Modifications to the Inlet Flow Field of a Transonic Compressor Rotor.

Abstract

The flow to the rotor of a single stage axial transonic compressor was found to be in disagreement with design requirements. The incidence angle to the rotor blading was measured to be towards stall in the hub and tip regions when close to design near center-span. Hardware modifications were made, guided by flow field calculations. Predictions were compared with measurements. The most significant improvement was obtained by increasing the flow rate at open throttle. No practical method to correct the flow near the hub was found. Keywords: MERIDL computer program; Transonic compressor; Inlet flow field; Distortion screens.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1985
Accession Number
ADA178746

Entities

People

  • Friedrich Neuhoff

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Compressor Rotors
  • Compressors
  • Diameters
  • Flow
  • Flow Fields
  • Flow Rate
  • Geometry
  • Leading Edges
  • Libraries
  • Mach Number
  • Mass Flow
  • Measurement
  • Peak Values
  • Radial Velocity
  • Shape
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.