Q2. The following particulars relate to a two row velocity compounded impulse wheelwhich forms a first stage of a combination turbine.Steam velocity at nozzle outlet = 579.12m/sMean blade velocity = 115.82m/sNozzle outlet angle = 16°Outlet angle first row of moving blades = 18°Outlet angle fixed guide blades = 22°Outlet angle, second row of moving blades = 36°Steam flow rate = 2.4 kg/sThe ratio of the relative velocity at outlet to that at inlet is 0.84 for all blades. Determinefor each row of moving blades the following⚫ The velocity of whirl• The tangential thrust on blades• The axial thrust on the blades• The power developedWhat is the efficiency of the wheel as a whole?

To solve this problem, we'll use the given data and calculate the required values for each row of…

Answered: Q2. The following particulars relate to…

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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The following data relate to a compound impulse turbine having two rows of moving blades and one row of fixed blades in between them. Steam velocity coming out of nozzle = 450 m/sec., Nozzle angle 15°, Moving blades tip discharge angles = 30°, Fixed blade discharge angle = 20°, Friction loss in each blade rows = 10% of the relative velocity. Find the blade velocity, blade efficiency and specific steam consumption for turbine.
please wright by hand and steb by steb
A single jet Pelton wheel is required to drive a generator to develop 10Mw. The available head at the nozzle is 762m. Assuming electric generator efficiency is 95%, Pelton wheel efficiency 87%, coefficient of velocity 0.97, mean bucket velocity 0.46 of the jet velocity, outlet bucket angle 15° and the friction of bucket reduces the relative velocity by 15%, find (a) the flow rate of water through turbine (b) the diameter of the jet (c) the force exerted by the jet to the nozzle.
6.9 One stage of an impulse turbine consists of a converging nozzle and one ring of moving blades. The nozzle angles are 22° and the blade angles are 35°. The velocity of steam at the exit from the nozzle is 650 m/s. If the relative velocity of steam to the blades is reduced by 14% in passing through the blade ring, find the diagram efficiency and the end thrust on the shaft when the blade ring develops 1650 kW. (79.2%, 449 N)
3. A 90% efficient Francis turbine running at 100 rpm discharges 6m * 3/s of water. The inner runner radius is 1.8 m and the outer periphery of the wheel has a radius of 2.5 m. The blade height is 50 cm. The blade angle beta_{1} is 80 degrees and beta_{2} is 160 degrees Find the vane angle, torque, and the power from the turbine
6.31 : A double-spool turbofan engine; Fig. (6.66), is used to power an aircraft flying at speed of 250 m/s at an altitude of 11,000 m. As shown in the figure below, the low-pressure turbine drives the fan and low-pressure compressor, while the high-pressure turbine drives the high-pressure compressor. The engine has the following data: Bypass ratio = 8. Total ingested air flow rate = 180 kg/s. Overall pressure ratio OPR = 35. Fan pressure ratio = 1.6. Pressure ratio of high-pressure compressor is four times that of the low-pressure compressor; πHPC= 4 πLPC. Turbine inlet temperature = 1650 K. Fuel heating value = 43 MJ/kg. Assuming all processes are ideal and neglecting any pressure drop, it’s required to: Find the thrust, TSFC, and efficiencies of the engine Plot the velocity and temperature distribution over the engine cross section (rear end).
Q1/1In a single-stage axial flow gas turbine of A319 Airbus Airplane has an axial velocity is equal to 250 m/s, and assume equal inlet and outlet velocities. Stage exit swirl angle is 9° , mass flow rate of gas is 15 kg/s, and nozzle efflux angle is 63°. Assume that blade speed is 350 m/s, gas enters at stagnation pressure of 5 bar, and stagnation temperature of 1980 °R. Also, assume y = 1.33, and C,,=1.147 kJ/kg. K. Determine the rotor blade gas angles, output power, blade-loading coefficient, and degree of reaction.
Q2) Design a Francis turbine with the following specifications: Head available 68m Speed Power output Hydraulic efficiency Overall efficiency Flow ratio X 750 rpm 330kw 94% 85% 0. 15 0.1 Breadth to diameter ratio at inlet Outer to inner diameter ratio 1/2 Assume 6% of circumferential area of runner occupied by thickness of vanes and flow velocity remains constant and flow is radial at exit.
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/sec
5.16. For a centrifugal compressor rotating at 2500 rpm, find the compression ratio for the following specifications. T = 300 K; 79 (volumetric flow rate)=1.25 m³/s and t (the thickness of the flow section at the exit) = 0.15 m. = 0.85; r, = 0.55; ra = 0.015; B, 60°,
3.21) An axial flow compressor has an overall pressure ratio of 4.0 and mass flow of 3 kg/s. If the polytropic efficiency is 0.88 and the stagnation temperature rise per stage must not exceed 25 K, calculate the number of stages required and the pressure ratio of the first stage. Assume equal temperature rise in all stages. If the absolute velocity approaching the 1st stage rotor is 165 m/s at an angle of 20° from the axial direction, the work done factor is 0.83, the velocity diagram is symmetrical, and the mean diameter of the 1st stage rotor is 18 cm, calculate the rotational speed and the length of the 1st stage rotor blade at inlet to the stage. Ambient conditions are 1.01 bar and 288 K. [7,1.273, 356 rev/s, 19.45 cm]
2. A Pelton wheel is working under a head of 180 m with a discharge of 0.8 m3 /s. The following data are available for the turbine: Coefficient of velocity = 0.985 Angle of deflection of jet = 165° Speed ratio 0.46 Relative velocity at exit = Relative velocity at inlet Jet ratio 12 Compute the (a) hydraulic efficiency, (b) velocity of whirl at inlet and outlet, and (c) mean bucket speed. Assume zero frictional loss in the bucket.

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