Rapid processing of laminar composite components
US-12180120-B2 · Dec 31, 2024 · US
US8991185B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-8991185-B2 |
| Application number | US-201113097221-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 29, 2011 |
| Priority date | May 3, 2010 |
| Publication date | Mar 31, 2015 |
| Grant date | Mar 31, 2015 |
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A combustion device ( 1 ) for a gas turbine includes portions ( 12 ) having an inner and an outer wall ( 13, 14 ) with an interposed noise absorption plate ( 15 ) having a plurality of holes ( 16 ). The combustion device ( 1 ) further has first passages ( 17 ) connecting zones between the inner wall ( 13 ) and the plate ( 15 ) to the inside of the combustion device ( 1 ) and second passages ( 21 ) for cooling the inner wall ( 13 ). The portions ( 12 ) also have an inner layer ( 22 ) between the inner wall ( 13 ) and the plate ( 15 ) defining inner chambers ( 23 ), each connected to at least a first passage ( 17 ), and an outer layer ( 24 ) between the outer wall ( 14 ) and the plate ( 15 ) defining outer chambers ( 25 ) connected to the inner chambers ( 23 ) via the holes ( 16 ) of the plate ( 15 ).
Opening claim text (preview).
We claim: 1. A combustion device for a gas turbine comprising: a portion having an inner wall and an outer wall and an interposed noise absorption plate having a plurality of holes between the inner wall and the plate, a plurality of zones being between the inner wall and the plate, the inner wall delimiting an inside of the combustion device; first passages connecting the zones between the inner wall and the plate to the inside of the combustion device; an inner layer between…
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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