Possible Application of Blade Boundary-Layer Control to Improvement of Design and Off-Design Performance of Axial-Flow Turbomachines

Abstract

A theoretical discussion of the application of blade boundary-layer control to increase the efficiency and the stage pressure ratio and to improve off-design performance of turbomachines is presented. A method based on the potential flow of a compressible fluid is developed for designing suction, or ejection, slotted blades having a prescribed velocity distribution along the blade and in the slot. The effect of the boundary layer on the design of the slot and the effect of ejecting gas at stagnation pressures and temperatures different from free-stream values are discussed.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1951
Accession Number
ADA382294

Entities

People

  • George R. Costello
  • John T. Sinnette Jr.

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Axial Flow
  • Axial Flow Compressors
  • Boundary Layer
  • Boundary Layer Control
  • Boundary Layer Flow
  • Coefficients
  • Complex Variables
  • Compressible Flow
  • Compressors
  • Fluid Dynamics
  • Incompressible Flow
  • Leading Edges
  • Mach Number
  • Mass Flow
  • Potential Flow
  • Stagnation Point
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.