaust heat

A. higher heating value

B. heating value

C. highest calorific value

E. higher calorific value

B. 18 m3/mt

C. 0.75 m3/mt

D. 1.5 m3/mt

E. 6 m3/mt

A. less power requirement

B. less loss of air due to leakage past the cylinder

C. better mechanical balance

D. more effective lubrication

A. work done in first stage should be more

B. work done in subsequent stages should decrease

C. work done in any stage is no criterion for minimum work but depends on other factors

E. work done in subsequent stages should increase

A. no such co-relationship with jet velocity exists

B. jet velocity

C. average of the jet velocity

D. twice the jet velocity

A. it does not increase pressure much

B. it requires cylinder to be placed in water

C. it is impossible in practice

D. ityrequires very big cylinder

A. ramjet-engine has no turbine

B. bypass turbo-jet engine increases the thrust without adversely affecting, the propulsive efficiency and fuel economy

D. propeller is an indirect reaction device

E. turbine drives compressor in a burbojet

B. increase in thermal efficiency but decrease in net output

C. increase in both thermal efficiency and net output

D. decrease in both thermal efficiency and net output

E. none of the above

A. the ratio of stroke volume to clearance volume

B. reciprocal of compression ratio

C. proportional to compression ratio

E. index of compressor performance

A. gas turbine requires lot of cooling water

B. gas turbines can be used to generate power only

C. gas turbines have high standby losses and require lot of maintenance

D. gas turbines have flat efficiency at part loads

A. 25C, 1 kg/cm2 and RH of 60%.

B. 15C and 1 kg/cm2

D. 0C and standard atmospheric conditions

E. atmospheric conditions at any specific location

B. U,<V0

C. Vri=Vm

D. Vt>V0

E. V,= U0

A. rockets

B. turbo-jet engine

C. hydraulic jet propulsion

D. propellers

A. 4:01

B. 2:01

C. 1:01

E. 1:02

A. cant be compared

B. unpredictable

C. equal

D. higher

A. diffuser losses

C. inlet losses

D. none of the above

E. impeller channel losses

A. axial flow compressors have instability region of operation

C. axial flow compressors have high capacity and efficiency

D. large gas turbines employ axial flow compressors

E. centrifugal compressors are used mainly on low flow pressure ratio gas turbines

A. uniformly heated

B. at the base

C. at the tip

E. in the center

A. may increase/decrease depending on compressor clearance

C. remain unaffected

D. increase

E. none of the above

A. same way as the natural gas

B. partial combustion of caol, eke, anthractie coal or charcoal in a mixed air steam blast

D. carbonisation of coal

E. passing air and a large amount of steam over waste coal at about 65C

A. does not require oxygen

B. uses surrounding air

C. depends on electrical energy supplied by solar cells

E. uses compressed atmospheric air

A. low/high depending on make and type

C. unpredictable

D. high

E. same

B. decrease

C. unpredictable

D. remain unaffected

E. other factors control it

B. better than isothermal and adiabatic

C. none of the above

D. same as adiabatic

E. same as isothermal

B. N.T.P. conditions

C. none of the above

D. 20C and 1 kg/cm2

E. 0C and 1 kg/cm2

A. mechanical balance is better

B. better lubrication is possible advantages of multistage

D. more uniform torque, light cylinder and saving in work

E. air can be cooled perfectly in between

A. steam power plant

C. solar plant

D. diesel engine

E. petrol engine

A. 0.5 kg

B. 1.0 kg

C. 2.2 kg

E. 3.2 kg

A. bulk modulus

B. toughness

C. fatigue

D. corrosion resistance

A. thrust power and fuel energy

C. propulsive power and fuel input

D. none of the above

E. engine output and propulsive power

A. increase pressure

B. decrease the delivery temperature for ease in handling

C. cool the air

E. reduce volume

B. employing intercooler

C. by constantly cooling the cylinder

D. none of the above

E. by insulating the cylinder

A. 20:01

B. 100:00:00

D. 15:01

E. 10:01

B. first decreases and then increases

C. unpredictable

D. decreases

E. increases

A. Outlet temperature is reduced

B. It is best suited for compression ratios around 7:1

C. Power consumption per unit of air delivered is low

E. The moisture in air is condensed in the intercooler

A. more

C. same

D. unpredictable

E. may be less or more depending on ambient conditons

A. liquid hydrogne

B. high speed diesel oil

D. demethylated spirit

E. methyl alcohol

A. pressure coefficient

C. slip factor

D. pressure ratio

E. stage factor

B. depends on other factors

C. same

D. unpredictably

E. more

A. none of the above

C. increase first at slow rate and then fast

D. increase first at fast rate and then slow

E. decrease continuously

B. rocket principle for its operation

C. one air stream

D. solid fuel firing

E. no air stream

A. first increases and then decreases

B. remains same

C. decreases

D. first decreases and then increases

A. hydrogen

C. none of the above

D. nitrogen

E. carbon dioxide

B. open cycle

C. both of the above

D. closed/open depending on other con-siderations

E. unpredictable

A. increase pressure ratio

C. reduce turbine size

D. increase speed

E. increase temperature

A. diesel engine

B. D.C. electric motor

D. A.C. electric motor

E. petrol engine

A. unpredictable

C. increases

D. increases/decreases depending on com-pressor capacity

E. decreases

A. is self-operating at zero flight speed

C. none of the above

D. requires no air for its operation

E. produces a jet consisting of plasma