Compressor section of gas turbine engine including shroud with serrated casing treatment
US11015465B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 25, 2019 |
| Grant date | May 25, 2021 |
| Priority date | — |
| Expiry date | Dec 5, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/10
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor section includes a shroud surface and a rotor with a blade tip that opposes the shroud surface. The rotor is configured to rotate within the shroud about an axis of rotation. Moreover, the compressor section includes a serration groove that is recessed into the shroud surface. The serration groove includes a forward portion with a forward transition and a forward surface that faces in the downstream direction. The forward transition is convexly contoured between the shroud surface and the forward surface. The serration groove includes a trailing portion with a taper surface and a trailing transition. The taper surface tapers inward as the taper surface extends from the forward surface to the trailing transition. The trailing transition is convexly contoured between the taper surface and the shroud surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.