Accession Number:

AD0759191

Title:

Transpiration Cooling. Part II. Experimental Study of Wake Effects.

Descriptive Note:

Final rept. 1 Jan 70-30 Nov 72,

Corporate Author:

OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS

Personal Author(s):

• Winget,Leon E.
• Han,L. S.

Report Date:

1973-03-01

Pagination or Media Count:

121.0

Abstract:

An experimental analysis is presented for the investigation of the stator wake effects on the rotor blades which are immediately downstream. A two-dimensional test apparatus is used to simulate the stator and rotor blades. The test section is 2 x 2 feet. The chord length of the test blades is 7 inches. All Reynolds number range is from 100,000 to 200,000. Static pressure readings are recorded along the surface of the rotor test blade as well as a pressure traverse behind the stator blades. The second row of blades are movable with respect to the first row to simulate various positions of the wake interaction. The boundary layer growth is computed by the integral method presented in Part I and compared with another method presented in a recent NASA report, NASA TN-D-5681 McNally, 1970. Author Modified Abstract

Descriptors:

• *GAS TURBINE BLADES
• *COOLING
• AIR COOLED
• CASCADE STRUCTURES
• BLADE AIRFOILS
• TRAILING EDGES
• WAKE
• SKIN FRICTION

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE