Turbine blade passive clearance control
US5688107A · kind A · utility
23Cited by
12References
4Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 28, 1992 |
| Grant date | Nov 18, 1997 |
| Priority date | — |
| Expiry date | Dec 28, 2012 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Intersecting judiciously located installed holes at the tip section of the airfoil of an internally cooled axial flow turbine blade for a gas turbine engine communicating with a passage adjacent the pressure side and another passage adjacent the suction side of the airfoil provide a resultant flow that creates an aerodynamic seal that opposes the flow of engine working medium leaking into the clearance between the tip of the airfoil and the surrounding annular shroud or outer air seal. The installed holes are in proximity to the intersection of the tip surface with the airfoil pressure side surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.