Seal assembly for gas turbine engine
AssigneeUnited Technologies Corporation
InventorsKevin L. Rugg, Winston Gregory Smiddy
Life of this patent
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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 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 engagement portion 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 an elongated opening to the internal cavity. A method of sealing is also disclosed.
Claims20
A seal assembly for a gas turbine engine comprising:
- a seal including a sealing portion that extends from an engagement portion;
- wherein the sealing portion includes a seal face that extends circumferentially between first and second mate faces;
- and
- wherein the engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion includes an impingement face opposite the seal face that defines an elongated opening to the internal cavity.
A gas turbine engine comprising:
- 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;
- and
- wherein the seal body defines an internal cavity that extends circumferentially between opposed mate faces and defines an elongated opening to the internal cavity along the impingement face.
A method of sealing of a gas turbine engine, comprising:
- securing a mounting block to an engine static structure such that the mounting block is positioned between mate faces of adjacent blade outer air seals;
- wherein each of the adjacent seals comprises:
- an elongated seal body including a seal face that bounds a gas path and an opposed impingement face;
- and
- wherein the seal body defines an internal cavity that extends circumferentially from a respective one of the mate faces, and an elongated opening to the internal cavity that is defined in the impingement face;
- and
- ejecting cooling flow from a plurality of cooling passages towards the impingement face.
Dependencies are inferred from the claim text.