Fuel nozzle assembly for a gas turbine engine
US-9200571-B2 · Dec 1, 2015 · US
US9021815B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9021815-B2 |
| Application number | US-201113015910-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jan 28, 2011 |
| Priority date | Feb 4, 2010 |
| Publication date | May 5, 2015 |
| Grant date | May 5, 2015 |
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The combustion device ( 1 ) of a gas turbine includes burners ( 2 ) connected to a front plate ( 5 ) of a combustion chamber ( 3 ). The front plate ( 5 ) has, spaced apart from one another, a front sheet ( 8 ) and an impingement sheet ( 7 ) with aligned holes ( 11, 12 ) housing the burners ( 2 ). A piston ring ( 15 ) is provided between the front sheet ( 8 ) and impingement sheet ( 7 ) to seal the holes ( 11, 12 ). The axial length of the border of the hole ( 11, 12 ) of the front sheet ( 8 ) and/or impingement sheet ( 7 ) is longer than the thickness of the corresponding front sheet ( 8 ) and/or impingement sheet ( 7 ).
Opening claim text (preview).
We claim: 1. A gas turbine combustion device comprising: a combustion chamber including a front plate; and at least one burner connected to the front plate; wherein the front plate comprises, spaced apart from one another, a front sheet and an impingement sheet, the front sheet and the impingement sheet including aligned holes receiving the at least one burner, and a piston ring between the front sheet and the impingement sheet to seal the holes; wherein an axial length of a…
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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