Abstract: A liquid-vapor separator includes a housing, an inlet disposed on the housing and configured to receive a working fluid into the housing, a vapor stream outlet disposed on the housing and configured to release a vapor stream of the working fluid, and a demister disposed in the housing and configured to transfer thermal energy between the working fluid and the vapor stream. In some embodiments, the working fluid absorbs thermal energy and evaporates to provide the vapor stream that includes entrained droplets. At least a portion of the entrained droplets absorbs thermal energy from the working fluid to evaporate when the vapor stream flows through the demister. In some embodiments, the liquid-vapor separator includes a passive demisting portion that demists by obstructing at least a portion of the entrained droplets.

Abstract: An evaporator includes a housing having a first end longitudinally opposing a second end. The evaporator includes an inlet disposed on the housing and configured to receive a fluid. The evaporator also includes a tube bundle disposed in the housing and configured to evaporate the fluid to provide a vapor stream arranged to exit through an outlet on the housing. Additionally, the evaporator has a flow balancer provided between the tube bundle and the outlet on the housing, and the flow balancer is configured to balance refrigerant quality between the first end and the second end of the evaporator by controlling the vapor stream.

Abstract: A liquid-vapor separator includes a housing, an inlet disposed on the housing and configured to receive a working fluid into the housing, a vapor stream outlet disposed on the housing and configured to release a vapor stream of the working fluid, and a demister disposed in the housing and configured to transfer thermal energy between the working fluid and the vapor stream. In some embodiments, the working fluid absorbs thermal energy and evaporates to provide the vapor stream that includes entrained droplets. At least a portion of the entrained droplets absorbs thermal energy from the working fluid to evaporate when the vapor stream flows through the demister. In some embodiments, the liquid-vapor separator includes a passive demisting portion that demists by obstructing at least a portion of the entrained droplets.

Abstract: An electronic actuator assembly operates an in-line valve. A valve seat of the in-line valve is surrounded by a plate. The plate can include one or more openings configured to allow fluid to pass through the plate. A perimeter of the plate outside of the openings can be configured to have ends of pipes joined on either side of the plate. The in-line valve can be operated by an electronic actuator. The electronic actuator can be powered by a supply line that enters the assembly through the plate. The electronic actuator assembly can be incorporated in to a fluid circuit to serve as an expander. The electronic actuator can be located in a housing to direct flow around the electronic actuator. The electronic actuator can be installed in place of an orifice plate of an existing fluid circuit of a heating, ventilation, air conditioning, or refrigeration (HVACR) system.

Abstract: An apparatus, system, and method of separating and directing process fluid flow via the use of both low pressure drop pipes and high performance tubes within a refrigerant evaporator are disclosed. The evaporator includes a shell; the shell includes a process fluid inlet and a process fluid outlet. The evaporator also includes a plurality of tubes disposed within the shell and carrying a process fluid; the plurality of tubes includes a first plurality of tubes and a second plurality of tubes. The evaporator further includes a plurality of redirect pipes disposed within the shell and carrying the process fluid; the plurality of redirect pipes includes a first redirect pipe and a second redirect pipe. The evaporator functions by separating and directing process fluid flow into two portions via the use of both tubes and redirect pipes.

Abstract: An apparatus, system, and method of separating and directing process fluid flow via the use of both low pressure drop pipes and high performance tubes within a refrigerant evaporator are disclosed. The evaporator includes a shell; the shell includes a process fluid inlet and a process fluid outlet. The evaporator also includes a plurality of tubes disposed within the shell and carrying a process fluid; the plurality of tubes includes a first plurality of tubes and a second plurality of tubes. The evaporator further includes a plurality of redirect pipes disposed within the shell and carrying the process fluid; the plurality of redirect pipes includes a first redirect pipe and a second redirect pipe. The evaporator functions by separating and directing process fluid flow into two portions via the use of both tubes and redirect pipes.

Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.

Abstract: A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.

Abstract: An airfoil has a wall, a cooling channel, a trench, and a plurality of cooling holes. The wall has a leading edge, a trailing edge, a pressure side, a suction side, an outer diameter end, and an inner diameter end to define an interior. The cooling channel extends radially through the interior of the wall between the pressure side and the suction side and along the leading edge. The trench extends radially along an exterior of the wall at the leading edge and is recessed axially into the leading edge to form a back wall. The back wall is contoured to include at least one undulation. The plurality of cooling holes extends through the back wall of the trench to connect the interior of the wall at the cooling channel to the exterior.

Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.

Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.

Abstract: A gas turbine engine component comprises a plurality of walls, a cooling channel, a plurality of ribs and a plurality of pedestals. The plurality of walls has a pair of major surfaces opposed to define an interior chamber. The cooling channel extends through the interior chamber of the plurality of walls between the major surfaces. The plurality of ribs extends through the cooling channel to form a plurality of wavy passages having bowed-out sections. The plurality of pedestals is positioned between adjacent ribs, each pedestal being positioned in a bowed-out section.

Abstract: A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.

Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface that provides a leading edge. A first cooling passage includes radially spaced legs extending laterally from one side of the leading edge toward another side of the leading edge and interconnecting to form a loop with one another. A trench extends radially in the exterior surface along the leading edge. The trench intersects one of the first and second legs to provide at least one first cooling hole in the trench.

Abstract: A gas turbine engine component comprises a plurality of walls, a cooling channel, a plurality of ribs and a plurality of pedestals. The plurality of walls has a pair of major surfaces opposed to define an interior chamber. The cooling channel extends through the interior chamber of the plurality of walls between the major surfaces. The plurality of ribs extends through the cooling channel to form a plurality of wavy passages having bowed-out sections. The plurality of pedestals is positioned between adjacent ribs, each pedestal being positioned in a bowed-out section.

Abstract: An example method of manufacturing an airfoil includes providing a ceramic core corresponding to an interior cooling channel. A refractory metal core is provided that corresponds to a cooling passage. The cores are arranged in a mold. An airfoil structure is cast about the cores to provide a turbine engine airfoil. The turbine engine airfoil includes a wall providing the interior cooling channel and an exterior airfoil surface. The cooling passage is provided in the wall and fluidly connects the interior cooling channel to the exterior airfoil surface. The cooling passage includes multiple inlets and multiple outlets respectively adjoining the interior cooling channel and the exterior airfoil surface. At least one of a first inlet and outlet has a different structural flow characteristic than at least one of a second inlet and outlet.

Abstract: A airfoil comprises a wall, a cooling channel, a trench and a plurality of leading edge cooling holes. The wall has a leading edge, a trailing edge, a pressure side, a suction side, an outer diameter end and an inner diameter end to define an interior. The cooling channel extends radially through the interior of the wall between the pressure side and the suction side and along the leading edge. The trench extends radially along an exterior of the wall at the leading edge and is recessed axially into the leading edge to form a back wall. The back wall is contoured to include at least one undulation. The plurality of leading edge cooling holes extends through the back wall of the trench to connect the interior of the wall at the cooling channel to the exterior.

Abstract: A method involves forming a core assembly. The forming includes deforming a wire, the deforming including increasing a transverse linear dimension along at least one portion of the wire. The wire is assembled to a ceramic core.

Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface providing a leading edge. A radially extending first cooling passage is arranged near the leading edge and includes first and second portions. The first portion extends to the exterior surface and forms a radially extending trench in the leading edge. The second portion is in fluid communication with a second cooling passage. In one example, the second cooling passage extends radially, and the first cooling passage wraps around a portion of the second cooling passage from a pressure side to a suction side between the second cooling passage and the exterior surface. In the example, the first portion is arranged between the pressure and suction sides. In one example, the first cooling passage is formed by arranging a core in an airfoil mold. The trench is formed by the core in one example.

Abstract: A turbine engine airfoil includes an airfoil structure having a side with an exterior surface. The structure includes a cooling passage extending a length within the structure and providing a convection surface facing the side. The convection surface is twisted along the length, which varies a heat transfer rate between the exterior surface and the convection surface along the length. In one example, the cooling passage is provided by a refractory metal core that is used during the airfoil casting process. The core includes multiple legs joined by a connecting portion. At least one of the legs is twisted along its length. The legs are deformed toward one another opposite the connecting portion to provide a desired core shape that corresponds to the shape of the cooling passage. Accordingly, the cooling passage provides desired cooling of the airfoil.