Clearance control for gas turbine engine seal
US8961115B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 19, 2012 |
| Grant date | Feb 24, 2015 |
| Priority date | — |
| Expiry date | Nov 20, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/407
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine section has a rotor carrying a plurality of blades. The blades have airfoils which define a radially outer tip. A blade outer air seal is positioned radially outwardly of the tips of the blades. The blade outer air seal is provided by at least a plurality of circumferentially spaced segments, which slide circumferentially relative to each other to adjust an inner diameter of an inner surface of the blade outer air seal segments. An actuator actuates the blade outer air seal segments to slide towards each other to control a clearance between the inner periphery of the blade outer air seal segments and the radially outer tip of the blade airfoils. A gas turbine engine is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.