EXPERIMENTAL COLD-FLOW INVESTIGATION OF CHORDWISE STATIC PRESSURE DISTRIBUTION AROUND A TURBINE AIRFOIL.

Abstract

The results from preliminary cold-flow tests are presented. The performance of the in-house turbine cascade rig was checked and calibrated over a cascade airflow range of 3 to 7 pounds per second. Cold-flow measurements were made to investigate the chordwise static pressure distribution around the test blade surface. Experimental data from these tests provided valuable velocity, pressure, and flow distributions around the test blade. Once the flow field around the 'standard' blade profile is known, the gas-to-blade heat transfer coefficients around the blade can more accurately be determined. This information is important in assessing the blade cooling design requirements for future hot-flow tests. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1968
Accession Number
AD0668766

Entities

People

  • David H. Quick
  • Robert E. Henderson
  • Wayne A. Tall

Organizations

  • Air Force Research Laboratory

Tags

DTIC Thesaurus Topics

  • Coefficients
  • Creep
  • Experimental Data
  • Flow
  • Flow Fields
  • Heat Transfer
  • Heat Transfer Coefficients
  • Measurement
  • Pressure Distribution
  • Static Pressure

Readers

  • Aerodynamics.
  • Aerospace Test and Evaluation
  • Combustion and Flow Dynamics.