Accession Number:

AD0637121

Title:

RESEARCH ON THE USE OF BLUNT TRAILING EDGE BLADES IN SUPERSONIC COMPRESSOR STAGES.

Descriptive Note:

Corporate Author:

VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)

Personal Author(s):

Report Date:

1966-05-01

Pagination or Media Count:

105.0

Abstract:

The report covers paper design for stator configurations to match the R-32 rotor tested under a previous grant, cascade tests of blade sections corresponding to those designs, and paper designs for a modified rotor version R-32II, and the associated stator. Tentative performance predictions are presented for both the initial and modified stages. Stator designs for the R-32 rotor have been made using both tandem cascade configurations, incorporating slot effects, and blunt trailing edge blades. Design conditions were to try to turn the flow to axial direction behind the rotor, implying turning of the order of 60 deg to 80 deg, with inlet Mach number to the stator of the orer of .9. Two designs using tandem cascade were studied one using an area reduction across the first row, the second with a constant hub-tip ratio throughout. Danger of choking is predicted for both configurations. Author

Subject Categories:

  • Hydraulic and Pneumatic Equipment

Distribution Statement:

APPROVED FOR PUBLIC RELEASE