Siemens Energy, Inc.

Daniel J Pierce

Richard Colin Charron

Jay Alan Morrison

Ching-Pang Lee

Matthew D Montgomery

Raymond Scott Nordlund

Walter Marussich

Kenneth K Landis

Jody W Wilson

Ernie B Campbell

A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced.

Combustor transition duct assembly with inner liner

A shaft cover support for a gas turbine engine is disclosed. The shaft cover support not only provides enhanced support to a shaft cover of the gas turbine engine, but also includes a cooling fluid chamber for passing fluids from a rotor air cooling supply conduit to an inner ring cooling manifold. Furthermore, the shaft cover support may include a cooling shield supply extending from the cooling fluid chamber between the radially outward inlet and the radially inward outlet on the radially extending region and in fluid communication with the cooling fluid chamber for providing cooling fluids to a transition section. The shaft cover support may also provide additional stiffness and reduce interference of the flow from the compressor. In addition, the shaft cover support accommodates a transition section extending between compressor and turbine sections of the gas turbine engine.

Structural cooling fluid tube for supporting a turbine component and supplying cooling fluid to transition section

A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.

Turbine transition component formed from an air-cooled multi-layer outer panel for use in a gas turbine engine

A shaft cover support for a gas turbine engine is disclosed. The shaft cover support not only provides enhanced support to a shaft cover of the gas turbine engine, but also includes a cooling fluid chamber for passing fluids from a rotor air cooling supply conduit to an inner ring cooling manifold. As such, the shaft cover support accomplishes in a single component what was only partially accomplished in two components in conventional configurations. The shaft cover support may also provide additional stiffness and reduce interference of the flow from the compressor. In addition, the shaft cover support accommodates a transition section extending between compressor and turbine sections of the engine. The shaft cover support has a radially extending region that is offset from the inlet and outlet that enables the shaft cover support to surround the transition, thereby reducing the overall length of this section of the engine.

Structural cooling fluid tube for supporting a turbine component and supplying cooling fluid

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.

Growing community of inventors

Waxhaw, NC, United States of America

Daniel J Pierce