Systems and methods for variable microchannel combustor liner cooling
US-11859818-B2 · Jan 2, 2024 · US
US9316396B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9316396-B2 |
| Application number | US-201313845439-A |
| Country | US |
| Kind code | B2 |
| Filing date | Mar 18, 2013 |
| Priority date | Mar 18, 2013 |
| Publication date | Apr 19, 2016 |
| Grant date | Apr 19, 2016 |
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A hot gas path duct or unibody liner for a gas turbine includes a main body having a forward end and an aft end. The main body defines a cross-sectional flow area and an axial flow length that extends between the forward end and the aft end. The main body further defines a fuel injection portion disposed downstream from the forward end and upstream from the aft end. The cross-sectional flow area decreases along the axial flow length between the forward end and the fuel injection portion and increases along at least a portion of the axial flow length downstream from the fuel injection portion.
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What is claimed is: 1. A unibody liner, comprising: a. a main body having a forward end and an aft end, the main body defining a cross-sectional flow area and an axial flow length that is defined between the forward end and the aft end, the main body further defining a fuel injection portion disposed downstream from the forward end and upstream from the aft end; and b. wherein the cross-sectional flow area decreases along the axial flow length between the forward end and the fue…
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