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US 2021/0325043 A1Published application
Gas turbine engine combustor with ceramic matrix composite liner
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsTed J. Freeman, Aaron D. Sippel
Life of this patent
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Abstract
A combustor adapted for use in a gas turbine engine includes a combustor shell comprising metallic materials. The combustor shell is formed to define an internal space. The combustor further includes a heat shield mounted to an axially aft surface of the combustor shell within the internal space and a combustor liner arranged to extend along inner surfaces of the combustor shell within the internal space. The combustor liner cooperates with the heat shield to define a combustor chamber.
Claims20
A combustor for use in a gas turbine engine, the combustor comprising
- a combustor shell comprising metallic materials, the combustor shell formed to define an internal space, the combustor shell including an inner annular wall that extends circumferentially around an axis, an outer annular wall that extends circumferentially around the axis and the inner annular wall to provide an internal space radially between the inner annular wall and the outer annular wall, and a dome panel that extends circumferentially around the axis and radially between an axially-forward end of the inner annular wall and an axially-forward end of the outer annular wall,
- a plurality of heat shields comprising ceramic matrix composite materials, each heat shield being mounted to an axially aft surface of the dome panel and arranged to extend partway around the axis, and
- a combustor liner arranged to extend along inner surfaces of the combustor shell within the internal space and to cooperate with the heat shield to define a combustor chamber, the combustor liner comprising ceramic matrix composite materials and including a plurality of outer liner tiles each arranged to extend only partway around the axis and axially away from the heat shield along the outer annular wall and a plurality of inner liner tiles each arranged to extend only partway around the axis and axially away from the heat shield along the inner annular wall,
- wherein one of the inner liner tile and the outer liner tile is formed integrally with the heat shield such that an axially-forward end of the one of the inner liner tile and the outer liner tile is supported only by the heat shield relative to the combustor shell within the internal space and to block flow of gases between the heat shield and the one of the inner liner tile and the outer liner tile without a seal therebetween.
1 more element
A combustor for use in a gas turbine engine, the combustor comprising
- a combustor shell comprising metallic materials, the combustor shell formed to define an internal space,
- a heat shield comprising ceramic matrix composite materials, the heat shield being mounted to an axially aft surface of the combustor shell within the internal space, and
- a combustor liner arranged to extend along inner surfaces of the combustor shell within the internal space and to cooperate with the heat shield to define a combustor chamber, the combustor liner comprising ceramic matrix composite materials and including an outer liner tile arranged to extend axially away from the heat shield and an inner liner tile arranged to extend axially away from the heat shield and spaced radially inward from the outer liner tile,
- wherein one of the inner liner tile and the outer liner tile is formed integrally with the heat shield such that an axially-forward end of the one of the inner liner tile and the outer liner tile is supported only by the heat shield relative to the combustor shell within the internal space.
1 more element
A method of manufacturing a combustor liner and a heat shield for a gas turbine engine, the method comprising
- providing a ceramic matrix composite preform comprising a plurality of ceramic matrix composite fibers, the preform having a rectangular portion and a plurality of protrusions that extend outwardly from the rectangular portion,
- infiltrating the ceramic matrix composite preform with ceramic matrix material to densify the ceramic matrix composite preform,
- molding the ceramic matrix composite preform by folding the rectangular portion in a first direction to provide a heat-shield preform and a tile preform and by folding each of the protrusions in a second direction away from the tile preform, and
- solidifying the ceramic matrix composite preform to provide the combustor liner and the heat shield integral with the combustor liner.
1 more element
Dependencies are inferred from the claim text.