3 Workout Problem Given: High-pressure Fan compressor High-pressure turbine High-pressure shaft Low-pressure shaft Low-pressure compressor Combustion Low-pressure Nozzle chamber turbine Total mass flow rate of air entering the engine Speed of air entering the engine Engine bypass ratio o (2.5 times more air passes through fan than core) Fan exit speed Core exit speed Find: Thrust of the engine. 300 kg/s 300 m/s 2.5 600 m/s 1,000 m/s
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- Parameter thrust Thrust chamber pressure Thrust chamber temperature Working fluid Universal gas constant Ambient pressure: At Sea level value 5MN 7MPa 2800K Air At Room Temperature (Ideal Gas) 8.314 J. (Mol. K) -1 101325N/m² At an altitude of 30km 1185.5 N/m² MW= 29kg/Kw The Following Performance and operation data was obtained from a rocket with a a nozzle designed to produce maximum thrust at sea level: Determine; A) Specific Impulse B) Mass Flow Rate C) Throat Diameter D) Exit Diameter E) Thrust Produced at An altitude of 30KM for the same fixed Nozzle GeometryYou have been asked to help with the low-pressure compressor (LPC) design for a turbofan engine with a bypass ratio of 8.4. The preliminary cycle design calls for the LPC to produce a pressure ratio of 9.4 with the following operating conditions and constraints. .Inlet Conditions TO2 Poz Core Air Mass Flowrate (kg/s) (K) (kPa) 282 24.6 47.0 Design Constraints Maximum Polytropic Efficiency 94.1% Maximum Stage Pr 1.55 Estimate the minimum number of stages required for this LPC. Then assuming the 1st stage of the LPC operates at the maximum allowable pressure ratio, determine the stagnation temperature exiting the 1st stage, and the stage's adiabatic efficiency. Also determine the power (W) required to operate the full LPC (not just 1st stage). Finally, what would be the percent change in the required power if the polytropic efficiency was only 90.0%.i need correct explanation my best wishes ton
- Internal combustion engine I hope for a solution and as soon as possible, with thanks and appreciationHom Work عماد داود عبود (35) Q1: The Fiat car has a four strok engine of 1089 C.C capacity -It develops maximum power 32kw at 5000 r-p.m. The volumetric efficiency at this speed is 75% and the air-fuel ratio 13:1, At peak power the theoretical air speed at the choke is 120 m/sec. The coefficient of discharge for the venturi is 0.85 and that of the main petrol jet is 0.66. An allowance should be made for the emulsion tube, the diameter of which can be taken as (1/2.5) of the choke diameter. the Petrol surface is 6 mm blow the choke at this engine condition. Calculate the size of a suitable chake (D) and main jet (d).The specific gravity of petrol is 0.75 and the atmospheric pressure 1.03 bar and temperature 27°c. [D=23.2mm,d=1.296mm]Fuel in Combustion chamber Turbine Net Power Air in Out Axial compressor Centrifugal compressor Exhaust Figure 1 Figure 1 shows the basic gas turbine cycle. Calculate the efficiency of the system if the temperature for the condition showed in T-s diagram below. Take that mass flow rate is 23 kg/s and the Cp is 35.5 J- K-. mol. TA 8913 °C- 3 4987 °C. 4665 °C- 1276 °CH 2.
- Please solve Sub parts A,B,C im needed max in 60 minutes thank u, im very needed the solve 1) Air enters the compressor from a Brayton cycle at a pressure of 100 kPa, temperature27oC and a volumetric flow rate of 1A m3/s. If the turbine inlet temperature is 11ACoC and the ratiopressure (B, 1A)*. If the Compressor Efficiency is 8A% and the turbine efficiency is 9B%. Define : A. From the simulation results, show the p-v or T-s diagram of each case study on B. Complete Compressor Power (kW), Turbine Power (kW), Net Work (kW), Heat In(kW), Net Heat (kW), Back work ratio, Thermal Efficiency (% No Description Pressure ratio=B Ratiopressure=1A 1 Compressor Work (kW) 2 Turbine Work (kW) 3 Net Work (kW) 4 Heat In (kW) 5 Net Heat (kW) 6 Back Work ratio 7 Thermal Efficiency (%) Attach below is the data from the cyclepad simulation in the form of a cycleproperties (if no answer…7. A converging-diverging nozzle receives steam at a pressure of 380 psia with temperature of 480F and expands it to a pressure of 50 psia. Assuming thelast digit 5 The Snecma M88 is a French afterburning turbofan engine developed by Snecma (now known as Safran Aircraft Engines) for the Dassault Rafale fighter. The following are some preliminary design data at takeoff conditions. The engine pressure ratio 24.5, bypass ratio 0.3 and total air mass flow rate 60+last digit kg/s. Inlet diffuser: stagnation pressure ratio 0.98. Fan: pressure ratio 1.3, isentropic efficiency 0.89, first-stage hubtip diameters 0.22/0.66 m, 0.96. 1. The air inlet velocity to the fan is 150 m/s entering axially and the LP-spool rotating speed is 5000 rpm. Draw the velocity triangle and blade shapes. Calculate maximum inlet relative Mach number. Check if there is any shock formation.
- Uz な、 以う0 Vrz VF = Vz Ure Maxe Dr. Ayser Muneer Turbomachines Example (5-2) An inward flow reaction turbine is supplied with water at a rate of (600 Vsec) with a 3 velocity of flow of (2 m/sec). the velocity of periphery and velocity of whirl at inlet are 24 m/sec and 18 m/sec respectively. Assuming radial discharge at outlet and the velocity of flow to be constant, find; 1- Vane angle at inlet, and 2- Head of water on the wheel. V Solution Vn Q = 0.6 m/sec, Vn=2m/sec, uj=24 m/sec, Vu=18m/sec, V1=Vr2 m/secPlease answerDescribe the reciprocating compressor piston, rod, crank-shaft, valves, valve plate, head, shaft seal, internal motor overload device, pilot-duty motor overload device, and coupling.