Abstract: A heat transfer system (e.g., a heat pump) can include at least a first fin array and at least a first pump disposed in fluid communication with the first fin array and configured to cause a first fluid to flow through the first fin array. The system can include at least a first heat transfer layer attached to and/or in thermal communication with the first fin array. The first heat transfer layer can define a second fluid flow path therein for a second fluid to flow fluidly isolated from the first fluid. The first heat transfer layer and the first fin array can be configured to cause heat transfer between the first fluid and the second fluid.

Abstract: An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.

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

Abstract: The application relates to unidirectional hydrokinetic turbines having an improved flow acceleration system that uses asymmetrical hydrofoil shapes on some or all of the key components of the turbine. These components that may be hydrofoil shaped include, e.g., the rotor blades (34), the center hub (36), the rotor blade shroud (38), the accelerator shroud (20), annular diffuser(s) (40), the wildlife and debris excluder (10, 18) and the tail rudder (60). The fabrication method designs various components to cooperate in optimizing the extraction of energy, while other components reduce or eliminate turbulence that could negatively affect other component(s).

Abstract: A turbine system component includes a body having an exterior surface, and a cooling passage defined in the body. The cooling passage has a first cross-sectional area in the body. The component also includes a hollow member defining a first exit opening at the exterior surface of the body and coupled in the cooling passage. The hollow member, at the first exit opening, has a second cross-sectional area that is less than the first cross-sectional area, creating an exit opening with a smaller dimension than the original cooling passage. The hollow member is made of a material having a melt temperature higher than an operating temperature of the turbine system. The hollow member(s) reduces the cooling capabilities of the cooling passage. A cooling profile of the component can be generated to identify those cooling passages having excess cooling so they can have their exit openings reduced in cross-sectional area.

Abstract: A split volute for a centrifugal pump is disclosed that provides a manufacturing advantage by improving the yield of high-chrome iron casting, providing for full surface coating capability using line-of-sight spray coating systems. Performance improvements include improved pump efficiency, abrasion resistance, and volute lifetime. Additional operational cost savings are enabled through reduced time required for common volute maintenance procedures and an increased replacement interval for the volute. Taken together, these advantages reduce the total cost of ownership of the split volute pump system.

Abstract: A power tool including an air inlet and an inlet muffler disposed within the air inlet, the inlet muffler comprising a plurality of inlet ports, each of the plurality of inlet ports comprising a peripheral surface defining a port aperture therethrough, at least one of the plurality of inlet ports further comprising a damper material provided on the peripheral surface of the at least one inlet port and further defining the port aperture therethrough.

Abstract: A stick pump assembly includes a tube having a first end, a second end, and an axis extending through the first and second ends. The tube accommodates fluid to flow therethrough. The stick pump assembly also includes a pump including a motor and an impeller. The pump has an inlet adjacent the first end and in fluid communication with the tube. The stick pump assembly further includes a handle having an outlet adjacent the second end and in fluid communication with the tube. The handle includes a receptacle configured to receive a battery pack. The stick pump assembly also includes a filter assembly supported by the pump and in fluid communication with the inlet. Fluid flows into the stick pump assembly though the inlet, around the motor, through the tube, and out of the stick pump assembly through the outlet.

Abstract: A ducted fan device provides enhanced containment capability resulting from a Fan Blade Out (FBO) event. The fan device includes an annular fan shroud (52) and an electric motor disposed at the center driving at least one fan blade (58, 64). The fan shroud (52) has a multilayer structure including a fiber layer (74) and a resin layer (70, 72). The shroud has an opposing section (A) that opposes a tip of at least one of the fan blades (58, 64) and a non-opposing section (B) that does not oppose the tips of the fan blades (58, 64). The opposing and non-opposing sections are arranged in the axial direction. In the non-opposing section (B), the fiber layer (74) is impregnated with part of resin forming the resin layer (70, 72). In the opposing section (A), the fiber layer (74) is not impregnated with the resin forming the resin layer (70, 72).

