Now showing items 1-20 of 123

    • A cascade tunnel for investigation of rotating stall 

      Kriebel, Anthony R.; Stenning, Alan H. (Alan Hugh) (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 ...
    • The effect of tip clearance on an axial flow fan 

      Ryan, Francis J. (Francis James); Ōhashi, Hiroshi (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 ...
    • Stall propagation in axial compressors 

      Stenning, Alan H. (Alan Hugh) (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1955], 1955)
      A theory of stall propagation in a cascade of airfoils of high solidity has been developed which includes the effects of finite blade chord and of the boundary layer response to changes in angle of attack. The theory is ...
    • An investigation of rotating stall in a single stage axial compressor 

      Montgomery, Stephen Ross; Braun, Joseph J. (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1955], 1955)
      The rotating stall characteristics of a single stage axial flow compressor were investigated. The number of stall cells and their propagation velocities were found with and without stator blades. The measured velocities ...
    • A study of the end wall boundary layer in an axial compressor blade row 

      Moore, Raymond W. (Raymond William); Richardson, David L. (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1955], 1955)
      Turbulent end wall boundary layers in the hub region of axial compressor blade rows have been studied in the Gas Turbine Laboratory. Both analytical and experimental work are presented. An attempt was made to predict the ...
    • Three-dimensional laminar boundary layer in curved channels with acceleration 

      Senoo, Y. (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1956], 1956)
      A theory is developed for two families of three-dimensional laminar boundary layers; namely, for the boundary layer on the parallel plane end walls of a curved channel with logarithmic spiral side walls, and for the boundary ...
    • Stall propagation in a cascade of airfoils 

      Kriebel, Anthony R. (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1956], 1956)
      An experimental investigation of stall propagation in a stationary circular cascade by means of high speed schlieren and interferometer photography is described. This investigation suggests an analytical approach to the ...
    • The three-dimensional turbulent boundary layer in a free vortex diffuser 

      Gardow, Ernest Bernhard (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)
      Experimental velocity profiles and static pressure measurements were obtained from the flow in a free vortex diffuser. The purpose of the study was to obtain additional three dimensional boundary layer data and to compare ...
    • The design of axial inducers for turbo-pumps 

      Stenning, Alan H. (Alan Hugh) (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 ...
    • Secondary flow and losses in a compressor cascade 

      Soderberg, Olof E. (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)
      Three ways in which secondary flow can be generated in a straight compressor cascade have been investigated. 1. Wakeflow. The inlet flow is characterized by a constant inlet angle and a varying stagnation pressure over the ...
    • Boundary layer on an airfoil in a cascade 

      Peterson, Carl R. ([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 effects on airfoil lift 

      Schneider, Kurt H. (Kurt Herbert) (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 ...
    • An investigation of cavitating inducers for turbopumps 

      Mullan, Philip Joseph (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1959], 1959)
      The experimental performance of two axial inducers is presented. One of the :designs is analytical and includes radial equilibrium considerations. The other is a simple helix, with a constant pitch angle. The performance ...
    • Cascade performance with accelerated or decelerated axial velocity 

      Kubota, Shigeo (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 ...
    • Asymmetric inlet flow in axial turbomachines 

      Seidel, Barry S. (Barry Stanley) (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 ...
    • The influence of tip clearance on stall limits of a rectilinear cascade of compressor blades 

      Khabbaz, Ghassan R. (Ghassan Raji) (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 ...
    • Skewed turbulent boundary layers 

      Nelson, Warren G. (Warren George) (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1959], 1959)
      The problem of predicting the growth of incompressible, skewed, turbulent boundary layers on smooth surfaces is considered. It is supposed that sufficient initial information and a complete knowledge of the external pressure ...
    • Temperature wake in an adverse pressure gradient 

      Sturek, Walter B. (Walter Beynon) (Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1961], 1961)
      A study is made of the flow pattern resulting from the presence of a temperature wake in a uniform velocity field subjected to various adverse pressure gradients. Dimensionless temperature profiles and velocity profiles ...
    • Comparative study of tip clearance effects in compressors and turbines 

      Yokoyama, Eiji (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 ...
    • Boundary layer separation ; preliminary report 

      Moses, Hal Lynwood (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 ...