Browsing Gas Turbine Laboratory by Title
Now showing items 41-60 of 123
-
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 ... -
Fluorescent visualization for turbomachine research
(Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine Laboratory, [1978], 1978)The quantitative gas fluorescence flow visualization technique using 2,3 butanedione as a tracer, has been refined and improved. Upgrading of the imaging system is responsible for the principal improvement. The technique ... -
Flutter analysis of a tuned rotor with rigid and flexible disks
(Cambridge : Massachusetts Institute of Technology, Gas Turbine & Plasma Dynamics Laboratory, [1979], 1979)The flutter behavior of a simple tuned rotor with a rigid and a flexible disk is reviewed. In Part A, the rotor assembly is assumed to consist of a rigid disk with N uniform flexible blades attached around the circumference, ... -
Flutter and forced response of mistuned rotors using standing wave analysis
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboraotry, [1983], 1983)The torsion flutter and forced response of tuned and mistuned cascades is examined using a standing wave approach, as opposed to the traditional traveling wave approach used in cascades aerodynamic models. The motion of ... -
FORTRAN program for calculating three-dimensional, inviscid, rotational flows with shock waves in axial compressor blade rows : I--user's manual
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1981], 1981)Summary: A FORTRAN-IV computer program has been developed for the calculation of the inviscid transonic/supersonic flow field in a fully three-dimensional blade passage of an axial compressor rotor or stator. Rotors may ... -
Heat transfer measurements in turbines
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1972], 1972)A blowdown turbine facility and an experimental program for the study of heat transfer in cooled turbines are described. The blowdown facility introduces the concept of using short duration experiments to test turbines by ... -
Induced strain actuation of composite plates
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1989], 1989)Two models of induced strain plate actuator/substrate systems are developed and verified experimentally. Equations relating the actuation strains produced by the strain actuators to the induced strains found in the system ... -
The influence of tip clearance on stall limits of a rectilinear cascade of compressor blades
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1959], 1959)An experimental study of the influence of tip clearance on the stall limits of compressor blades was conducted on a two dimensional rectilinear cascade. By using the mirror and image technique the end wall boundary layer ...
