Tailored thermal control system for gas turbine engine blade outer air seal array
US10408080B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 6, 2014 |
| Grant date | Sep 10, 2019 |
| Priority date | — |
| Expiry date | Mar 29, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/50212
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A clearance control ring for a clearance control system of a gas turbine engine includes a contoured radial outer portion that defines a multiple of fins and a multiple of slots. A clearance control system of a gas turbine engine includes a clearance control ring with a radial inner portion from which a contoured radial outer portion extends. The contoured radial outer portion defines a multiple of fins and a multiple of slots. A blade outer air seal assembly with a clearance control ring land which receives the radial inner portion. A method of controlling a radial tip clearance within a gas turbine engine includes tailoring a multiple of fins and a multiple of slots of a clearance control ring for both steady state and transient clearance operations.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.