Abstract: An improved fastener comprising a fastener body orientated about a central axis and having a tool-engaging portion, a threaded fastening portion and a shroud-receiving portion; a shroud concentrically mounted in the shroud-receiving portion to rotate relative to the fastener body under an applied external torque and having an outwardly extending annular shoulder; the shroud-receiving portion comprising an inwardly deformed stop radially overlapping the outwardly extending annular shoulder of the shroud; and the deformed stop of the shroud-receiving portion and the annular shoulder of the shroud forming a shroud-retaining element restraining the shroud from movement in at least a first axial direction along the central axis.

Abstract: A gas turbine engine has a converging duct that has combustion products flow at low mach speeds through a first portion and a high mach speeds through a second portion. The converging duct has two types of cooling schemes formed. One type of cooling scheme is beneficial for the low mach speed combustion product flow and one type of cooling scheme is beneficial for the high mach speed combustion product flow. The two cooling schemes are blended together in order increase the efficiency of the cooling of the converging duct.

Abstract: Method for constructing impingement/effusion cooling features in a component of a combustion turbine engine is provided. A pocket 102 may be arranged between an outer wall 104 and an inner wall 106 of the component. A lasing device 108 allows drilling through the component to form an effusion hole 110. The lasing device further allows welding closed an opening 117 formed at outer wall 104 of the component during the drilling with the lasing device through the component. Lasing device 108 further allows drilling through outer wall 104 of the component to form an impingement hole 118 for the impingement/effusion cooling feature. The proposed methodology in a multi-panel arrangement, for example, eliminates a need of having to pre-drill such holes in individual panels prior to the bonding and forming of the component, which overcomes various drawbacks commonly associated with such pre-drilling.

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 fuel injector for injecting alternate fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) may be fluidly coupled to a radial passage (22) in a plurality of vanes (20) that branches into passages (24) (e.g., axial passages) to inject a first fuel without jet in cross-flow injection. This may be effective to reduce flashback in fuels having a relatively high flame speed. A mixer (30) with lobes (32) for injection of a second fuel may be arranged at the downstream end of a fuel delivery tube (12). A fuel-routing structure (38) may be configured to route the second fuel within a respective lobe so that fuel injection of the second fuel takes place radially outwardly relative to a central region of the mixer. This may be conducive to an improved (e.g., a relatively more uniform) mixing of air and fuel.

Abstract: Method for constructing impingement/effusion cooling features in a component of a combustion turbine engine is provided. A pocket 102 may be arranged between an outer wall 104 and an inner wall 106 of the component. A lasing device 108 allows drilling through the component to form an effusion hole 110. The lasing device further allows welding closed an opening 117 formed at outer wall 104 of the component during the drilling with the lasing device through the component. Lasing device 108 further allows drilling through outer wall 104 of the component to form an impingement hole 118 for the impingement/effusion cooling feature. The proposed methodology in a multi-panel arrangement, for example, eliminates a need of having to pre-drill such holes in individual panels prior to the bonding and forming of the component, which overcomes various drawbacks commonly associated with such pre-drilling.

Abstract: An improved fastener comprising a fastener body orientated about a central axis and having a tool-engaging portion, a threaded fastening portion and a shroud-receiving portion; a shroud concentrically mounted in the shroud-receiving portion to rotate relative to the fastener body under an applied external torque and having an outwardly extending annular shoulder; the shroud-receiving portion comprising an inwardly deformed stop radially overlapping the outwardly extending annular shoulder of the shroud; and the deformed stop of the shroud-receiving portion and the annular shoulder of the shroud forming a shroud-retaining element restraining the shroud from movement in at least a first axial direction along the central axis.

Abstract: A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.

Abstract: An improved fastener comprising a fastener body orientated about a central axis and having a tool-engaging portion, a threaded fastening portion and a shroud-receiving portion; a shroud concentrically mounted in the shroud-receiving portion to rotate relative to the fastener body under an applied external torque and having an outwardly extending annular shoulder; the shroud-receiving portion comprising an inwardly deformed stop radially overlapping the outwardly extending annular shoulder of the shroud; and the deformed stop of the shroud-receiving portion and the annular shoulder of the shroud forming a shroud-retaining element restraining the shroud from movement in at least a first axial direction along the central axis.

