Browsing Gas Turbine Laboratory Reports by Title
Now showing items 120 of 123

Accurate, efficient difference operators for the turbulent field equations
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1975], 1975)Introduction: A potentially powerful method for predicting and describing turbulent flow fields is that of utilizing a finite number of moments of the instantaneous NavierStokes equations. This sequence of moment equations ... 
Active control of rotating stall in a threestage axial compressor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1993], 1993)Stall inception in a threestage axial compressor has been suppressed over a range of previously unstable operating points through the feedback of velocity perturbations to the inlet flow field. Perturbations were generated ... 
Active control of rotating stall in axial compressors
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1992], 1992)An active control system has been implemented on a lowspeed singlestage axial compressor. This control system stabilizes the perturbations which normally lead to rotating stall, thus extending the range of operation of ... 
Active stabilization of rotating stall and surge in a transonic single stage axial compressor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1997, 1997)Rotating stall and surge have been stabilized in a transonic singlestage axial compressor using active feedback control. The control strategy is to sense upstream wall static pressure patterns and feed back the measured ... 
Aerodynamics of aircraft engines : stride and stumbles
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1992, 1992)Summary: Attempts to understand and predict the aerodynamic behaviour of compressors and turbines in aircraft gas turbines have been encouraged by the intense competitive pressure which exists. Many of the apparently most ... 
Analysis and design of transonic cascades with splitter vanes
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1991, 1991)A new computational method, MISES, is developed for turbomachinery design and analysis applications. The method is based on the fully coupled viscous /inviscid method, ISES, and is applicable to bladetoblade analysis of ... 
An analytical and numerical study of the secondorder effects of unsteadiness on the performance of turbomachines
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1992], 1992)A linear approach in two dimensions is used to investigate the secondorder effects of unsteadiness on the efficiency of turbomachines. The three main themes are the identification of physical nature and location of unsteady ... 
Asymmetric inlet flow in axial turbomachines
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1959, 1959)A modified actuator disc analysis is made which, through an improved prediction of the blade forces, attempts to give closer correspondence with experiment than the previous theory. The fluid is assumed inviscid and ... 
Asymmetric inlet flows through axial compressors
(Cambridge : Massachusetts Institute of Technology, Gas Turbine & Plasma Dynamics Laboratory, [1980], 1980)A new analytical method is proposed for the study of flow through highlyloaded turbomachine stages. The technique is used in the present study in order to: (i) analyze the threedimensional induced effects of the viscous ... 
Asymptotic analysis of numerical wave propagation in finite difference equations
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1983], 1983)An asymptotic technique is developed for analysing the propagation and dissipation of wavelike solutions to finite difference equations. It is shown that for each fixed complex frequency there are usually several wave ... 
Attenuation of sound in lined circular ducts
(Cambridge : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1975], 1975)In the previous report, we have used approximate expressions for the wall impedance for the discussion of sound attenuation in lined circular ducts. For instance, Eq. (2.5) has been used for the wall impedance of a circular ... 
Attenuation of sound in lined ducts
(Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1974], 1974)Extensive computations have been carried out of the attenuation characteristics of resonator and porous type duct liners in rectangular and circular ducts. First the frequency dependence of the attenuation constant and the ... 
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 bladetip 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, twodimensional diffuser and two conical diffusers. A simple analytical ... 
Calculation of a selfconsistent, low frequency electrostatic field in the driftkinetic 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 inversesquare plasma frequency, for the selfconsistent, low frequency electrostatic field in tori. The derivation is consistent with the driftkinetic 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 ...