Method, system, and apparatus for reducing a turbine clearance
US9758252B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 22, 2016 |
| Grant date | Sep 12, 2017 |
| Priority date | — |
| Expiry date | Apr 18, 2036 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D31/06
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.