Active clearance control for gas turbine engine
US8998563B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jun 8, 2012 |
| Grant date | Apr 7, 2015 |
| Priority date | — |
| Expiry date | Jun 3, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C9/00
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An active clearance control system for a gas turbine engine includes a structural member that is configured to be arranged near a blade tip. A plenum includes first and second walls respectively providing first and second cavities. The first wall includes impingement holes. The plenum is arranged over the structural member. A fluid source is fluidly connected to the second cavity to provide an impingement cooling flow from the second cavity through the impingement holes to the first cavity onto the structural member. A method includes the steps of providing a conditioning fluid to an outer cavity of a plenum providing an impingement cooling flow through impingement holes from an inner wall of the plenum to an inner cavity, directing the impingement cooling flow onto a structural member, and conditioning a temperature of the structural member with the impingement cooling flow to control a blade tip clearance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.