Investigation of a High-Through-Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased 0.010 Inch (Configuration 2).
Abstract
This report presents the results of an experimental evaluation of the single-stage axial compressor with tip clearance increased 0.010 inch. This clearance increase was accomplished by grinding this amount off the tips of the rotor blades. The casing was untouched. The performance goals of this stage were based on a preliminary design study of a multi-stage compressor for an advanced turbojet engine. The results of the tests, reported herein, were achieved with one of a series of minor parametric modifications to the compressor stage. The parametric modifications considered consisted of three casing vortex generator configurations, three separate rotor tip running clearances, and one rotor tip vortex generator configuration. No casing or rotor tip vortex generators were used on the configuration reported herein.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1981
- Accession Number
- ADB059621
Entities
People
- C. Herbert Law
- Daniel J. Gurecki
- Efren C. Strain
- Robert D. Derose
Organizations
- Wright Laboratory