Aeroengine - axial flow compressor , Other Engineering

An axial-flow air compressor consists of 10 rotor/stator stages each built from p gblades of identical cross-section and designed such that the axial velocity is constant throughout the machine. The first stage is shown schematically in Figure L11. The flow enters each rotor row and leaves each stator row axially. All flow processes may be assumed to be isentropic. V3 V1Mass flow rate = 5 kg/sPressure ratio across each stage = 1.25 Degree of reaction for each stage = 50% Rotational speed = 6000 rpm 293 Inlet temperature and pressure = 293 K and 1 bar Stator entry flow angle = 25° to tangential V2

Calculate to 3 significant figures:

a) the overall pressure increase.

b) the density at inlet to the compressor.

c) the pressure, density and temperature at exit from the compressor.

d) the density and temperature at exit from the first stage.

e) the temperature at exit from the first rotor row.

f) the axial velocity

g) the rotor absolute exit velocity and the tangential velocity at exit from the first rotor row.

h) the overall power input into the compressor. 

1939_Axial flow compressor.png

Posted Date: 8/27/2012 2:51:14 AM | Location : United States







Related Discussions:- Aeroengine - axial flow compressor , Assignment Help, Ask Question on Aeroengine - axial flow compressor , Get Answer, Expert's Help, Aeroengine - axial flow compressor Discussions

Write discussion on Aeroengine - axial flow compressor
Your posts are moderated
Related Questions
Fuel control system in Aircraft Engine: The computer controls the fuel flow to the engine to maintain a constant rotor RPM. During normal operation the optimum engine/rotor spe

Expertsmind.com  brings you unique solution in Electrical Engineering Logic GATES   Logic gates process one or more input signals in a logical manner. Depending on th

how to making terrestrial tele scope an how its work and formulation of terrestrial telescope

Approach The Hanley solver does solve for the boundary layer and potential flow (in a way we will think about later). However, it only gives us full access to the potential solu

Acoustic linings in Aircraft engine: One method of suppressing the noise from the fan stage of a high by-pass ratio engine is to incorporate a noise absorbent liner around the

Blow Holes                    (i) Excessive moisture in the moulding sand.                   (ii) Low permeability and excessive fine grain sands.                   (iii

Comparison of  fp result with other metods Comparisons of FP results with results from other computational methods for inviscid flows are given. The FP results have been obtain

Q.  Define co-ordination number. Ans.CO-ORDINATION NUMBER: The number of atoms which are directly surrounding a given atom is known as coordination number. Number of atoms w

hOW LONG WILL IT TAKE AN AMOUNT TO DOUBLE IF THE INTEREST RATE IS 7% P.A. COMPOUNDED ANNUALLY

I have a fermenter case study which needs to be completed in the next 16 hours.