A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor, delivering a net power of 1 MW to the propeller. Air enters the diffuser at 8000 m altitude (Ta = 236K, pa = 36 kPa) with a velocity of 550 km/h, and decelerates essentially to zero velocity. The compressor pressure ratio is 5.3 and the compressor has an isentropic efficiency of 83%. The turbine inlet temperature is 1360 K, and its isentropic efficiency is 86%. The turbine exit pressure is 10 kPa higher than the ambient pressure at that altitude. Flow through the diffuser and nozzle is isentropic. Neglect kinetic energy except at the diffuser inlet and the nozzle exit.  Using an air-standard analysis, determine: a)    The mass and volumetric flow rates entering the diffuser, in kg

Q3//A// In a gas turbine plant compression is carried out in one stage and expansion in one stage turbine. If the maximum temperature (T3K) and minimum temperature (T,K) in the cycle remain constant, show that for maximum work of the plant, the pressure ratio is given by:

Air is expanded in a multi-stage axial flow turbine, and the pressure drop across each stage is very small. Assuming that air behaves as a perfect gas with ratio of specific heats γ, derive pressure-temperature relationships for the following processes: A) Reversible adiabatic expansion: B) Irreversible adiabatic expansion, with small stage efficiency ᵑp ; C) Reversible expansion in which the heat loss in each stage is a constant fraction k of the enthalpy drop in that stage.

An impulsive stage of a steam turbine is supplied with dry and saturated steam at 14.8 bar. The stage has a single row of moving blades running at 3500 rev/min. The mean diameter of the blade disc is 0.91 m. The nozzle angle is 16° and the axial component of the absolute velocity leaving the nozzle is 93.5 m/s. The height of the nozzles at their exit is 100 mm. The nozzle efficiency is 0.85 and the blade velocity co-efficiency is 0.966. The exit angle of the moving blades is 3° greater than at the inlet. Determine: (1) The blade inlet and outlet angles. (2) The isentropic heat drop in the stage. (3) The stage efficiency. (4) The power developed by the stage....solve with me 40 minutes

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A turboshaft engine comprising a gas generator and a free power turbine is selected to provide propulsive power for a helicopter. The helicopter is hovering in ISA conditions at an altitude of 4100 feet. The following data applies to this engine at this static max power operating point. Intake mass flow: 8.9 kg/s Compressor pressure ratio: 24.5 Compressor isentropic efficiency: 88% Mechanical efficiency: (HP & PT shaft) 99% Combustion chamber pressure loss Combustion chamber inlet pressure 4% Combustion efficiency 98.8% Combustion chamber exit temperature: 1585K Gas generator turbine isentropic efficiency:  92% Power turbine isentropic efficiency: 90%   The effects of the intake and exhaust ducts may be ignored. It may be assumed that for: Air: Cp = 1.005 kJ/kg • K, y = 1.4, R = 0.287 kJ/kg • K Combustion gases: Cp = 1.148kJ/kg • K, y = 1.333, R = 0.287 kJ/kg • K A 6% direct bleed of air from the exit of the compressor is…

Steam enters a turbine stage with an internal energy of 3,072 kJ/kg at 69 m/s and leaves the same stage with an internal energy of 2,111 kJ/kg and a velocity of 113. Calculate the power (in kW) if there are 1.965 kg/s steam admitted at the turbine throttle?