United Technologies Corporation

Raytheon Technologies Corporation

Judith F Brooks

William K Ackermann

Jonathan Jeffery Eastwood

Jonathan Lemoine

Ryan K Snyder

Brian Duguay

Michael S Stevens

Steven J Bauer

Darren M Smith

Christine F McGinnis

Pellegrino J Pisacreta

James P Chasse

Stephanie Ernst

Tomasz Pelic

Major D Jones

Jonathan Jeffrey Eastwood

A case assembly for a gas turbine engine, includes a case with a case boss, said case boss including a peripheral wall that defines a first inner diameter in a first condition to receive a piston seal, and a second inner diameter in a second condition, the second condition including enlargement of the first inner diameter to form a second inner diameter and a bushing mounted within the second inner diameter, an inner diameter of the bushing defines a bushing inner diameter about equivalent to the first inner diameter to receive the piston seal.

Sealing interface for a case of a gas turbine engine

A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.

Support ring with thermal heat shield for case flange

A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.

Fitting for mid-turbine frame of gas turbine engine

A seal assembly for a fan duct metering valve disposed within a casing of a gas turbine engine includes a tab for extending through an opening in the casing and attaching to the valve, a carrier for extending into the opening and engaging the valve such that fluid does not leak between the valve and the carrier.

Fan duct blocker actuation tab seal

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.

Composite slider seal for turbojet penetration

Growing community of inventors

Palo Alto, CA, United States of America

Judith F Brooks