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Comparison of three dimensional quasi-linear large swirl theory with measured outflow from a high-work compressor rotor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1975], 1975)
A three-dimensional perturbation theory for incompressible strongly swirling flow in an annulus is applied to predict the outflow from a high-work compressor rotor (1)(2). A comparison of the analytical result with the ...
An experimental and computational study of the flow in a transonic compressor rotor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1976], 1976)
A comprehensive investigation of the flow field produced by an isolated transonic compressor rotor has been completed. This rotor has an overall diameter of two feet, an inlet hub/tip ratio of 0.5, a tip Mach number of 1.2 ...
Rotor wake behavior in a transonic compressor stage and its effect on the loading and performance of the stator
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1980], 1980)
The structure and behavior of wakes from a transonic compressor rotor and their effects on the loading and performance of the downstream stator have been studied experimentally. The rotor is 2 feet in diameter with a tip ...
A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference
(Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine & Plasma Dynamics Laboratory, [1979], 1979)
A computational study of the flow in a Transonic Axial Compressor has been performed. This compressor has a tip Mach number of 1.2 and an inlet hub to tip ratio of 0.5. The numerical procedure used is a fully three-dimensional, ...
Newton solution of steady two-dimensional transonic flow
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1985], 1985)
A new method is developed for the solution of the steady, two-dimensional Euler equations for transonic flows. The discrete steady-state equations are derived in conservative finite-volume form on an intrinsic streamline ...
Sound generation from a transonic compressor stage
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1981], 1981)
Some aspects of the sound pressure wave characteristics produced by a transonic compressor stage are studied by the use of a simplified mathematical model involving flow parallel to a moving corrugated board. The critical ...
Prediction of three-dimensional compressible turbulent boundary layers on transonic compressor blades
(c1980, c1980)
A small crossflow approximation to the full three dimensional compressible turbulent boundary layer equations for turbomachine blade rows is developed by taking advantage of the nature of blade geometry and inviscid flow ...
Detailed time resolved measurements and analysis of unsteady flow in a transonic compressor
(c1980, c1980)
Detailed time and space resolved measurements for a transonic compressor stage have been completed in the MIT Blowdown Compressor Facility. The stage studied was a new first stage for a NASA two-stage machine which ...
Wake behavior downstream of a transonic compressor rotor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1974, 1974)
Measurements of the static pressure resolved in radial and axial directions downstream of a transonic compressor rotor have been harmonically analyzed. The investigation is part of a program addressing the behavior of ...
Exit flow from a transonic compressor rotor
(Cambridge : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1975], 1975)
Summary: The three dimensional unsteady flow field behind a transonic compressor rotor with a design pressure ratio of 1.6 at a tip Mach number of 1.2 has been resolved on the blade-passing time scale, using the M.I.T. ...