Rotor assembly with blade sealing tab
US10975714B2 · kind B2 · utility
0Cited by
38References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 22, 2018 |
| Grant date | Apr 13, 2021 |
| Priority date | — |
| Expiry date | Mar 12, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The gas turbine engine rotor assembly includes a rotor disc with a plurality of sealing tabs projecting radially out from a peripheral surface of the rotor disc in the rear end portion thereof. A said sealing tab is disposed at a tip portion of a fixing member of the disc, formed between pairs of blade root slots, adjacent a trailing edge of the rotor disc. The sealing tabs help to reduce the leakage of secondary air out the back of a blade pocket defined between adjacent blades mounted on the rotor disc.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.