Coolable outer air seal assembly for a gas turbine engine
US5333992A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 5, 1993 |
| Grant date | Aug 2, 1994 |
| Priority date | — |
| Expiry date | Feb 5, 2013 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D11/005
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A coolable outer air seal assembly for a gas turbine engine is disclosed. Various construction details are developed which provide an outer air seal assembly comprised of a plurality of seal segments including bumpers adapted to maintain adequate cooling fluid flow through the clearance gap between adjacent seal segments. In one particular embodiment, each seal segment includes a mating surface having a plurality of bumpers disposed adjacent to cooling fluid channel outlets and an axially extending ridge disposed along the radially outer edge of the mating surface. The bumpers extend circumferentially a distance H.sub.b to maintain a minimum opening G.sub.min between adjacent seal segments and extend a radial distance W.sub.b to restrict fluid from flowing axially through the clearance gap. The ridge extends radially outward to define in part a seal edge for engaging a feather seal.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.