Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Yuntao Chen

Walter Ray Laster

Juan Enrique Portillo Bilbao

Andrew J North

Joseph Meadows

Lucky Tran

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

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.

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Oviedo, FL, United States of America

Yuntao Chen