Accession Number:

AD0745834

Title:

Influence of the Cooling Air Exhaust Method on the Effectiveness of Cooling of the Trailing Edges of Gas Turbine Blades,

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

• Ronkin,L. M.

Report Date:

1972-04-27

Pagination or Media Count:

10.0

Abstract:

Blades of the same profile, with a deflector ensuring transverse flow in the blade cavity from the leading to the trailing edge were tested to study the cooling characteristics of several types of air exhaust with respect to the trailing edges of the blades. Best trailing edge cooling was obtained with blades where the cooling air is exhausted directly into the ring clearance. Author

Descriptors:

• *GAS TURBINE BLADES
• *COOLING
• EXHAUST GASES
• HEAT TRANSFER COEFFICIENTS
• USSR

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE