Two-Dimensional Flow on General Surfaces of Revolution in Turbomachines

Abstract

A method of analysis is developed for two-dimensional flow on general surfaces of revolution in turbomachines with arbitrary blade shapes. The method of analysis is developed for steady, compressible, nonviscous, irrotational flow that is assumed uniform normal to the surfaces of revolution. Incompressible solutions on a mean surface of revolution between the hub and shroud are presented for four flow rates through each of two centrifugal impellers with the same hub-shroud contours but with different blade spacings. In addition, correlation equations are developed whereby the velocity components and the stream function distribution can be predicted for compressible or incompressible flow in straight-bladed impellers only, with any tip speed, flow rate, area variation, blade spacing, and for any flow surface of revolution.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1952
Accession Number
ADA380530

Entities

People

  • Gaylord O. Ellis
  • John D. Stanitz

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Axial Flow
  • Blade Tips
  • Blades
  • Channel Flow
  • Compressible Flow
  • Coordinate Systems
  • Differential Equations
  • Equations
  • Flow
  • Flow Rate
  • Incompressible Flow
  • Mach Number
  • Partial Differential Equations
  • Static Pressure
  • Three Dimensional
  • Two Dimensional
  • Two Dimensional Flow

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster