Gas turbine engine rapid response clearance control system
US10301961B2 · kind B2 · utility
6Cited by
10References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 23, 2014 |
| Grant date | May 28, 2019 |
| Priority date | — |
| Expiry date | Jul 2, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.