Shroud for gas turbine engine
US10989070B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 31, 2018 |
| Grant date | Apr 27, 2021 |
| Priority date | — |
| Expiry date | Nov 4, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/205
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.