A repeating turbine stage with R=0 operates with axial entry. The nozzle turns the flow by 640. Taking gases with Cp=1148 J/kg K, determine: a. The flow coefficient b. The velocity at the nozzle exits if the axial velocity is 240 m/s e. The power per unit mass flow delivered by the stage and drop in stagnation temperature

A repeating turbine stage with R=0 operates with axial entry. The nozzle turns the flow by 640. Taking gases with Cp=1148 J/kg K, determine: a. The flow coefficient b. The velocity at the nozzle exits if the axial velocity is 240 m/s e. The power per unit mass flow delivered by the stage and drop in stagnation 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

See similar textbooks

Similar questions

In a trial run, the De Laval steam turbine at Oman Power Plant rotates at 3000 rpm. The steam is issued from the nozzle at 400 m/s and the nozzle angle is 20o. The blade speed ratio is 0.41and the friction loss in the blade channel is 15%of the kinetic energy corresponding to the relative velocity at the inlet to the blades. As a turbine engineer at that station, how do you determine the (i) power developed by the turbine for a flow rate of 10 kg/s and (ii) suitable inlet and outlet angles for the blades when axial thrust is zero. Also, how would you determine the size of the turbine wheel required? Draw a suitable velocity diagram.
Each stage of an axial flow compressor is of 0.5 reaction, has the same mean blade speed and the same flow outlet angle of 30 degree relative to the blades. The mean flow coefficient is constant for all stages at 0.5. At entry to the first stage the stagnation temperature is 278 K, the stagnation pressure 101.3 kPa, the static pressure is 87.3 kPa and the flow area 0.372 m. Using compressible flow analysis determine the axial velocity and the mass flow rate.
Assuming the clearance is negligible for a single stage compressor with the following data.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/min Take “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K 1.Evaluate the mass flow rate of air inside the compressor operating isentropically in kg/min to 3 decimal places.
At a particular stage of a reaction turbine the mean blade speed is 140 m/sec and the steam is at a pressure of 20 bar with temperature of 250° C. Fixed and moving blades at this stage have inlet angles 30° and exit angles 20°. The stage efficiency is 80%. Determine (1) Specific entholpy drop across the stage in kJ/kg. (i) Drum Dia and blade height if heigh is one-twelfth of the drum dia. and the steam flow is 120 kg/sec. (ii) The percentage increase in the relative velocity across the bladings as a result of pressure drop across the blading.
Assuming the clearance is negligible for a single stage compressor with the following data.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/minTake “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K 1.What is the power input to the compressor in kW to 3 decimal places if the compression reversible isothermal?
A small ramjet engine is to be designed for a maximum thrust of 1000 lb at sea level at a velocity of 950 ft/s. If the exit velocity and pressure are 2000 ft/s and 1.0 atm, respectively, how large should the inlet be?
At a particular stage of a reaction turbine the mean blade speed is 140 m/sec and the steam is at a pressure of 20 bar with temperature of 250° C. Fixed and moving blades at this stage have inlet angles 30° and exit angles 20°. The stage efficiency is 80%. Determine (1) Specific entholpy drop across the stage in kJ/kg.
Specifications: Altitude = 700m Bypass ratio = 0.5 Speed = 260m/s Total mass flow rate = 15kg/s (in cold flow pipe) The pressure = 0.7bar (in cold flow pipe) Stagnation Temperature = 270K (at the turbine outlet) Stagnation gas pressure = 1.84 bar (at the turbine outlet) Temperature = 687.40C Both nozzles have a 95% efficiency For an aircraft powered by a low bypass ratio turbofan engine: 1a) For the flow expansion via the hot core nozzle, draw a T-s diagram. b) Determine the thrust produced by the hot nozzle. c) Determine the overall thrust produced by the turbofan engine and the thrust generated by the cold nozzle.
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.
Assuming the clearance is negligible for a single stage compressor with the following data.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/min Take “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K 1.What is the power input to the compressor if compression is isentropic in kW to 3 decimal places?
The steam from the nozzles of a single wheel impulse turbine is 600m/s and at 20degree to the plane of the wheel. The blade wheel rotates at 3000rev/min and the mean blade radius is 590mm. The axial velocity of the steam at exit from the blade is 164m/s and the blades are symmetrical. Calculate 1: The blade angles; 2: The diagram work per unit mass flow rate steam. 3: The diagram efficiency. 4: The blade velocity coefficient.
A blade pair in an axial flow compressor is being designed. The axial flow component of gas velocity is 174m/s. The engine diameter at the mean blade height is 0.73m and the blade height at the rotor inlet is 0.21m. The rotor's absolute inlet flow angle is 26 degrees. The stagnation conditions at the inlet to the blade pair are 298K and 130kN/m² Using Cp 1.005k/kg/K, R-0.287k/kg/K, and taking the ratio of specific heat capacities as 1.4, calculate the engine mass flow rate to the nearest kg/s