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: A gas turbine engine has a converging duct that has combustion products flow at low mach speeds through a first portion and a high mach speeds through a second portion. The converging duct has two types of cooling schemes formed. One type of cooling scheme is beneficial for the low mach speed combustion product flow and one type of cooling scheme is beneficial for the high mach speed combustion product flow. The two cooling schemes are blended together in order increase the efficiency of the cooling of the converging duct.

Abstract: A process for producing a titanium load-bearing structure, which comprises cold-gas dynamic spraying of titanium particles on to a suitably shaped support member, and a titanium load bearing structure so-produced.

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: The present disclosure provides a gas turbine combustor liner (34) comprising an outer surface (38) and an inner surface (36), a plurality of film cooling holes (44) through a thickness of the gas turbine combustor liner (34), and a plurality of resonator boxes (32) affixed to the outer surface (38) of the gas turbine combustor liner (34). The film cooling holes (44) extend circumferentially around the gas turbine combustor liner (34) and comprise a first set of holes (56) having a first axial row spacing X and a second set of holes (58) having a second axial row spacing X?. The second set of holes (58) is formed in the gas turbine combustor liner (34) in a downstream direction relative to the first set of holes (56). The second axial row spacing X? is greater than the first axial row spacing X.

Abstract: A cooling system for a fuel system in a turbine engine that is usable to cool a fuel nozzle is disclosed. The cooling system may include one or more cooling system housings positioned around the fuel nozzle, such that the cooling system housing forms a cooling chamber defined at least partially by an inner surface of the cooling system housing and an outer surface of the fuel nozzle. The fuel nozzle may extend into a combustor chamber formed at least in part by a combustor housing. The fuel nozzle may include one or more fuel exhaust orifices with an opening in an outer surface of the fuel nozzle and configured to exhaust fluids unrestricted by the housing forming the cooling system cooling chamber. The cooling system may provide cooling fluids to cool the fuel nozzle within the cooling system cooling chamber regardless of whether the fuel nozzle is in use.

Abstract: A secondary fuel stage (14) of a combustor of a gas turbine engine. The combustor has a main combustion zone (43) upstream of the secondary fuel stage to ignite working gas The secondary fuel stage includes a nozzle (18) with dual outlets (20, 22) oriented with a circumferential component to inject an air-fuel mixture (24) into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas (44) such that a peak temperature (46) of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature (50) of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle (118).

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: A gas turbine engine has a non-axially symmetric main duct portion (113). The non-axially symmetric main duct portion (113) may provide improved aerodynamics, heat load, structural strength and engine compactness.

Abstract: An improved combustion system having a reduced combustion residence time in a combustion turbine engine is provided. The combustor system may include a flow-accelerating structure (16, 51) having an inlet (26) and an outlet (28). The inlet of the flow-accelerating structure is fluidly coupled to receive a flow of combustion gases from a combustor outlet. At least one fuel injector (32, 64, 66) is disposed between the inlet and the outlet of the flow-accelerating structure. The flow-accelerating structure causes an increasing speed to the flow of combustion gases, and, as a result, the flow of combustion gases in the flow-accelerating structure experiences a decreased static temperature and a reduced combustion residence time, each of which is effective to reduce NOx emissions at the high firing temperatures of the turbine engine.

Abstract: A gas turbine engine component (10), having: a base layer (60) including an array (110) of pockets (52) separated by raised ribs (36), and a film cooling hole (70) through the base layer in each pocket; and a cover sheet (62) diffusion bonded to the raised ribs and including an impingement hole (72) for each pocket of the array of pockets. The raised ribs include a thickness (104) that is less than half of a smallest dimension (96) of the pocket. The component is configured to receive combustion gases from a combustor and accelerate and deliver the combustion gases onto a first row of turbine blades without a turning vane.