The capability for experimental assessment of unsteady shock wave effects on turbine blade performance has been developed. A novel shock-generation system utilizing a shotgun blast has been implemented into the Virginia Tech Wind Tunnel Transonic Cascade Facility. Specialized optical systems and high-performance pressure instrumentation were utilized to obtain both qualitative and quantitative information.
Shadowgraph photos of the unsteady shock wave propagation through the cascade indicate presence of a vortical region and its movement from the blade surface into the passage flow. A previously unseen distortion of the trailing edge shock wave is also identified. High-frequency blade surface pressure measurements reveal large fluctuations in surface pressure during shock passage. An estimate of unsteady blade lift is made which reveals a 120 percent peak-peak variation. Furthermore, an approximated loss coefficient was determined to fluctuate as much as 40 percent near the blade passage center. Comparisons are made with previously-published experimental and analytical results. / Master of Science
| Identifer | oai:union.ndltd.org:VTETD/oai:vtechworks.lib.vt.edu:10919/44281 |
| Date | 18 August 2009 |
| Creators | Collie, Jeffery C. |
| Contributors | Mechanical Engineering, Moses, Hal L., Schetz, Joseph A., O'Brien, Walter F. Jr. |
| Publisher | Virginia Tech |
| Source Sets | Virginia Tech Theses and Dissertation |
| Language | English |
| Detected Language | English |
| Type | Thesis, Text |
| Format | xi, 175 leaves, BTD, application/pdf, application/pdf |
| Rights | In Copyright, http://rightsstatements.org/vocab/InC/1.0/ |
| Relation | OCLC# 24957108, LD5655.V855_1991.C653.pdf |
Page generated in 0.1451 seconds