United Technologies Corporation

David F Cloud

Peter M Munsell

Brian Ellis Clouse

Cheng-Zhang Wang

Donna Clough

Jorn Axel Glahn

Eric W Malmborg

David P Houston

Clifton J Crawley, Jr

Thomas G Phillips

Joseph W Bridges, Jr

Robert Newman

Michelle Diana Stearns

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. A retention flange extends from the leading edge portion and a leaf seal contacts the retention flange.

Blade outer air seal with secondary air sealing

A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90&#xb0;. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.

Customer bleed air pressure loss reduction

A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

Engine mid-turbine frame transfer tube for low pressure turbine case cooling

A blade outer air seal (BOAS) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion.

Blade outer air seal having shiplap structure

A seal assembly for a gas turbine engine includes an annular body and a flow-through tube that extends through the annular body. The flow-through tube includes an upstream orifice, a downstream orifice and a tube body that extends between the upstream orifice and the downstream orifice. The tube body establishes a gradually increasing cross-sectional area between the downstream orifice and the upstream orifice.

Growing community of inventors

Simsbury, CT, United States of America

David F Cloud