Accession Number:

ADA243881

Title:

Experimental Investigation into the Effects of Riblets on Compressor Cascade Performance

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING

Personal Author(s):

• Rothenflue, James A.

Report Date:

1991-12-01

Pagination or Media Count:

120.0

Abstract:

The effects of adding riblets to the blades of a subsonic, linear compressor cascade were investigated at the Air Force Institute of Technology. Three blade configurations were tested, including a set of unmodified NACA 64- A905 series blades, a set with riblets applied to the suction surface, and a set with riblets on the pressure surface. Performance was evaluated over a wide range of Reynolds numbers, and at low and high free stream turbulence levels. Cascade performance was evaluated in terms of total pressure loss coefficient, turning angle, and static pressure rise. No riblet configuration offered robust cascade performance improvements however, performance was significantly enhanced under certain specific conditions. Riblets also degraded cascade performance at other conditions.

Descriptors:

• *PRESSURE GRADIENTS
• ANGLES
• AIR FORCE
• PERFORMANCE(ENGINEERING)
• BLADES
• COEFFICIENTS
• PRESSURE
• SUBSONIC CHARACTERISTICS
• LOSSES
• RANGE(EXTREMES)
• COMPRESSORS
• SUCTION
• STATIC PRESSURE
• REYNOLDS NUMBER

Subject Categories:

• Fluid Mechanics
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE