Browsing Gas Turbine Laboratory by Title
Now showing items 13-32 of 123
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Blade passage flow structure effects on axial compressor rotating stall inception
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1996], 1996)A new computational approach has been developed to study the inception of rotating stall in axial compressors. Using this approach the flow structures within the compressor blade passages have been examined in order to ... -
Blade scale effects of tip leakage
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1990], 1990)The effects of blade-tip leakage in a turbine are investigated by modeling the stage as an incomplete actuator disk. It is found that the spanwise flow redistribution due to the gap is such as to produce a uniform unloading ... -
Boundary layer effects on airfoil lift
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)A study of the discrepancy in lift between potential flow calculations and experiments was made. In potential flow the fluid is assumed to follow the contour of the airfoil, forming a stagnation point at the geometric ... -
Boundary layer on an airfoil in a cascade
([Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)A study of the turbulent boundary layer on an airfoil in a cascade is presented. The major portion of the observations are on the suction surface of the airfoil. The effect of added diffusion across the cascade due to a ... -
Boundary layer separation ; preliminary report
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1962], 1962)The phenomenon of incompressible boundary layer separation and the existing methods of predicting it are discussed. The failure of these theories in many cases clearly indicates a need for further investigation. A program ... -
Boundary layer separation in internal flow
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1965], 1965)An investigation of incompressible turbulent boundary layer separation in internal flow is presented with experimental results for a variable geometry, two-dimensional diffuser and two conical diffusers. A simple analytical ... -
Calculation of a self-consistent, low frequency electrostatic field in the drift-kinetic approximation
(Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine and Plasma Dynamics Laboratory, [1977], 1977)We derive an asymptotic series in [omega]p -2 , the inverse-square plasma frequency, for the self-consistent, low frequency electrostatic field in tori. The derivation is consistent with the drift-kinetic ordering and may ... -
Cascade performance with accelerated or decelerated axial velocity
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1959], 1959)A theoretical method to estimate the effect of axial velocity change through a cascade was investigated. The change of axial velocity was reproduced by distributing sinks and sources within the blade passages, and the ... -
A cascade tunnel for investigation of rotating stall
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1954], 1954)A test apparatus which will reproduce the rotating stall phenomenon found in axial compressors has been constructed and installed in the main wind tunnel circuit of the Gas Turbine Laboratory. The test section consists of ... -
Centrifugal effect on the boundary layer on a blade of an axial turbo-machine
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1962], 1962)A study of the effect of centrifugal force acting on the turbulent boundary layer of a blade in a turbo-machine is presented. The study includes experimental work conducted in an apparatus featuring an annular cascade of ... -
Channel flow modeling of impingement cooling of a rotating turbine blade
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1984], 1984)Local heat transfer distributions in impingement cooling have been measured by Kreatsoulas [1] and Preiser [2] for a range of conditions which model those in actual turbine blades, including the effects of rotation. These ... -
Collapse of the inter-electrode breakdown arc in the magnetic field direction
(Cambridge : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1975], 1975)A two-dimensional inter-electrode breakdown arc which is uniform in the magnetic field direction is shown to be unstable. The growth time for the instability is of the order of the arc development time. It is unlikely that ... -
Comparative study of tip clearance effects in compressors and turbines
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1961], 1961)The influence of tip clearance on the lift distribution along a blade span was studied on linear compressor and turbine cascades. The wall boundary layer was removed by means of the image technique. The lift distribution ... -
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 ... -
A computational model for rotating stall and inlet distortions in multistage compressors
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1999], 1999)This thesis presents the conceptualization and development of a computational model for describing three-dimensional non-linear disturbances associated with instability and inlet distortion in multistage compressors. ... -
Computational simulation of unsteady flow in transonic compressor rotor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1986], 1986)The unsteady flow about a section of a modern first stage transonic compressor rotor was simulated using a finite difference approximation to the two-dimensional, Reynolds averaged, unsteady, compressible, viscous Navier-Stokes ... -
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, ... -
Condensation of supersaturated organic vapors in a supersonic nozzle
(Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1967], 1967)Experiments were performed involving condensation of supersaturated benzene and chloroform vapors in a supersonic nozzle, with compressed air as the carrier gas. Experiments showed that the magnitude of the water vapor ... -
Condensation of supersaturated organic vapors in a supersonic nozzle
(Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1967], 1967)Experiments were performed involving condensation of supersaturated benzene and chloroform vapors in a supersonic nozzle, with compressed air as the carrier gas. Experiments showed that the magnitude of the water vapor ... -
Control of the unsteady flow in a stator blade row interacting with upstream moving wakes
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1993], 1993)A computational study of the unsteady flow in a 2-D stator blade row interacting with upstream rotor wakes has been carried out. A direct spectral-element Navier-Stokes solver has been used for the laminar flow regime ...
