Siemens Energy, Inc.

Siemens Westinghouse Power Corporation

Siemens Power Generation, Inc.

Chris Campbell

Ramesh Subramanian

Andrew Jeremiah Burns

Jay Alan Morrison

Gary Brian Merrill

Yevgeniy P Shteyman

Jay Edgar Lane

Harry A Albrecht

Daniel George Thompson

A combustion catalyst coating () applied to the surface of a ceramic thermal barrier coating () which is supported by a metal substrate (). The microstructure of the thermal barrier coating surface provides the necessary turbulent flow and surface area for interaction of the catalyst and a fuel-air mixture in a catalytic combustor of a gas turbine engine. The temperature gradient developed across the thermal barrier coating protects the underlying metal substrate from a high temperature combustion process occurring at the catalyst surface. The thermal barrier coating deposition process may be controlled to form a microstructure having at least one feature suitable to interdict a flow of fuel-air mixture and cause the flow to become more turbulent than if such feature did not exist.

Method of forming a catalyst element having a thermal barrier coating as the catalyst substrate

Catalyst element having a thermal barrier coating as the catalyst substrate

A hybrid vane ( ) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member ( ) bonded to a substantially solid core member ( ). The airfoil member and core member are cooled by a cooling fluid ( ) passing through cooling passages ( ) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond (( ) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation ( ) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.

Ceramic matrix composite gas turbine vane

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Orlando, FL, United States of America

Chris Campbell