Two Axial Compressor Designs for a Stage Matching Investigation
Abstract
The design of two single-stage axial-flow compressors for a stage matching investigation are described. The purpose of the investigation is to develop a data base and design techniques necessary to match supersonic blade rows in turbomachinery compression systems. Two compressor designs are required to investigate both fan-type and core-type compression systems, since each configuration has unique aerodynamic and performance characteristics. The latest state-of-the-art aerodynamic and mechanical design techniques were used to design two supersonic stages to be tested in an environment typical of the second-stage of an advanced military fan and an advanced military core compressor. This report presents the results of the detailed aerodynamic design of the two compressor stages. Keywords: Axial compressor, Gas turbine, Aircraft turbine engine.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1989
- Accession Number
- ADA206951
Entities
People
- C. H. Law
Organizations
- Wright Laboratory