Shock cancellation mechanism for the control of unsteady interaction in contra-rotating high- and low-pressure turbines
US8739508B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Sep 29, 2009 |
| Grant date | Jun 3, 2014 |
| Priority date | — |
| Expiry date | Dec 23, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a high pressure turbine used in combination with a contra-rotating low pressure turbine, in which the geometry of the inlet guide vane of the low pressure turbine induces a reflection of the incident shock wave from the high pressure turbine airfoil that propagates back upstream to impact the blade thereby denigrating both the performance of the high pressure turbine and its durability. The shock wave reflection is eliminated by fitting the downstream vanes with holes or indentations that allow jets of compressor bleed air to penetrate the boundary layer and induce a net velocity component across the main-flow direction in the near-wall region. This induced flow component acts to cancel the net flow component created by the moving shock from the upstream blade row thereby obviating the reflection that occurs naturally to cancel the flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.