Gas turbine with baffle reducing hot gas ingress into interstage disc cavity
US6558114B1 · kind B1 · utility
54Cited by
16References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 29, 2000 |
| Grant date | May 6, 2003 |
| Priority date | — |
| Expiry date | Sep 29, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/081
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The subcavity between a stator seal assembly and the upstream rotor disc in the interstage disc cavity of a gas turbine is divided into a radially inward region and a radially outward region by an annular baffle that extends from the seal assembly partially across the subcavity toward the rotor disc. The volume of cooling air injected into the interstage disc cavity can be reduced to increase turbine efficiency because the baffle interrupts recirculation in the subcavity to confine ingress of the hot main gas flow to the radially outward region away from the rotor seals.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.