Turbine rim cavity sealing
US8038399B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Nov 22, 2008 |
| Grant date | Oct 18, 2011 |
| Priority date | — |
| Expiry date | Jun 10, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/083
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rim cavity seal arrangement for a gas turbine engine, where the rim cavity is formed between two rotor disk stages with a stator vane assembly positioned between the rotor disks and extending into the rim cavity. A cover plate secured onto a side of the rotor disk includes a plurality of cooling air injectors directed to discharge cooling air into an annular groove formed on the underside of the vane endwall adjacent to the rotor disk to form an air cushion that seals the rim cavity from hot gas ingestion. The cover plate forms a cooling air supply passage with the rotor disk side to supply the injectors, and the cover plate includes at least one metering hole to meter the pressurized air into the injectors.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.