SEAL ASSEMBLY FOR GAS TURBINE ENGINE
First Claim
1. A seal assembly for a gas turbine engine comprising:
- a seal including a seal body having a sealing portion that extends from an engagement portion, the sealing portion including a seal face that extends circumferentially between first and second mate faces, the seal body defining an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion including an impingement face opposite the seal face that defines a plurality of apertures to the internal cavity; and
a housing mounted to the seal such that the impingement face is exposed to define a plenum between the housing and the impingement face, the housing defining a plurality of cooling passages, and each of the plurality of cooling passages defining a passage axis that is oriented such that a projection of the passage axis intersects the seal body.
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Accused Products
Abstract
A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body having a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The seal body defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines a plurality of apertures to the internal cavity. A housing is mounted to the seal such that the impingement face is exposed to define a plenum between the housing and the impingement face. The housing defines a plurality of cooling passages, and each of the plurality of cooling passages define a passage axis that is oriented such that a projection of the passage axis intersects the seal body. A method of sealing is also disclosed.
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Citations
20 Claims
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1. A seal assembly for a gas turbine engine comprising:
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a seal including a seal body having a sealing portion that extends from an engagement portion, the sealing portion including a seal face that extends circumferentially between first and second mate faces, the seal body defining an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion including an impingement face opposite the seal face that defines a plurality of apertures to the internal cavity; and a housing mounted to the seal such that the impingement face is exposed to define a plenum between the housing and the impingement face, the housing defining a plurality of cooling passages, and each of the plurality of cooling passages defining a passage axis that is oriented such that a projection of the passage axis intersects the seal body. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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14. A gas turbine engine comprising:
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an engine case extending along an engine axis; an array of blades rotatable about the engine axis; and an array of blade outer air seals distributed about the array of blades to bound a core flow path, wherein each of the seals comprises; an elongated seal body including a seal face that faces toward the core flow path and an opposed impingement face; wherein the seal body defines an internal cavity that extends circumferentially between opposed mate faces, and the seal body defines a plurality of apertures to the internal cavity along the impingement face; and wherein the seal is mounted to the engine case such that the impingement face is exposed; wherein the engine case defines a plurality of cooling passages spaced apart from the impingement face, and each of the plurality of cooling passages defines a passage axis that is oriented such that a projection of the passage axis intersects the seal body of a respective one of the seals. - View Dependent Claims (15, 16)
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17. A method of sealing of a gas turbine engine, comprising:
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securing a mounting block to an engine static structure such that the mounting block is positioned along an intersegment gap between mate faces of adjacent blade outer air seals; wherein each of the adjacent blade outer air seals comprises; an elongated seal body including a seal face that faces toward a gas path and an opposed impingement face; and wherein the seal body defines an internal cavity that extends circumferentially between opposed mate faces and defines a plurality of apertures to the internal cavity along the impingement face; wherein the engine static structure defines a plurality of cooling passages, and each of the plurality of cooling passages defines a passage axis that is oriented such that a projection of the passage axis intersects the seal body of a respective one of the adjacent seals; and ejecting cooling flow from the plurality of cooling passages such that the cooling flow impinges on surfaces of the seal body. - View Dependent Claims (18, 19, 20)
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Specification