Abstract: A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

Abstract: Disclosed are pumps designed to make priming more efficient and therefore reduce priming time. The disclosed pumps include one or more deflection structures that prevent fluid moving through a diffuser of the pump from continuing in a circular path and instead divert the fluid in a different direction that leads directly to an outlet of the pump. This deflection reduces air bubble accumulation inside the pump while priming and makes it easier for air to escape through the pump outlet. Making it easier for air to escape the pump outlet ultimately allows air to escape the pump faster during priming, reducing back pressure caused by trapped air pockets inside the pump and improving priming performance.

Abstract: A grille assembly for an air handling unit is provided. The grille assembly includes a plurality of first wires aligned in a first plane perpendicular to a direction of flow of air and a plurality of second wires aligned in a second plane perpendicular to the direction of flow of air. The plurality of first wires and the plurality of second wires together form a staggered structure to at least partly enclose an air passage opening of the air handling unit. The second plane is parallel to the first plane and separated by an offset distance along a third plane parallel to the direction of flow of air.

Abstract: Described is an acceptor/adapter device for securing an outboard jet motor to a watercraft. The acceptor/adapter comprises a shrouded opening for communication with an intake of the outboard jet motor. Sidewalls of the acceptor/adapter device can form a tunnel, wherein the tunnel is configured for directing a flow of water through the tunnel, into the adapter/acceptor device, and into the intake of the outboard jet motor. Also described is a hull with a tunnel for directing a flow of water to an intake of an outboard jet motor, as well as a directional device which allows for vertical or horizontal adjustments to the jet output or reversing the jet output.

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 section of a turbomachine includes a housing that houses and supports the rotating group for rotation about an axis. The housing defines a circumferential inlet passage that extends about the axis. The housing defines a turbine wheel upstream area that is disposed downstream of the circumferential inlet passage and upstream of the turbine wheel. The housing defines an outlet that is downstream of the turbine wheel. Furthermore, the turbine section includes a first flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, across the turbine wheel, to the outlet. Moreover, the turbine section includes a recirculation flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, and back to the circumferential inlet passage.

Abstract: The present disclosure is to reduce a blowing resistance while securing a mechanical strength of a fan guard. An outdoor unit 100 includes a housing 10 in which an air discharge port X is formed on an upper wall 11, a blowing fan 20 disposed inside the housing 10 to correspond to the air discharge port X, and a fan guard 30 configured to cover the blowing fan 20, wherein the fan guard 30 includes a plurality of annular ribs 32 disposed to be spaced apart from each other in a radial direction of the blowing fan 20, and radial ribs 33 configured to connect a plurality of the annular ribs 32, and wherein the radial ribs 33 are formed such that free ends 3a thereof are bent in the same direction in a cross section orthogonal to a stretching direction and a pair of opposing piece portions 3b including each of the free ends 3a are in surface contact with each other.

Abstract: A hanger for a turbine engine can include a first surface confronting a cooling airflow, a second surface facing a heated airflow, and a third surface radially outward of the first surface. The hanger can also include a cyclonic separator with a dirty air inlet and a clean air outlet, as well as a cooling air circuit extending through the cyclonic separator.

Abstract: An element for compressing or expanding a gas including a rigid housing (2) containing an internal chamber; a rotor (3a, 3b) situated in the internal chamber and comprising a rotor shaft (4a, 4b); one or more bearings (7) in which the rotor shaft (4a, 4b) is bearing-supported, wherein the rotor (3a, 3b) with its rotor shaft (4a, 4b) is rotatably mounted with respect to the housing (2) by means of these bearings (7), wherein the rotor (3a, 3b) is mounted with one or more clearances with respect to a wall (5) of the internal chamber, and the element (1) is provided with a separate yielding component (10) which is positionally adjustable with respect to the housing (2) in such a way that at least one of the clearances can be acted upon, wherein the separate yielding component (10) is not directly attached to the rotor (3a, 3b).

