Turbine disk interstage seal axial retaining ring
US5338154A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Mar 17, 1993 |
| Grant date | Aug 16, 1994 |
| Priority date | — |
| Expiry date | Mar 17, 2013 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T403/7058
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An axial retention system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk and a second stage disk. The interstage seal includes a web portion having an aft arm extending from said web, the aft arm having a peripheral rim adjacent the second stage disk. The axial retention system comprising a split ring having two overlapping ends and a plurality of radially outwardly extending tabs for engaging a plurality of inwardly extending tabs located on the second stage disk adjacent the peripheral rim, in a bayonet connection. The retaining ring is located within a slot formed in the peripheral rim and the outwardly extending tabs are positioned in a passageway formed by the disk tabs.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.