Abstract: In general, techniques are described by which to provide a turbine engine compressor particulate offtake. A gas turbine engine comprising a compressor may perform the techniques. The compressor may comprise a plurality of compressor stages, where each compressor stage comprises a circumferential row of stator vanes and a rotor. The compressor may also include an outer circumferential casing that defines a fluidic opening within or between adjacent compressor stages. The fluidic opening may be configured to receive particulate flowing and air through the compressor and output the particulate and air outside of the gas turbine engine. The gas turbine engine also includes a combustor in series flow downstream of the compressor, and a turbine in series flow downstream of the combustor.

Abstract: An airfoil of a gas turbine engine includes a leading edge and an opposed trailing edge defining a chord between the leading edge and the trailing edge, wherein the chord has a chord length. A concave surface is between the leading edge and the trailing edge, which includes a first portion proximal the leading edge of the airfoil and a second portion proximal the trailing edge of the airfoil, wherein the first portion of the concave surface includes about 10% to about 50% of the chord length. An erosion-resistant ceramic, cermet or intermetallic coating is on the second portion of the concave surface, which includes a coating leading edge pattern. The first portion of the concave surface is free of the erosion-resistant coating.

Abstract: In general, techniques are described by which to provide a turbine engine compressor particulate offtake. A gas turbine engine comprising a compressor may perform the techniques. The compressor may comprise a plurality of compressor stages, where each compressor stage comprises a circumferential row of stator vanes and a rotor. The compressor may also include an outer circumferential casing that defines a fluidic opening within or between adjacent compressor stages. The fluidic opening may be configured to receive particulate flowing and air through the compressor and output the particulate and air outside of the gas turbine engine. The gas turbine engine also includes a combustor in series flow downstream of the compressor, and a turbine in series flow downstream of the combustor.

Abstract: An airfoil of a gas turbine engine includes a leading edge and an opposed trailing edge defining a chord between the leading edge and the trailing edge, wherein the chord has a chord length. A concave surface is between the leading edge and the trailing edge, which includes a first portion proximal the leading edge of the airfoil and a second portion proximal the trailing edge of the airfoil, wherein the first portion of the concave surface includes about 10% to about 50% of the chord length. An erosion-resistant ceramic, cermet or intermetallic coating is on the second portion of the concave surface, which includes a coating leading edge pattern. The first portion of the concave surface is free of the erosion-resistant coating.

Abstract: Systems and methods for suppressing infrared radiation generated by a turbine engine. A system comprises a primary assembly having a center body, a plurality of vanes extending from the center body, an outer radial duct with the plurality of vanes extending therethrough, a structural baffle, and a mixer. The primary assembly is disposed in the exhaust flow path of a turbine engine and encased in ducting and/or an airfoil. An air flow path defined between the center body and outer radial duct is axially spit by an interface rim and flow segregator. The flow segregator segregates engine core flow from ambient air flow.

Abstract: Systems and methods for suppressing infrared radiation generated by a turbine engine. A system comprises a primary assembly having a center body, a plurality of vanes extending from the center body, an outer radial duct with the plurality of vanes extending therethrough, a structural baffle, and a mixer. The primary assembly is disposed in the exhaust flow path of a turbine engine and encased in ducting and/or an airfoil. An air flow path defined between the center body and outer radial duct is axially spit by an interface rim and flow segregator. The flow segregator segregates engine core flow from ambient air flow.

Abstract: In some examples, a method includes forming a photoresist layer on a surface of a metallic substrate and developing the photoresist layer to define a pattern exposing a portion of the surface of the metallic substrate. The method also may include forming an electrically conductive layer on a surface of the photoresist layer and the exposed portions of the surface of the metallic substrate. The electrically conductive layer contacts the exposed portions of the surface of the metallic substrate. The method may further include submerging the substrate, the photoresist layer, and the electrically conductive layer in an electrolyte solution; and applying a voltage to between a cathode and an anode submerged in the electrolyte solution to anisotropically etch the metallic substrate where the electrically conductive layer contacts the exposed portions of the surface of the metallic substrate to form at least one feature in the metallic substrate.

Abstract: One embodiment of the present invention is a unique engine hot section component having a coating system operative to reduce heat transfer to the hot section component. Another embodiment is a unique method for making a gas turbine engine hot section component with a coating system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, hot section components and coating systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique engine hot section component having a coating system operative to reduce heat transfer to the hot section component. Another embodiment is a unique method for making a gas turbine engine hot section component with a coating system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, hot section components and coating systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: In some examples, a method includes forming a photoresist layer on a surface of a metallic substrate and developing the photoresist layer to define a pattern exposing a portion of the surface of the metallic substrate. The method also may include forming an electrically conductive layer on a surface of the photoresist layer and the exposed portions of the surface of the metallic substrate. The electrically conductive layer contacts the exposed portions of the surface of the metallic substrate. The method may further include submerging the substrate, the photoresist layer, and the electrically conductive layer in an electrolyte solution; and applying a voltage to between a cathode and an anode submerged in the electrolyte solution to anisotropically etch the metallic substrate where the electrically conductive layer contacts the exposed portions of the surface of the metallic substrate to form at least one feature in the metallic substrate.

Abstract: One embodiment of the present invention is a unique system for measuring radiant energy in gas turbine engines, gas turbine engine components and gas turbine engine/component rigs. Another embodiment is a unique method for measuring radiant energy in gas turbine engines, gas turbine engine components and gas turbine engine/component rigs. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for measuring radiant energy. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: An apparatus includes a first flow panel and a second flow panel. The first flow panel includes a first flow portion and a second flow portion. The first flow portion defines a flow passageway within which a gas can flow in a first direction. The second flow portion defines a set of microchannels in fluid communication with the flow passageway and within which the gas can flow in a second direction, where the second direction is nonparallel to the first direction. The first flow panel is coupled to the second flow panel to define a heat transfer passageway within which a heat transfer medium can be conveyed in a third direction, where the third direction is opposite the first direction. In such embodiments, the heat transfer passageway is fluidically isolated from the flow passageway and the set of microchannels by a thermally conductive side wall.

Abstract: One embodiment of the present invention is a unique system for measuring radiant energy in gas turbine engines, gas turbine engine components and gas turbine engine/component rigs. Another embodiment is a unique method for measuring radiant energy in gas turbine engines, gas turbine engine components and gas turbine engine/component rigs. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for measuring radiant energy. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: Disclosed is an exhaust mixer (50) including a passage (54) extending from an inlet (56) to an outlet (58) that is coincident with a centerline axis of mixer (50). Several ridges (68) are circumferentially disposed about the axis and each flare away from the centerline axis relative to a direction along the centerline axis from inlet (56) toward outlet (58). Ridges (68) each define a corresponding one of several inner channels (74) radially disposed about passage (54) that each intersect passage (54) between inlet (56) and outlet (58). Several outer channels (84) are also radially disposed about passage (54) and are each positioned between a corresponding pair of inner channels (74). Ridges are each shaped to turn inner channels (74 and outer channels (84) about the axis as ridges (68) extend along the indicated direction. Inner channels (74) diverge away from the axis and one another in this direction while outer channels (84) converge toward the axis and one another in this direction.

Abstract: Disclosed is an exhaust mixer (50) including a passage (54) extending from an inlet (56) to an outlet (58) that is coincident with a centerline axis of mixer (50). Several ridges (68) are circumferentially disposed about the axis and each flare away from the centerline axis relative to a direction along the centerline axis from inlet (56) toward outlet (58). Ridges (68) each define a corresponding one of several inner channels (74) radially disposed about passage (54) that each intersect passage (54) between inlet (56) and outlet (58). Several outer channels (84) are also radially disposed about passage(54) and are each positioned between a corresponding pair of inner channels (74). Ridges are each shaped to turn inner channels (74and outer channels (84) about the axis as ridges (68) extend along the indicated direction. Inner channels (74) diverge away from the axis and one another in this direction while outer channels (84) converge toward the axis and one another in this direction.

Abstract: The present invention contemplates a gas turbine engine compressor including a plurality of effervescent atomizers to inject a mixture of water and methanol into the compressor inlet. A plurality of droplets, preferably less than ten microns in size, travels through the inlet duct to the compressor. In one embodiment the plurality of effervescent atomizers are located around the circumference of the inlet duct and upstream of the compressor inlet and the injection occurs into a gas having a substantially ambient pressure.

Abstract: The present invention contemplates a gas turbine engine compressor including a plurality of effervescent atomizers to inject a mixture of water and methanol into the compressor inlet. A plurality of droplets, preferably less than ten microns in size, travels through the inlet duct to the compressor. In one embodiment the plurality of effervescent atomizers are located around the circumference of the inlet duct and upstream of the compressor inlet and the injection occurs into a gas having a substantially ambient pressure.