United Technologies Corporation

Siemens Aktiengesellschaft

Thomas F Pechette

Ching-Pang Lee

Andrew R Narcus

Darryl S Eng

Jae Y Um

Christopher K Rawlings

Keith S Brewer

Friedrich T Rogers

A shroud cooling system configured to cool a shroud adjacent to an airfoil within a gas turbine engine is disclosed. The turbine engine shroud may be formed from shroud segments that include a plurality of cooling air supply channels extending through a forward shroud support for impingement of cooling air onto an outer radial surface of the shroud segment with respect to the inner turbine section of the turbine engine. The channels may extend at various angles to increase cooling efficiency. The backside surface may also include various cooling enhancement components configured to assist in directing, dispersing, concentrating, or distributing cooling air impinged thereon from the channels to provide enhanced cooling at the backside surface. The shroud cooling system may be used to slow down the thermal response by isolating a turbine vane carrier from the cooling fluids while still providing efficient cooling to the shroud.

Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines

A liner for a gas turbine engine is provided that includes a first liner section and a second liner section. The first liner section includes a first flange having a first contact surface. The second liner section includes a second flange having a second contact surface and a plurality of apertures. The first and second flanges axially overlap one another, and in a circumferential liner the second flange is disposed radially outside of the first flange. A channel is formed by the two liner sections that is open to the core gas path. In a first position, the first flange axially overlaps the second flange by a first distance and the apertures are misaligned with the first flange and disposed within the channel. Cooling air entering apertures within the second flange subsequently passes into the channel. In a second position, the first flange axially overlaps the second flange by a second distance. The second distance is greater than the first distance and in the second position the apertures in the second flange are substantially aligned with the first flange. Cooling air entering the second flanges apertures subsequently impinges on the first flange.

Gas turbine engine liner

Juxtaposed recirculation zones for the pilot in the burner of an augmentor for a gas turbine engine is created by fabricating the engine's tail cone in two components and including an annular gap defined between the juncture of both components that injects a stream of cooling air radially into the augmentor's gas path for eliminating or minimizing screeching in the augmentor.

Recirculating zone inducing means for an augmentor burning section

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Palm Beach Gardens, FL, United States of America

Thomas F Pechette