Accession Number:

AD0687231

Title:

AN EXPERIMENTAL INVESTIGATION OF PRESSURE DISTRIBUTION ON THE END OF A COOLED BLADE,

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1969-03-04

Pagination or Media Count:

15.0

Abstract:

The pressure distribution on the end plane of a cooled blade was studied in order to facilitate control of the cooling air flow rate. The test stand consisted of a centrifugal compressor, a combustion chamber, a mixing chamber, a honeycomb damper, the test section with the investigated cascade profiles, a fuel-feed system, a control panel, and monitoring instrumentation. The investigated cascade consisted of five cylindrical blades, only one of which was cooled. The blades had a chord of 121.7 mm, a height of 120 mm, and a pitch of 83.3 mm. The mounting of the blades provided a shock-free inlet flow. The cooling air was supplied from the main flow. The pressure distribution in the radial clearance was studied with respect to the following factors 1 air flow rate through the cascade 2 size of the radial clearance 3 cooling air flow rate through the blade channels and 4 the total effect of the three factors. Author

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE