Abstract: A turbine section for a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first outlet, and a second turbine with a second inlet. The turbine section includes an inter-turbine duct extending from the first outlet to the second inlet and configured to direct a flow along a flow direction. The inter-turbine duct is defined by a hub and a shroud. The turbine section includes at least a first splitter blade positioned between the hub and the shroud. The first splitter blade includes a pressure side, a suction side, and at least one vortex generating structure having a leading end opposite a trailing end positioned on the suction side such that a first angle is defined between the vortex generating structure and the flow direction. The vortex generating structure extends in a radial direction from the suction side toward the hub.

Abstract: A turbine section for a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first outlet, and a second turbine with a second inlet. The turbine section includes an inter-turbine duct extending from the first outlet to the second inlet and configured to direct a flow along a flow direction. The inter-turbine duct is defined by a hub and a shroud. The turbine section includes at least a first splitter blade positioned between the hub and the shroud. The first splitter blade includes a pressure side, a suction side, and at least one vortex generating structure having a leading end opposite a trailing end positioned on the suction side such that a first angle is defined between the vortex generating structure and the flow direction. The vortex generating structure extends in a radial direction from the suction side toward the hub.

Abstract: A turbine section is provided for a gas turbine engine. The turbine section is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least a first splitter blade disposed within the inter-turbine duct. The first splitter blade includes a pressure side facing the shroud, a suction side facing the hub, and at least one vortex generating structure positioned on the suction side.

Abstract: A turbine section is provided for a gas turbine engine. The turbine section is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least a first splitter blade disposed within the inter-turbine duct. The first splitter blade includes a pressure side facing the shroud, a suction side facing the hub, and at least one vortex generating structure positioned on the suction side.

Abstract: Methods and apparatus to produce alkynes are described. The method includes combusting fuel and an oxidizer in a combustion zone to create a carrier gas stream, which is accelerated to supersonic speed in an expansion zone. A feedstock material is injected into a feedstock injection zone using two or more pluralities of injection nozzles. The injection nozzles are arranged annularly. The carrier gas stream is transitioned from supersonic speed to subsonic speed to create a shockwave in a reaction zone. The reaction zone is directly connected to the feedstock injection zone, and the shockwave is created adjacent to the feedstock injection zone. The carrier gas stream and the feedstock material are simultaneously mixed and reacted.

Abstract: A turbine section of a gas turbine engine is provided. The turbine section includes a first turbine with a first inlet and a first outlet; second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least two splitter blades disposed within the inter-turbine duct. The at least two splitter blades include a first splitter blade and a second splitter blade radially interior to the first splitter blade. At least the second splitter blade has a radial position that is greater than 60% of a distance from the shroud to the hub.

Abstract: Methods and apparatus to produce alkynes are described. The method includes combusting fuel and an oxidizer in a combustion zone to create a carrier gas stream, which is accelerated to supersonic speed in an expansion zone. A feedstock material is injected into a feedstock injection zone using two or more pluralities of injection nozzles. The injection nozzles are arranged annularly. The carrier gas stream is transitioned from supersonic speed to subsonic speed to create a shockwave in a reaction zone. The reaction zone is directly connected to the feedstock injection zone, and the shockwave is created adjacent to the feedstock injection zone. The carrier gas stream and the feedstock material are simultaneously mixed and reacted.

Abstract: A pyrolytic reactor comprising a fuel injection zone, a combustion zone adjacent to the fuel injections zone, an expansion zone adjacent to the combustion zone, a feedstock injection zone comprising a plurality of injection nozzles and disposed adjacent to the expansion zone, a mixing zone configured to mix a carrier stream and feed material and disposed adjacent to the feedstock injection zone, and a reaction zone adjacent to the mixing zone. The plurality of injection nozzles are radially distributed in a first assembly defining a first plane transverse to the feedstock injection zone and in a second assembly transverse to the feedstock injection zone.

Abstract: A turbine section of a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; and an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine. The inter-turbine duct has a first station with a first meridional area, a second station with a second meridional area, and a third station with a third meridional area. The first station is upstream of the second station and the second station is upstream of the third station, and the second meridional area is less than or equal to the first meridional area.

Abstract: A pyrolytic reactor comprising a fuel injection zone, a combustion zone adjacent to the fuel injections zone, an expansion zone adjacent to the combustion zone, a feedstock injection zone comprising a plurality of injection nozzles and disposed adjacent to the expansion zone, a mixing zone configured to mix a carrier stream and feed material and disposed adjacent to the feedstock injection zone, and a reaction zone adjacent to the mixing zone. The plurality of injection nozzles are radially distributed in a first assembly defining a first plane transverse to the feedstock injection zone and in a second assembly transverse to the feedstock injection zone.

Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.

Abstract: A pyrolytic reactor comprising a fuel injection zone, a combustion zone adjacent to the fuel injections zone, an expansion zone adjacent to the combustion zone, a feedstock injection zone comprising a plurality of injection nozzles and disposed adjacent to the expansion zone, a mixing zone configured to mix a carrier stream and feed material and disposed adjacent to the feedstock injection zone, and a reaction zone adjacent to the mixing zone. The plurality of injection nozzles are radially distributed in a first assembly defining a first plane transverse to the feedstock injection zone and in a second assembly transverse to the feedstock injection zone.

Abstract: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.

Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.

Abstract: A pyrolytic reactor comprising a fuel injection zone, a combustion zone adjacent to the fuel injections zone, an expansion zone adjacent to the combustion zone, a feedstock injection zone comprising a plurality of injection nozzles and disposed adjacent to the expansion zone, a mixing zone configured to mix a carrier stream and feed material and disposed adjacent to the feedstock injection zone, and a reaction zone adjacent to the mixing zone. The plurality of injection nozzles are radially distributed in a first assembly defining a first plane transverse to the feedstock injection zone and in a second assembly transverse to the feedstock injection zone.

Abstract: A turbine section of a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; and an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine. The inter-turbine duct has a first station with a first meridional area, a second station with a second meridional area, and a third station with a third meridional area. The first station is upstream of the second station and the second station is upstream of the third station, and the second meridional area is less than or equal to the first meridional area.

Abstract: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.