Abstract: A cutting system for a grinding pump, including a cutting disc attached to the pump near an inlet and having a cutting surface with multiple cutting orifices, and a rotating cutter attached to the rotating shaft of the pump and having two cutting blades, each blade having a cutting edge on a forward-facing side of the rotating cutter. The rotating cutter is located on the upstream side of the cutting disc, and cooperates with the cutting orifices of the cutting disc to perform cutting actions. Each cutting orifice has a hole extending from the cutting surface through the cutting disc to form a feeding orifice, and a cutting protrusion protruding from the cutting surface and surrounding the hole region. The multiple cutting orifices define recessed areas of the cutting surface between the cutting orifices. The cutting system can prevent uncut floating matters from being trapped, and is effective and safe.

Abstract: Provided is a heating blower, comprising an air duct, a motor and a wind wheel arranged in the air duct, and a heating device arranged at a first air outlet of the air duct; the wind wheel is fixed to a rotating shaft of the motor; the heating device comprises a housing, an electric heater and a moving assembly; the housing is sleeved on the first air outlet, forming an inner chamber, which comprises a first area facing directly to the first air outlet and a second area not facing directly to the first air outlet; the electric heater is arranged on the moving assembly, and moves between the first area and the second area along with the moving assembly, so that an airflow blown from the first air outlet switches between a state of passing the electric heater and a state of not passing the electric heater, and is blown out from a second air outlet provided at the housing.

Abstract: A method of fabricating a gas turbine casing out of composite material of varying thickness, the method including making a strip-shaped fiber texture by three-dimensional weaving; winding the fiber texture as a plurality of superposed layers onto a mandrel of profile corresponding to the profile of the casing that is to be fabricated, so as to obtain a fiber preform of shape corresponding to the shape of the casing that is to be fabricated; and densifying the fiber preform with a matrix; wherein, before beginning to wind the fiber texture onto the mandrel, a reinforcing band of width smaller than the width of the fiber texture is placed on the mandrel in a zone that is to form a retention zone of the casing.

Abstract: An air conditioner according to the disclosure includes a blowing fan including a suction port, a bell mouth formed along a circumferential direction of the suction port, and a fan guard extending from an inner circumferential surface of the bell mouth and covering the suction port, wherein the fan guard includes a plurality of annular ribs arranged concentrically with a gap from a center of the fan guard corresponding to a rotation axis of the blowing fan, the plurality of annular ribs includes a first annular rib adjacent the outermost edge of the fan guard and the first annular rib is arranged to be inclined to the rotation axis in a direction corresponding to the tangent line of the bell mouth.

Abstract: An interface of a centrifugal fan includes an inlet shroud of an impeller, an air intake positioned in overlapping arranged with a portion of the inlet shroud, and a clearance defined between the inlet shroud and the air intake. The clearance forms a labyrinth fluid flow path for a leakage air flow.

Abstract: Disclosed is an apparatus when installed with an Electrical Submersible Pump for fluid production protects the motor from the effect of solids on the shaft seal. The invention provides an apparatus that dynamically filters the solids and prevents them from contacting or accumulating at the vicinity of the shaft seal. The apparatus extends the run life of the ESP and prevents the motor dielectric fluid from being contaminated.

Abstract: A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flowpath, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not in operation, but does not occur continuously during engine operation.

Abstract: Turbine engine systems for interstage particle separation in multistage radial compressors are disclosed. The multistage radial compressor system includes an interstage region positioned between a first stage radial compressor and a second stage radial compressor. The interstage region includes a radially-outward oriented section, a longitudinally-oriented section, and a radially-inward oriented section. The radially-outward oriented section transitions to the longitudinally-oriented section at a first approximately 90-degree bend, and the longitudinally-oriented section transitions to the radially-inward oriented section at a second approximately 90-degree bend. The multistage radial compressor system further includes a particle separation system including an extraction slot and an aspiration slot located downstream from the extraction slot. The particle separation system is positioned along the interstage region outside of the air flow path.

