Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Siemens Aktiengesellschaft

Andrew J North

Walter Ray Laster

Juan Enrique Portillo Bilbao

Yuntao Chen

Timothy A Fox

Joseph Meadows

Lucky Tran

Juan Enrique Portilllo Bilbao

A finely distributed combustion system for a gas turbine engine is provided. A combustor body may extend along a longitudinal axis. A premixer space may be formed within the combustor body to premix air and fuel. The premixer space is in communication with an array of finely distributed perforations arranged in a wall of the combustor body to eject an array of premixed main flamelets throughout a contour of the combustor body between the upstream base of the combustor body and the downstream base of the combustor body. The array of finely distributed perforations&#x2014;potentially comprising thousands or even hundreds of thousands of perforations spatially distributed on a miniaturized scale&#x2014;for ejecting the premixed main flamelets is technically advantageous compared to conventional distributed combustion systems, where injection of relatively longer main flames occurs just at a few discrete axial locations.

Finely distributed combustion system for a gas turbine engine

Injector assemblies () and ducting arrangement () including such injector assemblies are provided. The injector assembly may include a reactant-guiding structure () arranged to convey a flow of reactants () into the combustion stage and means for injecting () a flow of air () into the combustion stage. The flow of air injected into the combustion stage may be arranged to condition interaction of the flow of reactants injected into the combustion stage with a cross-flow of combustion products (), as the flow of reactants is admitted into the combustion stage.

Ducting arrangement with injector assemblies configured to form a shielding flow of air injected into a combustion stage in a gas turbine engine

A ducting arrangement () in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct () is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct () includes a duct segment () with an expanding cross-sectional area () where one or more injector assemblies () are disposed. Injector assembly () includes one or more reactant-guiding structures () arranged to deliver a flow of reactants into the downstream combustion stage to be mixed with the cross-flow of combustion gases. Disclosed injector assemblies are arranged in expanding cross-sectional area () to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.

Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine

Method and computer-readable model for additively manufacturing a ducting arrangement () for a gas turbine engine are provided. Ducting arrangement () may include a duct () to be fluidly coupled to receive a cross-flow of combustion gases from a main combustion stage. Duct () includes a duct segment () with an expanding cross-sectional area () where one or more injector assemblies () are disposed. Injector assembly () includes one or more reactant-guiding structures () arranged to deliver a flow of reactants to be mixed with the cross-flow of combustion gases. The ducting arrangement is effective to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.

Method and computer-readable model for additively manufacturing ducting arrangement for a gas turbine engine

Method and computer-readable model for additively manufacturing a ducting arrangement () in a combustion stage are provided. The ducting arrangement may include a combustor wall () in a combustion stage fluidly coupled to receive a cross-flow of combustion products (). An injector assembly () may be in fluid communication with cooling fluid conduits () in the combustor wall to receive cooling fluid that passes through the cooling fluid conduits. The injector assembly may include means for injecting () a flow of the cooling fluid () arranged to condition interaction of a flow of reactants () injected with the cross-flow of combustion products. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.

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Orlando, FL, United States of America

Andrew J North