Shroud cooling assembly for gas turbine engine
US5169287A · kind A · utility
104Cited by
16References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 20, 1991 |
| Grant date | Dec 8, 1992 |
| Priority date | — |
| Expiry date | May 20, 2011 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- 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 to baffle plenums and thence through baffle perforations to impingement cool the shroud rails and back surface. Impingement cooling air then flows through elongated, convection cooling passages in the shroud and exits to flow along the shroud front surface with the main gas stream to provide film cooling. 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.