Thermal control passages for horizontal split-line flanges of gas turbine engine casings
US6352404B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 18, 2000 |
| Grant date | Mar 5, 2002 |
| Priority date | — |
| Expiry date | Feb 18, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D25/243
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A casing for a gas turbine engine having a longitudinal axis extending therethrough, including a first casing portion having a substantially arcuate section and a split-line flange extending from each end thereof and a second casing portion having a substantially arcuate section and a split-line flange extending from each end thereof. The first and second casing portions are mated at each end by connecting together respective pairs of the split-line flanges. A channel is formed in at least one mating surface of the split-line flanges to provide an axial passage therethrough so that air flow provided to the axial passage reduces a temperature gradient between the arcuate sections and the flanges of the first and second casing portions. The gas turbine engine casing also includes a first radial channel formed in at least one mating surface of the split-line flanges to provide an entrance to the axial passage and a second radial channel formed in at least one mating surface of the split-line flanges to provide an exit to the axial passage so that flow communication is established between a flowpath through the casing and the axial passage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.