APPLICATION OF THE BLUNT TRAILING EDGE BLADE CONCEPT TO LOW HUB TIP RATIO TRANSONIC-SUPERSONIC COMPRESSORS.
Abstract
The report covers first cascade calculations and testing on blunt trailing edge blade in the subsonic range. A relaxation method, suitable for the calculation of the flow in blunt trailing edge blade is first described. A semi-empirical method of calculation for the flow in the blade passage in the compressible range, including local supersonic region terminated by normal shock and taking into account shock-boundary layer interaction, is then described as well as its verification against experiment. A semi-empirical correlation of secondary losses against blade camber and aspect ratio is then described, which appears to be of rather general application. The report then describes the design methods utilized and the resulting design for the stator blading adapted to the Mach 2, 0.5 hub-tip ratio rotor designed previously. It covers blade shape evaluation including trailing edge evolution in function of radius, wall shaping and loss prediction. A single blade row, using blunt trailing edge blade is obtained. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 30, 1969
- Accession Number
- AD0691091
Entities
People
- F. Breugelmans
- H. Griepentrog
- H. Rottiers
- Joë-Marc Chauvin
Organizations
- von Kármán Institute for Fluid Dynamics