Compact advanced passive tip clearance control
US10344612B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 13, 2017 |
| Grant date | Jul 9, 2019 |
| Priority date | — |
| Expiry date | Nov 20, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/177
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.