Seal segment for a gas turbine engine
First Claim
Patent Images
1. A gas turbine engine, comprising:
- a housing;
at least one compressor positioned within the housing;
at least one turbine operably coupled to the at least one compressor and including a plurality of blades extending radially from a longitudinal axis of the engine; and
a seal segment positioned along a portion of the housing and comprising;
a radially outer wall having a first length extending annularly around a portion of the engine, the radially outer wall including at least one elongate aperture extending along a width of the seal segment and defining a slot on and through the radially outer wall configured to receive a connector member;
a radially inner wall positioned intermediate the outer wall and the portion of the engine and having a second length, the radially outer wall comprised of ceramic matrix composite material;
a first lateral wall and a second lateral wall, extending between the outer wall and the inner wall;
a rib member integrally formed with and extending between the outer wall and the inner wall intermediate the first and second lateral walls without overlapping the at least one elongate aperture of the outer wall;
a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and
a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage.
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Abstract
A seal segment for a gas turbine engine has a radially outer wall with a first length, a radially inner wall with a second length, and a rib member which extends radially between the outer wall and the inner wall and along the first and second lengths.
25 Citations
21 Claims
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1. A gas turbine engine, comprising:
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a housing; at least one compressor positioned within the housing; at least one turbine operably coupled to the at least one compressor and including a plurality of blades extending radially from a longitudinal axis of the engine; and a seal segment positioned along a portion of the housing and comprising; a radially outer wall having a first length extending annularly around a portion of the engine, the radially outer wall including at least one elongate aperture extending along a width of the seal segment and defining a slot on and through the radially outer wall configured to receive a connector member; a radially inner wall positioned intermediate the outer wall and the portion of the engine and having a second length, the radially outer wall comprised of ceramic matrix composite material; a first lateral wall and a second lateral wall, extending between the outer wall and the inner wall; a rib member integrally formed with and extending between the outer wall and the inner wall intermediate the first and second lateral walls without overlapping the at least one elongate aperture of the outer wall; a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage. - View Dependent Claims (2, 3, 4, 5)
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6. A gas turbine engine, comprising:
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a housing; at least one compressor positioned within the housing; at least one turbine operably coupled to the at least one compressor and including a plurality of blades extending radially from a longitudinal axis of the engine; and a seal segment positioned along a portion of the housing and comprising; a radially outer wall including at least one elongate aperture extending along a width of the seal segment and defining a slot on and through the radially outer wall configured to receive a connector member; a radially inner wall positioned intermediate the outer wall and at least one of the at least one compressor and the at least one turbine, the radially outer wall comprised of ceramic matrix composite material; a first lateral wall extending between the outer and inner walls; a second lateral wall extending between the outer and inner walls; a rib member integrally formed with and extending between the outer wall and the inner wall and intermediate the first and second lateral walls without overlapping the at least one elongate aperture of the outer wall; a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage. - View Dependent Claims (7, 8, 9, 10, 11, 12)
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13. A gas turbine engine, comprising:
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a housing; at least one compressor positioned within the housing; at least one turbine operably coupled to the at least one compressor and including a plurality of blades extending radially from a longitudinal axis of the engine; and a seal segment positioned along a portion of the housing and comprising; a radially outer wall including at least one elongate aperture extending along a width of the seal segment and defining a slot on and through the radially outer wall configured to receive a connector member; a radially inner wall positioned intermediate the outer wall and the blades of the turbine, the radially outer wall comprised of ceramic matrix composite material; a first lateral wall extending between the outer and inner walls; a second lateral wall extending between the outer and inner walls; and a rib member integrally formed with and extending between the outer wall and the inner wall and intermediate the first and second walls without overlapping the at least one elongate aperture of the outer wall, wherein the outer wall, the inner wall, the rib member, and the first lateral wall define a first rectangular cross-section of the seal segment, and wherein the outer wall, the inner wall, the rib member, and the second lateral wall define a second rectangular cross-section of the seal segment. - View Dependent Claims (14, 15, 16, 17, 18, 19, 20, 21)
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Specification