Systems and methods for variable microchannel combustor liner cooling
US-11859818-B2 · Jan 2, 2024 · US
US9200526B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9200526-B2 |
| Application number | US-201113332106-A |
| Country | US |
| Kind code | B2 |
| Filing date | Dec 20, 2011 |
| Priority date | Dec 21, 2010 |
| Publication date | Dec 1, 2015 |
| Grant date | Dec 1, 2015 |
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A transition piece 10 in an embodiment is provided with an inner duct 20 through which a combustion gas is led to a turbine part 130 and an outer duct 30 that is provided so as to cover an outer periphery of the inner duct 20 and has a plurality of ejection holes 31 to eject air onto an outer peripheral surface of the inner duct 20 formed therein. It is structured such that a channel cross-sectional area of a cooling air channel 50 that is formed between the inner duct 20 and the outer duct 30 and through which the air ejected from the ejection holes 31 flows gradually decreases at an air flow downstream side rather than the portion where the ejection holes 31 are formed, and gradually increases from a throat portion 60 having the minimized channel cross-sectional area to an air flow downstream side.
Opening claim text (preview).
What is claimed is: 1. A transition piece configured to lead a combustion gas to a turbine, the combustion gas being generated by burning air pressurized by a compressor and fuel in a combustor liner, the transition piece comprising: an inner duct connected to an end portion of an outlet of the combustor liner, the inner duct being configured to lead the combustion gas from the combustor liner to the turbine; an outer duct surrounding an outer periphery of the inner duct with an…
Mechanical Engineering · mapped topic
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