Composite slider seal for turbojet penetration
AssigneeUnited Technologies Corporation
InventorsJonathan Jeffery Eastwood, Judith F. Brooks
Life of this patent
Estimating the term…
Abstract
A seal assembly for a turbo machine, such as a turbo jet, includes a housing having a retainer secured relative to the housing. A seal is arranged between the housing and the retainer. The seal provides an opening configured to receive a penetrating element. The seal comprises a composite material. In one example, an anti-rotation feature prevents the seal from rotating relative to the housing. The anti-rotation feature includes a rivet received in a hole in the seal that cooperates with at least one of the housing and the retainer to maintain the seal in a desired angular position.
Claims12
A seal assembly for a turbo machine comprising:
- a housing;
- a retainer secured relative to the housing;
- a seal arranged between the housing and retainer, the seal providing an opening configured to receive a penetrating element, the seal comprising a composite material, wherein the opening includes a surface having a portion that is at an non-perpendicular angle relative to generally parallel opposing sides of the seal;
- and
- an anti-rotation feature cooperates with at least one of the housing and retainer to maintain an angular position of the seal relative to the housing.
A seal for a gas turbine engine penetration seal assembly comprising:
- a composite structure including carbon fiber fabric layers laminated with a resin, and an opening configured to receive a penetrating element, the composite structure includes generally parallel spaced apart sides and a generally circular perimeter, the opening centrally located within the perimeter, and the composite structure includes a hole spaced from the opening.
A gas turbine engine comprising:
- a core;
- a duct surrounding the core and having an aperture;
- a housing secured to the duct around the aperture;
- a seal supported by the housing and including an opening, the seal comprising a composite material;
- a penetrating element extending through the opening and supported by the core;
- a retainer secured relative to the housing, wherein the opening includes a surface having a portion that is at an non-perpendicular angle relative to generally parallel opposing sides of the seal;
- and
- an anti-rotation feature cooperating with at least one of the housing and retainer to maintain an angular position of the seal relative to the housing.
A gas turbine engine comprising:
- a core;
- a duct surrounding the core and having an aperture;
- a housing secured to the duct around the aperture;
- a seal supported by the housing and including an opening, the seal comprising a composite material;
- a penetrating element extending through the opening and supported by the core
- an anti-rotation feature cooperating with at least one of the housing and retainer to maintain an angular position of the seal relative to the housing, the anti-rotation feature includes a hole in the seal;
- and
- a rivet arranged in the hole cooperating with the at least one of the housing and the retainer, the rivet includes a plastically deformed end received in the slot, the rivet includes a head on one side of the seal, and a washer is arranged between an opposite side of the seal and the plastically deformed end, the seal clamped between the washer and the head.
Dependencies are inferred from the claim text.