Determination of Rotor and Stator Loss Coefficients for an Axial Turbine with Supersonic Stator Exit Conditions.

Abstract

The results of seven different tests of a single stage axial turbine with converging-diverging stator nozzle are reported. From measurements in a special test rig, losses occurring in the stator and rotor blade rows were separately calculated and the performance of the stage was also determined. The rotor speeds varied from 9,500 to 18,600 r.p.m. and the pressure ratios varied from 1.75 to 3.25. The Mach numbers at the stator exit varied from 0.79 to 1. 38. The results for this turbine are appraised and a procedure is demonstrated for smoothing loss coefficient data from the turbine rig.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1976
Accession Number
ADA028286

Entities

People

  • Edward Franklin Robbins

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Accuracy
  • Boundary Layer
  • Calibration
  • Data Reduction
  • Efficiency
  • Engineering
  • Equations
  • Flow Rate
  • Fluid Dynamics
  • Geometry
  • Kinetic Energy
  • Labyrinth Seals
  • Mach Number
  • Measurement
  • Plastic Explosives
  • Pressure Measurement
  • Reynolds Number

Fields of Study

  • Physics

Readers

  • Aerodynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow