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| Content Provider | The American Society of Mechanical Engineers (ASME) Digital Collection |
|---|---|
| Author | Rodrick, V. Chima |
| Copyright Year | 1996 |
| Abstract | The flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data. Tip clearance effects were modeled both by gridding the clearance gap and by using a simple periodicity model across the ungridded gap. The simple model was run with both the full gap height, and with half the gap height to simulate a vena-contracta effect. Comparisons between computed and measured performance maps and downstream profiles were used to validate the models and to assess the effects of gap height on the simple clearance model. Recommendations were made concerning the use of the simple clearance model. Detailed comparisons were made between the gridded clearance gap solution and the laser anemometer data near the tip at two operating points. The computed results agreed fairly well with the data but overpredicted the extent of the casing separation and underpredicted the wake decay rate. The computations were then used to describe the interaction of the tip vortex, the passage shock, and the casing boundary layer. |
| Sponsorship | International Gas Turbine Institute |
| File Format | |
| ISBN | 9780791878729 |
| DOI | 10.1115/96-GT-114 |
| Volume Number | Volume 1: Turbomachinery |
| Conference Proceedings | ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition |
| Language | English |
| Publisher Date | 1996-06-10 |
| Publisher Place | Birmingham, UK |
| Access Restriction | Open |
| Subject Keyword | Nasa Rotors Wake turbulence Clearances (engineering) Compressors Separation (technology) Flow (dynamics) Lasers Computation Wakes Shock (mechanics) Probes Boundary layers |
| Content Type | Text |
| Resource Type | Article |
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