Search
Now showing items 1-7 of 7
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 ...
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, ...
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. ...
Stalled flow performance of a single stage transonic compressor
(Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine & Plasma Dynamics Laboratory, [1978], 1978)
The stalled flow performance of a single stage transonic compressor is examined, using data from the MIT Gas Turbine Laboratory's Blowdown Compressor Facility. Measurements of the blowdown corrected weightflow are included, ...