Siemens Aktiengesellschaft

Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Ernie B Campbell

Jay Alan Morrison

Kok-Mun Tham

Richard Colin Charron

Matthew D Montgomery

Todd A Ebert

Kevin Michael Light

Raymond Scott Nordlund

Jody W Wilson

Yan Yin

Robert W Sunshine

Daniel J Pierce

A cooling system configured to cool aspects of the turbine engine between a compressor and a turbine assembly is disclosed. In at least one embodiment, the cooling system may include one or more mid-frame cooling channels extending from an inlet through one or more mid-frame torque discs positioned downstream of the compressor and upstream of the turbine assembly. The inlet may be positioned to receive compressor bleed air. The mid-frame cooling channel may be positioned in a radially outer portion of the mid-frame torque disc to provide cooling to outer aspects of the mid-frame torque disc such that conventional, low cost materials may be used to form the mid-frame torque disc rather than high cost materials with capacity to withstand higher temperatures. The cooling fluid routed through the mid-frame cooling channel in the mid-frame torque disc may be exhausted into a cooling system () for the downstream turbine assembly.

Compressor bleed cooling system for mid-frame torque discs downstream from a compressor assembly in a gas turbine engine

An arrangement () for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement () including a plurality of interconnected integrated exit piece (IEP) sections () defining an annular chamber () oriented concentric to a gas turbine engine longitudinal axis () upstream of the turbine first stage blade section. Each respective IEP () includes a first flow path section () receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis () there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (). Each respective IEP further includes a second flow path section () receiving a partially bounded second flow from an upstream adjacent IEP () and delivering at least part of the second flow to the turbine first stage blade section.

Assembly for directing combustion gas

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Orlando, FL, United States of America

Ernie B Campbell