Systems and methods for variable microchannel combustor liner cooling
US-11859818-B2 · Jan 2, 2024 · US
US9010122B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9010122-B2 |
| Application number | US-201213560622-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jul 27, 2012 |
| Priority date | Jul 27, 2012 |
| Publication date | Apr 21, 2015 |
| Grant date | Apr 21, 2015 |
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A turbine engine assembly includes a combustor and a stator vane arrangement having a plurality of stator vanes. The combustor includes a combustor wall that extends axially from a combustor bulkhead to a distal combustor wall end, which is located adjacent to the stator vane arrangement. The combustor wall includes a support shell with a plurality of impingement apertures, and a heat shield with a plurality of effusion apertures. The combustor wall end includes a plurality of circumferentially extending film cooled regions. At least one of the film cooled regions is circumferentially aligned with one of the stator vanes and includes a cooling aperture.
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What is claimed is: 1. A turbine engine assembly, comprising: a stator vane arrangement including a plurality of stator vanes; and a combustor including a combustor wall extending axially from a combustor bulkhead to a distal combustor wall end that is located adjacent to the stator vane arrangement; wherein the combustor wall includes a support shell with a plurality of impingement apertures, and a heat shield with a plurality of effusion apertures; wherein the combustor wa…
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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