Siemens Energy Global Gmbh & Co. Kg

Siemens Aktiengesellschaft

Daniel Cassar

Wojciech Dyszkiewicz

Ramesh Subramanian

Clifford E Johnson

Domenico Gambacorta

Rajesh Rajaram

Sachin Terdalkar

Manish Kumar

John M Crane

Lieke Wang

Michael Walker

A hybrid three-layer system is presented. The hybrid three-layer system includes a two-layer composite system and an additively manufactured third layer comprising a lattice structure. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features. The lattice structure is in contact with a surface of the metallic substrate of the composite layer system.

High temperature capable additively manufactured turbine component design

A system effective for dual utilization of cooling fluid in a gas turbine engine is provided. A cooling annulus is subject to a hot-temperature combustion flow received from a combustor basket and includes a liner including a feed channel to receive cooling fluid. A feed manifold is in fluid communication with feed channel to feed cooling fluid to a plurality of conduits in fluid communication with a plurality of exit orifices that is in fluid communication with a plurality of resonators. A distributor manifold includes a plurality of manifold sectors in fluid communication with a plurality of conduits arranged to convey cooling fluid. Some of the plurality of resonators operates with different amounts of cooling fluid. A group of the plurality of exit orifices is configured to supply an amount of cooling fluid appropriate for a resonator in fluid communication with the group of the plurality of exit orifices.

System with conduit arrangement for dual utilization of cooling fluid in a combustor section of a gas turbine engine

A gas turbine engine has a resonator ring that is formed by two circumferentially extending rings. The first and second circumferentially extending rings have located within them baffles. Both the first ring and the second ring are able to mitigate acoustic frequencies generated by the gas turbine engine.

Gas turbine engine with resonator rings

A gas engine turbine has a transition duct () that has improved cooling features and a method for forming the cooling features. A continuous exit section cooling channel () is formed through the transition duct panel (), the exit frame () and the connection (). The continuous exit section cooling channel () reduces the need for effusion channels in the transition duct. The continuous exit section cooling channel () further reduces costs and improves the emissions associated with the transition duct () of the gas engine turbine.

Cooling features for a gas turbine engine transition duct

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Charlotte, NC, United States of America

Daniel Cassar