Abstract: 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—potentially comprising thousands or even hundreds of thousands of perforations spatially distributed on a miniaturized scale—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.

Abstract: Injector assemblies (12) and ducting arrangement (20) including such injector assemblies are provided. The injector assembly may include a reactant-guiding structure (16) arranged to convey a flow of reactants (19) into the combustion stage and means for injecting (24, 25, 26) a flow of air (22) 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 (21), as the flow of reactants is admitted into the combustion stage.

Abstract: 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.

Abstract: A combustion system in a combustion turbine engine is provided. The system may include a combustor wall fluidly coupled to receive a cross-flow of combustion products. The combustor wall may include a plurality of cooling air conduits. An injector assembly may be in fluid communication with the cooling fluid conduits to receive cooling fluid that passes through the cooling fluid conduits. Injector assembly includes means for injecting a flow of the cooling fluid into the combustion stage. The flow of the cooling fluid may be arranged to condition interaction of a flow of reactants injected to admix with the cross-flow of combustion products.

Abstract: Injector assemblies (12) and ducting arrangement (20) including such injector assemblies are provided. The injector assembly may include a reactant-guiding structure (16) arranged to convey a flow of reactants (19) into the combustion stage and means for injecting (24, 25, 26) a flow of air (22) 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 (21), as the flow of reactants is admitted into the combustion stage.

Abstract: A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) 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 (24) 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.

Abstract: Method and computer-readable model for additively manufacturing a ducting arrangement (10) for a gas turbine engine are provided. Ducting arrangement (10) may include a duct (18) to be fluidly coupled to receive a cross-flow of combustion gases from a main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) 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.

Abstract: An improved combustion system in a combustion turbine engine is provided. The combustor system may include an injector assembly disposed in a combustion stage disposed downstream from a main combustion stage of the combustor system. The injector assembly may include a reactant-guiding structure arranged to deliver to the combustion stage respective jets of reactants through an array of ejection orifices disposed on one or more side walls of the reactant-guiding structure. The reactant-guiding structure may be configured to form a stream-lined body relative to a flow of a fluid to be mixed with the jets of reactants delivered to the combustion stage. The ejection orifices of the array may be aerodynamically-shaped to define a respective stream-lined orifice cross-section, (e.g., airfoil shaped).

Abstract: Method and computer-readable model for additively manufacturing a ducting arrangement (20) in a combustion stage are provided. The ducting arrangement may include a combustor wall (40) in a combustion stage fluidly coupled to receive a cross-flow of combustion products (21). An injector assembly (12) may be in fluid communication with cooling fluid conduits (46) in the combustor wall to receive cooling fluid that passes through the cooling fluid conduits. The injector assembly may include means for injecting (24, 25, 26) a flow of the cooling fluid (22) arranged to condition interaction of a flow of reactants (19) 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.

Abstract: Method and computer-readable model for additively manufacturing a ducting arrangement (20) in a combustion stage are provided. The ducting arrangement may include a combustor wall (40) in a combustion stage fluidly coupled to receive a cross-flow of combustion products (21). An injector assembly (12) may be in fluid communication with cooling fluid conduits (46) in the combustor wall to receive cooling fluid that passes through the cooling fluid conduits. The injector assembly may include means for injecting (24, 25, 26) a flow of the cooling fluid (22) arranged to condition interaction of a flow of reactants (19) 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.

Abstract: Method and computer-readable model for additively manufacturing a ducting arrangement (10) for a gas turbine engine are provided. Ducting arrangement (10) may include a duct (18) to be fluidly coupled to receive a cross-flow of combustion gases from a main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) 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.

Abstract: A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) 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 (24) 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.

Abstract: Injector assembly and ducting arrangement including such assemblies for a combustor system in a gas turbine engine are provided. A reactant-guiding structure (42) may be configured to define a curvilinear flow path (47) to route a flow of reactants from a first flow direction (50) to a second flow direction (52) toward a cross-flow of combustion gases (60). A cross-flow guiding structure (54) may further define a flow path (58) to route a portion of the cross-flow of combustion gases toward an outlet side of the cross-flow guiding structure. Disclosed injector assemblies can be configured to reduce pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective injector assemblies 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) technology.

Abstract: Method and computer-readable model for additively manufacturing an injector assembly or a ducting arrangement including such assembles, as may be used in a combustion system of a gas turbine engine. The injector assembly may include a reactant-guiding structure (42) that may be configured to define a curvilinear flow path (47) to route a flow of reactants from a first flow direction (50) to a second flow direction (52) toward a cross-flow of combustion gases (60). A cross-flow guiding structure (54) may further define a flow path (58) to route a portion of the cross-flow of combustion gases toward an outlet side of the cross-flow guiding structure. Disclosed injector assemblies can be configured to reduce pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow.

Abstract: Method and computer-readable model for additively manufacturing a ducting arrangement in a combustion system of a gas turbine engine are provided. The ducting arrangement may be formed by duct segments (32) circumferentially adjoined with one another to form a flow duct structure (e.g., a flow-accelerating structure (34)) and a pre-mixing structure (35). The flow duct structure may be fluidly coupled to pass a cross-flow of combustion gases. The pre-mixing structure (35) may include an array of pre-mixing tubes (48) fluidly coupled to receive air and fuel conveyed by a manifold (42) to inject a mixture of air and fuel into the cross-flow of combustion gases that passes through the flow duct structure. The duct segments 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) technology.

Abstract: A ducting arrangement (30) in a combustion system of a gas turbine engine is provided. The ducting arrangement may be formed by duct segments (32) circumferentially adjoined with one another to form a flow duct structure (e.g., a flow-accelerating structure (34)) and a pre-mixing structure (35). The flow duct structure is fluidly coupled to pass a cross-flow of combustion gases. The pre-mixing structure (35) may include an array of pre-mixing tubes (48) fluidly coupled to receive air and fuel conveyed by a manifold (42) to inject a mixture of air and fuel into the cross-flow of combustion gases that passes through the flow duct structure. The duct segments 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) technology.