Wall element for use in combustion apparatus
First Claim
1. A wall element connected with a gas turbine engine combustor wall that has an inner surface and an outer surface, the wall element and the inner surface defining a space therebetween, the wall element comprising deformable cooling pedestals extending into the space and which on contact with the inner surface deform against the inner surface of the combustor wall, wherein the wall element further comprises a body portion and elongate edge portions projecting from the body portion towards the inner surface of the combustor wall and wherein the deformable cooling pedestals are provided on the body portion which project in the same direction as and extend beyond the edge portions into the space.
1 Assignment
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Accused Products
Abstract
A tile for use as part of an inner wall of a gas turbine engine combustor, the tile being provided with deformable cooling pedestals extending into a space between the tile and the outer wall. The pedestals are deformed in contact with the outer wall of the combustor.
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Citations
10 Claims
- 1. A wall element connected with a gas turbine engine combustor wall that has an inner surface and an outer surface, the wall element and the inner surface defining a space therebetween, the wall element comprising deformable cooling pedestals extending into the space and which on contact with the inner surface deform against the inner surface of the combustor wall, wherein the wall element further comprises a body portion and elongate edge portions projecting from the body portion towards the inner surface of the combustor wall and wherein the deformable cooling pedestals are provided on the body portion which project in the same direction as and extend beyond the edge portions into the space.
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9. A gas turbine combustor wall structure comprising:
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a combustor wall; and a plurality of discrete tiles attached to the combustor wall on the combustion side, there being a space formed between each discrete tile and the combustor wall; each of the discrete tiles provided with deformable cooling pedestals extending into the space; the cooling pedestals deforming laterally when contacting the combustor wall, wherein discrete tile edges overlap.
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10. A gas turbine engine combustion chamber comprising:
a combustor wall with discrete tiles attached to an inner surface of the combustor wall, the discrete tiles and the inner surface defining a space therebetween, the discrete tiles provided with deformable cooling pedestals extending into the space and which on contact with the inner surface of the combustor wall deform against the inner surface.
Specification