Collins Engine Nozzles Patente

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A torch igniter for a combustor of a gas turbine engine includes an igniter body (20) and an igniter head. The igniter body is disposed within a high-pressure case (18) of a gas turbine engine and extends primarily along a first axis, and includes an annular wall and an outlet wall. The annular wall surrounds the first axis and defines a radial extent of a combustion chamber therewithin. The outlet wall is disposed at a downstream end of the annular wall, defines a downstream extent of the combustion chamber, and includes an outlet fluidly communicating between the combustion chamber and an interior of the combustor. The igniter head (22) is removably attached to the igniter body at an upstream end of the annular wall, wherein the igniter head defines an upstream extent of the combustion chamber, and includes an ignition source and a fuel injector (34).

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A filter assembly comprising: a manifold (1) having a fluid inlet (2) and a fluid outlet (3), a filter housing (4) having a filter medium (6) provided therein, the filter medium defining an inner filter chamber (7) and defining an outer filter chamber (8) between the filter medium and the filter housing, the filter housing being removably attached to the manifold so as to provide a fluid flow path from the inlet into the inner filter chamber via a supply channel (11), through the filter medium into the outer chamber and out of the outlet; characterised by the filter assembly further comprising a bypass valve assembly forming a bypass channel (13) from the supply channel (11) that bypasses flow through the filter medium, the bypass valve assembly comprising one or more openings (200) in a wall of the supply chamber and a corresponding one or more flaps (202) associated with respective openings (200), the one or more flaps (202) being configured to move from a default closed position over the respective opening (200) to close the opening, to an open position relative to the respective opening in which fluid can flow from the supply channel (11) via the opening (200), the flaps moveable from the closed to the open position in response to a pressure differential across the flap exceeding a predetermined value, the flaps further configured to return from the open to the closed position when the pressure differential is below the predetermined value.

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A fuel injection system (100) for a gas turbine engine (102) includes a first plurality of fuel nozzles (110) arrayed in a circular pattern. Each of the nozzles in the first plurality of fuel nozzles (110) includes a first airflow area defined therethrough. A second plurality of fuel nozzles (112) radially inward from the first plurality of fuel nozzles (110). Each of the nozzles in the second plurality of fuel nozzles (112) includes a second airflow area defined therethrough. The first airflow area is larger than the second airflow area. A third plurality of fuel nozzles (114) can be radially inward from the second plurality of fuel nozzles (112). Each of the nozzles in the third plurality of fuel nozzles (114) can include a third airflow area defined therethrough. The second airflow area can be larger than the third airflow area.

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A method of making an impeller (100) includes building the impeller (100) in a layer by layer process in a build direction along the rotational axis starting from a base of the hub (102). The plurality of blades includes a plurality of perforated blades that support the shroud (106) during additively manufacturing the impeller (100). The method can include installing the impeller (100) in a fuel pump, air compressor, or the like, without removing the perforated blades from the impeller (100).

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A system for depowdering additively manufactured parts includes a deflection plate (122), a hammer device (126) mounted to a first side of the deflection plate (122), and a mounting plate (108) operatively connected to a second side of the deflection plate (122) relative to the hammer device (126), the mounting plate (108) being configured for rotation relative to the deflection plate (122).

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A fuel injector assembly (100) has a fuel nozzle (102) including a radial feed arm with an elongated axially extending nozzle portion (106) having a central axis (X) extending therethrough, the elongated nozzle portion has a distal spray tip (108) with a frusto-conical outer surface (110) and a planar front surface (112), wherein a primary pressure atomizer port (114) is centrally provided in the planar front surface of the distal spray tip and a set of circumferentially spaced apart secondary flat spray slots (116) are provided in the frusto-conical outer surface of the distal spray tip.

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A filter assembly comprising: a manifold (1) having a fluid inlet (2) and a fluid outlet (3), a filter housing (4) having a filter medium (6) provided therein, the filter medium defining an inner filter chamber (7) and defining an outer filter chamber (8) between the filter medium and the filter housing, the filter housing being removably attached to the manifold so as to provide a fluid flow path from the inlet into the inner filter chamber, through the filter medium into the outer chamber and out of the outlet; characterised by the filter assembly further comprising a valve assembly mounted inside the manifold, the valve assembly comprising a valve piston (20) and a valve spring (21) arranged in engagement with the valve piston to bias the valve piston into a first position and to compress, in response to a pressure differential across the valve piston exceeding the spring force, to move the valve piston to a second position being a bypass position in which a bypass channel is opened to direct flow from the fluid inlet to the fluid inlet without passing through the filter medium, the valve assembly further comprising an adaptor ring (22) located between the valve piston (20) and the filter housing (4) and provided with an annular seal (24), and wherein the valve piston (20) is provided with a radially extending flange (23) and an inner piston wall configured such that as the filter housing is being detached from the manifold, the valve spring expands to move the valve piston to a third, shut off position whereby the piston flange is in sealing engagement with the adaptor ring and the outlet seal and the inner piston wall is in sealing engagement with inlet seals such that flow from the inlet and the outlet is shut off from entering the filter housing.

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An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle (27), and a torch igniter (10) within the combustor case. The torch igniter (10) includes a combustion chamber, a cap defining the upstream end of the combustion chamber and configured to receive a fuel injector and a surface igniter, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The torch igniter (10) is situated such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case.

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A system includes an air manifold (102), a fuel manifold (104), and a plurality of fuel injectors (106). At least one of the fuel injectors includes a heat exchanger portion (108) for supplying compressed, cooled air form the heat exchanger portion to the air manifold. An air valve (122) is operatively connected to an outlet of the air manifold for controlling release of air from the air manifold. A controller (128) is operatively connected to the air valve, wherein the controller includes machine readable instructions configured to control the air valve to regulate flow of air through the air valve based on fuel temperatures in the fuel channel. The machine readable instructions can be configured to cause the controller to flow air through the air valve in a heat exchange mode if a fuel temperature in the fuel injectors is below a predetermined fuel temperature.

A system can include a torsion applicator (e.g., a torsion motor and shaft) configured to apply a torque to a test article (108) that is additively built on and attached to a build plate (103). The system can include at least one twist sensor and at least one torque sensor. A method for determining quality of an additively manufactured article or batch thereof can include torsion testing at least one additively manufactured test article that is built on and attached to a build plate (103) while the at least one test article is still attached to the build plate (103).

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