Gas turbine engine compressor stator seal
US9169849B2 · kind B2 · utility
4Cited by
10References
3Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | May 8, 2012 |
| Grant date | Oct 27, 2015 |
| Priority date | — |
| Expiry date | Jun 24, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor section for use in a gas turbine engine has a plurality of compressor stages. Each compressor stage is provided with a rotor hub, and each rotor hub mounts a plurality of compressor blades. A rotor drum extends between adjacent rotor hubs. A plurality of stator stages have an outer ring and a radially inner ring. A plurality of vanes extend between the outer and inner rings. An inner surface of the inner ring is spaced by a gap from an outer surface of the rotor drum. The rotor drum is provided with a plurality of blades having a general airfoil shape to resist leakage across the gap.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.