Abstract: A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.

Abstract: A turbine engine including an engine core, a nacelle, and a cowl door. The engine core including in serial, axial flow arrangement a compressor section, a combustor section, and a turbine section and defining a first airflow axially through the engine core. The nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow along the exterior surface and an internal passage located between the exterior surface and the engine core and defining a third airflow. The cowl door located along the nacelle.

Abstract: An unducted fan turbine engine comprising an engine core including a first airflow, and a nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further comprising an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The unducted fan turbine engine further comprising a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a cowl door located in the nacelle.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: A gas turbine engine includes a turbomachine defining a core flowpath extending through a first compressor and a second compressor, wherein a first compressor frame defines a compressor bypass passage extending from the core flowpath at the first compressor frame; and a forward compressor frame positioned between the first compressor and the second compressor, wherein the forward compressor frame defines at least in part a second portion of the core flowpath at a location downstream of the first portion of the core flowpath, wherein the forward compressor frame defines a compressor bleed passage extending from the core flowpath at a location downstream of the first compressor and upstream of the second compressor to egress a flow of air away from the core flowpath.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: An unducted fan turbine engine comprising an engine core including a first airflow, and a nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further comprising an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The unducted fan turbine engine further comprising a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a cowl door located in the nacelle.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: A turbine engine includes: a core cowl, a core within the core cowl, the core including a compressor having a bleed port; an undercowl space; a cooling duct at least partially in the undercowl space and having an inlet and an outlet, the inlet communicating with a source of cooling air, the outlet communicating with the compressor bleed port; a valve assembly in the cooling duct; and a cooling blower operable to move air flow from the inlet of the cooling duct towards the outlet of the cooling duct and into the compressor bleed port. A method of cooling an engine having a core cowl and a compressor, combustor and turbine includes: operating the engine; shutting the engine down; after or during engine shutdown, operating a cooling blower internal to the engine cowl, to force air through the compressor by way of a compressor bleed port.

Abstract: A muffling device for exhausting at least one fluid flow in a gas turbine engine includes a first diffuser coupled in flow communication with a first conduit. The first diffuser is configured to exhaust a first fluid flow. The device further includes a second diffuser disposed adjacent the first diffuser. The second diffuser is coupled in flow communication with a second conduit. The second diffuser is configured to exhaust a second fluid flow. The device also includes a third diffuser at least partially surrounding the first diffuser and the second diffuser. The third diffuser is coupled in flow communication with the first diffuser and the second diffuser. The third diffuser includes a body with apertures and is configured to exhaust a third fluid flow. The third fluid flow includes at least one of the first fluid flow and the second fluid flow.

Abstract: A muffling device for exhausting at least one fluid flow in a gas turbine engine includes a first diffuser coupled in flow communication with a first conduit. The first diffuser is configured to exhaust a first fluid flow. The device further includes a second diffuser disposed adjacent the first diffuser. The second diffuser is coupled in flow communication with a second conduit. The second diffuser is configured to exhaust a second fluid flow. The device also includes a third diffuser at least partially surrounding the first diffuser and the second diffuser. The third diffuser is coupled in flow communication with the first diffuser and the second diffuser. The third diffuser includes a body with apertures and is configured to exhaust a third fluid flow. The third fluid flow includes at least one of the first fluid flow and the second fluid flow.

Abstract: Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15.

Abstract: A hot gas seal for sealing an opening in a heat shield element or between heat shield elements of a heat shield includes a resilient portion for providing a force which is designed such that the hot gas seal can be held in the opening by the force and/or that the sealing efficiency of the hot gas seal is increased by the force. Further, a hot gas seal assembly for sealing an opening in a heat shield element or between heat shield elements of a heat shield against a hot gas is provided, the assembly including a sealing body and a further sealing element which is in a solid state at room temperature and in a high viscosity liquid state at a temperature of the hot gas.

Abstract: An inventive hot gas seal for sealing an opening, e.g. a gap or hole, in a heat shield element or between heat shield elements of a heat shield or a liner comprises at least one resilient portion for providing a force which is designed such that the hot gas seal can be held in said opening by said force and/or that the sealing efficiency of the hot gas seal is increased by said force. Thus, further means for holding the seal in place and/or for increasing the sealing efficiency are not necessary. The invention is particularly useful if the design of said resilient portion is such that the force provides a holding action and increases the sealing efficiency, at the same time.

Abstract: Methods and systems for operating an integrated actuator are provided. The integrated actuator comprises an actuator body, an extension rod coupled to the actuator body. The extension rod includes a piston valve and is configured for selective movement between a first position in a first mode of operation where the piston valve is fully open and a second position in a second mode of operation where the piston valve is less than fully open. The integrated actuator further comprises a flow body coupled to the actuator body such that the flow body houses the piston valve and a modulation device coupled to the extension rod. The modulation device is operable by movement of the extension rod and is configured to be fully open in the first mode of operation and is configured to be less than fully open in the second mode of operation.

Abstract: Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15.

Abstract: A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element.

Abstract: Compact, high-pressure exhaust muffling devices are disclosed. Some example muffling devices may include an inner flow conditioner including an inlet configured to convey a pressurized fluid flow into an inner flow conditioner interior. The inner flow conditioner may include a plurality of inner flow conditioner holes. The muffling device may include an exhaust can disposed substantially around the inner flow conditioner and arranged to receive the pressurized fluid flow via the inner flow conditioner holes into an exhaust can interior. The exhaust can may include a plurality of exhaust screen holes arranged to discharge the pressurized fluid flow from the exhaust can interior. The exhaust can interior may be substantially devoid of flow obstructions between the plurality of inner flow conditioner holes and the exhaust screen holes.

Abstract: A system for venting a high-pressure flow stream is disclosed, the system comprising a device having a plurality of orifice plates, each orifice plate having a plurality of orifices, wherein the plurality of orifice plates are oriented relative to each other such that the pressure of the flow stream substantially drops.

Abstract: A system for venting a high-pressure flow stream is disclosed, the system comprising a device having a plurality of orifice plates, each orifice plate having a plurality of orifices, wherein the plurality of orifice plates are oriented relative to each other such that the pressure of the flow stream substantially drops.