A gas turbine power plant receives an unknown type of hydrocarbon fuel. Some of the fuel is burned with air, yielding the following Orsat analysis of the products of combustion, CO2 = 10.5%; O2 = 5.3% and N2 = 84.2%. Determine the percentage of theoretical air.

1.      Based on various gas turbine configurations (i.e turboprop, turbojet, turbofan, turboshaft), indicate which engine type would be most applicable for the following aerospace applications, and why it is the most appropriate i)                   Military application of the Joint Strike Fighter (JSF) ii)                  A short range commercial flight, i.e. Cardiff to Dublin iii)                A hypersonic unmanned aerospace vehicle (UAV) iv)                A long range commercial flight, i.e. London-New York

If the range of the aircraft needs to be increased to 8000km from 6000km what changes to the engine would you consider to be appropriate?

Can you please help me with ONLY the C,D, and E parts of this question? I would appreciate any insight or explanation on the final 3 parts only.  I asked this question already but I got an explanation of the first 3 instead of the final. lol. Thank you! For C, I understand that Th>Ti>Tc, does this mean that since the ec=1-Tc/Th that the efficiency won't change with having two engines because we are using the same temps?

consider the mass and pulley system in the attached file. mass m1 = 29 kg and mass m2 = 12kg. the angle of the inclined plane is given and the coefficient of kinetic friction between mass m2 and the inclined plane is uk = 0.12. assume the pulleys are massless and frictionless when mass m2 moves a distance 4.94 m up the ramp, how far downward does mass m1 move? d= ?

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Please solve with full explain and analyze max in 2 hours thank u Describe what is done in the combustion process in the combustion chamber of a gas turbine to overcome the problem of a very low laminar flame speed compared to aircraft speed and a limited flame limit range?

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ENGINE SPECIFICATIONS: Engine Type : Four cylinder Four stroke Diesel engine, Bore: 0.073m, Stroke: 0.0889m Capacity: 1489cc, Power: 36 H.P. at 4000 rpm, Torque : 8.5 kg.m at 2250 rpm and Compression Ratio :17.3:1 Explain how to measure the :- (i) Fuel consumption. (ii) (iii) Manometer readings for air flow. RPM, power output etc. Study of various components of diesel engine.