Question

.A-7 The gas turbine engines that are used on a military jet air plane likely consists of a diffuser, compressor, combustor, turbine, afterburmer, and nozzle that are arranged in series as shown in Figure 4.A-7(a) and flying with a velocity of 350 mph. The analysis will be carried out on a component-by component basis. Model the air as an ideal gas and assume that it has constant c and cp R 287.1 Ikg-K and c-1005 Jkg-K). Difuser Air drawn into the engine first encounters the diffuer. The purpose of the diffuser is to reduce the velocity of the air (with respect the engine) which causes an increase in its pressure. The diffuser is the reverse of a nozzle; it is a duct with a varying cross-sectional area that slows the air L. 13-227°C down. The air enters the diffuser with a velocity that is equal to the velocity of the jet, V 350 mph. The mass flow rate of air entering the engine is?-25 kes. The jet is flying at an altitude where the inlet air pressure is P 75 kPaand the temperature is Ti- 5°C. The pressure of the air leaving the diffuser is P220 kPa. Assume that the diffuser operates at steady state and is adiabatic. Further assume that the exit velocity of the diffuser (the velocity at state 2) is small enough that the kinetic energy of the air leaving the diffuser is negligible. You may ignore the potential energy of the flow entering and leaving the diffuser a.) Determine the inlet diameter of the diffiuser. b.) Determine the temperature of the air exiting the diffuser. T4-1120°C P P5.5 urbine (5250 kPa P.-220 kPa 0) / T,-1120C intet air +-25.0 kg's 7,-900 C The compressor shown in Figure 2 for the GoblinII engine is a single stage centrifugal compressor which has a pressure ratio PR 5.5, that is, the pressure at the compressor exit (P) is 5.5 times larger than the pressure at the compressor inlet (P). The temperature of the air leaving the compressor is T- 227°C. You may assume that the compressor operates at steady state and is adiabatic. Vou may neglect the kinetic and potential energy of the flow entering and leaving the compressor. c.) Determine the volumetric flow rate leaving the compressor. d) Determine the power required by the compressor 350 mph =75kPa r =5°C Figure 4.A-7a): Schematic of a gas turbine jet engine with an afterburner. Figure 4A-7(b) shows the Goblin II turbojet engine (used as the primary engine on the F80 airplane) sectioned so that the compressor, combustion chambers, and turbine are all visible. As the air passes through the combustor, it is mixed with fuel which is ignited, releasing heat. Here, we will model this combustion as a hcat transfer, Qat a rate that is sufficient to bring thc temperature ofthe air leaving the combustor to T.-112OC. You may assume that there is no pressure loss in the combustor so that P4P. The combustor operates at steady state and you can ignore the kinetic and potential energy of the flow entering and leaving the combustor. e) What is the rate of heat transfer that must be provided to the combustor, Q? Twbine The turbine provides sufficient mechanical power to drive the compressor (sometime additional power is extracted to run auxiliary systems like electronics, etc. but we'll neglect that herc); therefore, -W. The turbine exit pressure is P 250 kPa. You may assume that the turbine operates at steady state and is adiabatic. Vou may neglect the kinetic and potential energy of the flow entering and leaving the turbine. f) Determine the temperature of the air leaving the turbine. Aterburner In order to achieve a short duration boost in the thrust that the engine provides, the pilot can activate the afterburner. The afterburner acts like an additional combustor. As the air through the afterburner, it is mixed with fuel which is ignited, releasing heat Here, we will model this combustion as a heat transfer, Q at a rate that is sufficient to bring the temperature Figure4A-7(b): The Goblin II jet engine. passes This problem analyzes the jet engine shown in Figure 4.A-7(a) under conditions that are approximately consistent with the Goblin II jet engine mounted on a plane flying at high altitude

please solve h to m

Answer 1