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Small disturbances in compressor annuli with swirl, throughflow and entropy variation
(Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1970], 1970)
Introduction: Control of the radiation of sound from the compressors and turbines of jet engines depends to a great extent on understanding of the propagation of acoustical modes in the ducting, the general design approach ...
The M.I.T. Blowdown Compressor Facility
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1972], 1972)
A Blowdown Compressor Test Facility has been developed which allows aerodynamic testing of full-scale compressor stages at low cost. The rotor is brought to speed in vacuum, a diaphragm is opened, and the test gas allowed ...
Noise generation by shock-turbulence interaction
(Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1970], 1970)
The noise produced by convection of turbulence through an oblique shock wave has been measured and compared to theoretical predictions by Ribner and Kerrebrock. There is excellent agreement with the theoretical prediction ...
Rotor wake transport in turbomachine stators
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1971], 1971)
The mechanism of rotor wake interaction with stators has been examined experimentally by using helium, injected into the rotor wakes, as a tracer for the wake fluid. Time averaged helium Drofiles downstream of the stator, ...
Noise and performance of propellers for light aircraft : final report
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1980], 1980)
Introduction and Summary: The project "Noise and Performance of Propellers for Light Aircraft," Contract #NASl-15154 between NASA Langley and MIT, has now been completed, and the main results obtained are summarized in ...
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. ...