Browsing Gas Turbine Laboratory Reports by Title
Now showing items 34-53 of 123
-
The design of axial inducers for turbo-pumps
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)In many turbopump applications it is desirable to run the pump at the highest possible speed to minimise the size and weight of the unit and facilitate matching with a drive turbine. Frequently, a limit on rotational speed ... -
Design of the MIT Breakdown Turbine Facility
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1985], 1985)Summary: This report details the design, construction, and preliminary testing of a short duration (0.4 sec) test facility capable of testing 0.5 meter diameter, film cooled, high work aircraft turbine stages under conditions ... -
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 ... -
The development of a perturbed, incompressible, turbulent boundary layer
(Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1969], 1969)The response of a fully-developed equilibrium turbulent boundary layer to a small disturbance was observed experimentally under low-Mach number conditions: a turbulent boundary layer in an axisymmetric channel under zero ... -
The display of multi-dimensional flows in turbomachinery
(Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1972], 1972)Introduction: As part of a general development of computational techniques for multidimensional flows through turbomachine passages and over turbomachine blading at the M.I.T. Gas Turbine Laboratory, display techniques and ... -
Dynamic control of rotating stall in axial flow compressors using aeromechanical feedback
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1993], 1993)Dynamic control of rotating stall in an axial flow compressor has been implemented using aeromechanical feedback. The control strategy developed used an array of wall jets upstream of a single stage compressor which were ... -
Effect of swirl on turbulent jets in ducted streams
(Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine Laboratory, [1968], 1968)An experimental and theoretical program of research has been carried out to determine the effect of swirl on the mixing of a turbulent jet in a ducted stream. The term swirl is used to describe a flow pattern within the ... -
The effect of tip clearance on an axial flow fan
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1955], 1955)The effect of tip clearance on the performance of a single stage axial flow (6000 cfm) fan was investigated for tip clearances ranging from 0.003 in. to 0.252 in. It was found that, at the rated flow, the stagnation pressure ... -
The effect of upstream rotor vortical disturbances on the time-average performance of axial compressor stators
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1997, 1997)Time-accurate Reynolds-averaged Navier-Stokes simulations have been carried out to investigate the impact of upstream rotor wakes and tip leakage vortices on the loss of a compressor stator. The objective is to (1) identify ... -
Effects of compressor endwall suction and blowing on stability enhancement
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1988], 1988)An experimental investigation was carried out to examine the effects on stall margin of flow injection into, and removal out of, the endwall region of an axial compressor blade row. A main goal was to identify the mechanism ... -
Effects of inlet conditions on centrifugal diffuser performance
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1997], 1997)This report examines the influence of inlet flow conditions, including Mach number, flow angle, blockage, and axial flow non-uniformity, on the performance and operating range of a straight channel centrifugal compressor ... -
Effects of non-axisymmetric tip clearance on axial compressor performance and stability
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1997], 1997)The effects of circumferentially non-uniform tip clearance on axial compressor performance and stability have been investigated experimentally and analytically. A theoretical model for compressor behavior with non-axisymmetric ... -
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. ... -
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 ... -
Experimental investigation of flow distortion effects on the performance of radial discrete-passage diffusers
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1991], 1991)A swirling-radial-flow generator has been developed for the study of fluid-dynamic phenomena in radial passage- and vaneless-diffusers. A unique feature of the swirling-flow generator is the capability of providing a wide ... -
Experimental investigation of Stator hub treatment in an axial flow compressor
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1981], 1981)An experiment was carried out to examine the effects, on stator stall margin and performance, of a slotted hub treatment rotating beneath the stator of an axial flow compressor. The compressor was run with this hub treatment ... -
Experiments on turbulent boundary layers along a circular cylinder with and without separation
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1967], 1967)Summary: Experiments were conducted in a turbulent boundary-layer near separation along a circular cylinder with the flow in the axial direction. The pressure gradient along the axis of the cylinder could be varied such ... -
Experiments on turbulent boundary layers along a circular cylinder with and without separation
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1967], 1967)Summary: Experiments were conducted in a turbulent boundary-layer near separation along a circular cylinder with the flow in the axial direction. The pressure gradient along the axis of the cylinder could be varied such ... -
Feedback stabilization of compression systems
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1993, 1993)An experimental and analytical study was conducted on the use of feedback stabilization to extend the stable operating range of compression and pumping systems. Prevention of surge, in aircraft gas turbine engines, an ... -
Flow visualization study of the inlet vortex phenomenon
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1981], 1981)The inlet vortex phenomenon was experimentally investigated in a water tunnel, using hydrogen bubble flow visualization techniques. Several inlet ambient flow combinations were studied, including an inlet and ground plane ...
