Tapered enlargement metering inlet channel for a shroud cooling assembly of gas turbine engines
US5165847A · kind A · utility
60Cited by
16References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 20, 1991 |
| Grant date | Nov 24, 1992 |
| Priority date | — |
| Expiry date | May 20, 2011 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
To cool the shroud in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow through channels, which include tapered enlargement frustroconical recuperators, to baffle plenums and thence through baffle perforations to impingement cool the shroud rails and back surface. The baffle perforations and the convection cooling passages are interactively located to achieve maximum cooling benefit and highly efficient cooling air utilization.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.