Gas turbine engine having outlet guide vanes
US-2024418094-A1 · Dec 19, 2024 · US
US9512781B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9512781-B2 |
| Application number | US-201113806523-A |
| Country | US |
| Kind code | B2 |
| Filing date | Aug 10, 2011 |
| Priority date | Sep 30, 2010 |
| Publication date | Dec 6, 2016 |
| Grant date | Dec 6, 2016 |
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In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a wall, and that recovers and reuses the bled and pressurized air as combustion air for burning fuel in the combustor together with a main flow of the compressed air, wall cooling in which cooling air is supplied to cooling air passages formed in the wall of the combustor to perform cooling involves a downstream wall region, closer to a turbine, that is cooled using the bled and pressurized air as the cooling air and an upstream wall region, closer to a burner, that is cooled using, as the cooling air, bled compressed air bled from a main flow of the compressed air through a housing inner space.
Opening claim text (preview).
The invention claimed is: 1. A cooling structure for a recovery-type air-cooled gas turbine combustor comprising: first cooling passages formed in a downstream wall region of a wall of the gas turbine combustor, the first cooling passages being configured to cool the downstream wall region of the gas turbine combustor by receiving first cooling air bled from a compressed air supply passage and pressurized; and second cooling passages formed in an upstream wall region of the wall…
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