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Unconventional blade design for compressors
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1969], 1969)
One of the factors causing the low efficiency of axial flow compressors operating at decreased flow rates is the flow separation at blade extremities. To postpone this tendency to separate to lower flow rates, compressor ...
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, ...
Measurements of aerodynamic damping on the MIT transonic rotor
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1981], 1981)
A method has been developed and demonstrated for the direct measurement of aerodynamic forcing and aerodynamic damping of a transonic compressor. The method is based on the inverse solution of the structural dynamic equations ...
Uniform-inlet three-dimensional transonic Beltrami flow through a ducted fan
(Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine Laboratory, [1977], 1977)
Introduction: This report is a continuation of a line of analytical treatment of three dimensional flows in compressor or ducted fans. In the earlier theories [1,2,9,10], the blade row is modelled as a set of spinning ...
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, ...