Siemens Energy, Inc.

Siemens Aktiengesellschaft

Brian Harry Terpos

Ching-Pang Lee

Kok-Mun Tham

Kevin Michael Light

Robert Watson Spitzer

Dustan M Simko

David James Wiebe

Yevgeniy P Shteyman

James S Marshall

Robert T Brooks

Abdullatif M Chehab

Jonathan M Leagon

Zhengxiang Pu

Scott W Smith

Brian Micklos

Christopher Scogin

Scott T Waechter

Dan Guinan

A thermal management arrangement () in a gas turbine engine (), including: a conduit-arrangement () providing fluid communication between a compressor section () and: a relatively thermally responsive portion () of a turbine vane carrier (); and a relatively thermally unresponsive portion () of a first turbine vane carrier. The conduit-arrangement includes: a general cooling flow outlet () disposed proximate the relatively thermally responsive portion of the turbine vane carrier and configured to discharge a general cooling flow (); and an impingement flow outlet () disposed proximate the relatively thermally unresponsive portion and configured to discharge an impingement flow (). The thermal management arrangement is configured such that a flow rate of the impingement flow is effective to accelerate a thermal response of the relatively thermally unresponsive portion toward a thermal response of the relatively thermally responsive portion.

Vane carrier thermal management arrangement and method for clearance control

An air injection system for use in a gas turbine engine includes at least one outlet port through which air is extracted from the engine only during less than full load operation, at least one rotor cooling pipe, which is used to inject the air extracted from the outlet port(s) into a rotor chamber, a piping system that provides fluid communication between the one outlet port(s) and the rotor cooling pipe(s), a blower system for extracting air from the engine through the outlet port(s) and for conveying the extracted air through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent air from passing through the piping system, and open during less than full load engine operation to allow air to pass through the piping system.

Air injection system in a gas turbine engine

A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.

Exhaust manifold flange connection

An inner mounting ring () for gas turbine flow path components such as shroud ring segments (). The inner ring () may be mounted to an outer ring () on radially slidable mounts () that maintain the two rings () in coaxial relationship, but allows them to thermally expand at different rates. This allows matching of the radial expansion rate of the inner ring () to that of the turbine blade tips (), thus providing reduced clearance () between the turbine blade tips () and the inner surface of the shroud ring segments () under all engine operating conditions. The inner ring () may be made of a material with a lower coefficient of thermal expansion than that of the outer ring ().

Inner ring with independent thermal expansion for mounting gas turbine flow path components

Aspects of the invention are directed to an interface between an exhaust cylinder and an exhaust diffuser in a turbine engine. The interface allows relative radial movement of the exhaust diffuser and the exhaust cylinder. According to aspects of the invention, the diffuser and the cylinder are operatively connected about their peripheries by a plurality of connecting members, which can be tie rods. Each connecting member can be pivotally connected at a first end to a joint bolt affixed to the exhaust cylinder and at a second end to an exhaust diffuser. Thus, the connecting members can join the cylinder and the diffuser in the axial direction, while allowing for the differential thermal expansion of the two components. Relative circumferential movement between the cylinder and the diffuser can be reduced by positioning neighboring connecting members at opposing angles in relation to one another.

Radially expanding turbine engine exhaust cylinder interface

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Oviedo, FL, United States of America

Brian Harry Terpos