At the start of cruise the temperature and pressure of the air entering the engine may be taken tobe 259 .5K and 46.0 kPa. Assume a pressure ratio of 1.6 for flow through the fan which enters the coreand a pressure ratio of 25 in the core compressor itself. Assume isentropic efficiencies of 90% in eachcomponent. Find the temperature rise across the fan of the flow entering the core compressor, thetemperature entering the core compressor and thence the temperature at exit from the corecompressor.Fan bypass statorLP TurbineLP Booster stageBypass jetFanCorejetRotorHP CompressorCombustorCorenozzle2-stage HP turbineBypass nozzle

temperature rise across the fan = T2' -T1 = 300.94-259.5 = 41.44 K temperature at the entry point of…

Answered: At the start of cruise the temperature…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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please provide fast answer Steam issues from the nozzle of a single-impulse turbine at 800 m/sec on to blades moving at 300 m/sec. The blade tip angles at inlet and outlet are 36º each. The steam is to enter the blades without shock and the flow over the blades is frictionless. Determine— (a) the angle at which the nozzles are inclined to the motion of the blades; (b) diagram efficiency.
centrifugal compressor has pressure ratio of 4:1 with an isentropic efficiency of 80% when running at 15000 rpm and inducting air of 293° K. Curved vanes at inlet given the air a pre whirl of 25° to the axial direction curved vanes at inlet given the air a pre whirl of 25° to the axial direction at all radil and mean dia of eye is 250 mm. The absolute air velocity at inlet is 150 m/sec. Impellér tip dla 600 mm calculate slip
axial flow compressor of 50% reaction, blading has isentropic efficiency of 82%. It draws air at 17 °C and compresses in the pressure ratio of 4:1. The mean blade speed and flow velocity are constant through out the compressor. The inlet and outlet angles of blades are 15° and 45° respectively from axial direction. Blade speed = 180 m/sec work input factor, 2=0.84. Calculate (i) flow velocity (il) no. of stages.
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an air compressor of three stage compresses air from 100 kpa to 1000 kpa. calculate the intercooler pressure between the first and second stage
The compression ratio in a gasoline engine is 8. The total cylinder volume of the engine (for the bottom dead point) is 600 ml, and air enters the cylinders at a temperature of 20 ° C and a pressure of 100 kPa andThe maximum temperature of the cycle is known as 1500 ° C. a) Calculate the heat input in the cycle in kJ. b) Calculate the thermal efficiency of the cycle c) Calculate the power generated in the cycle.
Steam issues from the nozzle of a single-impulse turbine at 800 m/sec on to blades moving at 300 m/sec. The blade tip angles at inlet and outlet are 36º each. The steam is to enter the blades without shock and the flow over the blades is frictionless. Determine— (a) the angle at which the nozzles are inclined to the motion of the blades; (b) diagram efficiency.
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An ammonia refrigerator produces 30 tonnes of ice from ant at 0 °C in 24 hours. The temperature range of the compressor is 25 °C to -15 °C. The vapour is dry saturated at the end of compression. Assume a coefficient of performance to be 60% of the theoretical value. Calculate the power required to drive the compressor. Latent heat of ice = 135 kJ/kg. Properties of ammonia are as follows:Temperat ureEnthalpy (kJ/kg)Specific entropy (kJ/kg-K)(oC) Liquid Vapour (hf) (hg)Vapor (Sf) (Sg)Liquid25 -15298.90 1465.84 112.34 1426.541.1242 0.45725.0391 5.5490
explanation of the performance tests undertaken for a wind turbine. With the options found, give a justified recommendation for the best system.

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