Abstract: An air circulator includes a blower unit that is provided with an airflow opening on its front side, and a support unit that supports the blower unit. A grill is provided in the airflow opening. The grill is provided with plural airflow guide blades in a spiral manner. Inner end portions thereof closer to the center of the spiral of the airflow guide blades are protruded from outer end portions thereof in an airflow direction. The blower unit has a cover for forming an outer panel thereof, and the cover has a spherical shape.

Abstract: An air-sending device includes a fan and a grille provided downstream of the fan in a direction of airflow generated by the fan. The grille includes a first grille that includes a plurality of first bars spaced from each other, and a second grille that includes a plurality of second bars spaced from each other. The plurality of second bars are more densely arranged than the plurality of first bars. The second grille is provided upstream of the first grille in the direction of the airflow generated by the fan, and spaced from the first grille to face the first grille.

Abstract: A fan case with crack-arresting backsheet structure and removable containment cartridge is disclosed. An example engine fan case includes a segmented backsheet structure, the segmented backsheet structure including at least a first backsheet segment of a first length and a second backsheet segment of a second length, the first backsheet segment coupled to the second backsheet segment and at least one of the first backsheet segment or the second backsheet segment coupled to the fan case, a honeycomb structure, and a containment structure for blade fragment retention, the containment structure coupled to the segmented backsheet structure.

Abstract: A claw pole stator for a transversal flux motor includes a multiplicity of segments positioned next to one another along a circumferential direction for the annular claw pole stator. Each segment extends from an inner circumferential surface along a radial direction to an outer circumferential surface and is delimited in the circumferential direction by a first side surface and a second side surface and in an axial direction by a first end surface and a second end surface. Each segment is connected by the side surfaces to at least one other segment to form the annular claw pole stator. Segments positioned adjacent each other contact each other by a first contact surface on the first side surface or by a second contact surface on the second side surface and due to the contact surfaces form a form-locking connection in the circumferential direction.

Abstract: An air circulator includes a blower unit that is provided with an airflow opening on its front side, and a support unit that supports the blower unit. A grill is provided in the airflow opening. The grill is provided with plural airflow guide blades in a spiral manner. Inner end portions thereof closer to the center of the spiral of the airflow guide blades are protruded from outer end portions thereof in an airflow direction. The blower unit has a cover for forming an outer panel thereof, and the cover has a spherical shape.

Abstract: A softwall containment system for a machine includes an inner wall circumscribing a bladed rotatable member of the machine and extending from a forward end to an aft end. The softwall containment system also includes an outer wall circumscribing the inner wall and extending from a forward end to an aft end. The outer wall is spaced radially outwardly from the inner wall. The outer wall extends axially between a first joint coupling the forward end of the inner wall to the forward end of the outer wall and a second joint coupling the aft end of the inner wall to the aft end of the outer wall. The softwall containment system also includes an anti-ballistic material wrap covering the outer wall, the anti-ballistic material wrap including at least one of a first extension extending forward of the first joint and a second extension extending aft of the second joint.

Abstract: Systems and methods are provided for cleaning one or more cooling passages associated with a combustion chamber of a gas turbine engine. The gas turbine engine has a compressor section upstream from the combustion section. The method includes receiving a pressurized fluid from a source and directing the pressurized fluid through an inlet of a chamber such that a portion of a plurality of particles within the chamber is entrained within the pressurized fluid. The method includes injecting the pressurized fluid with the entrained portion of the plurality of particles downstream from the compressor section through an end wall of a diffuser and deswirl system upstream from a combustor plenum of the combustion section to clean the one or more cooling passages associated with the combustion chamber.

Abstract: A gas turbine engine includes a compressor and a turbine; a plurality of rotor blades positioned in the compressor or the turbine and arranged in a plurality of stages along an axial direction; an outer drum positioned at least partially radially outward of the plurality of rotor blades and rotatable with the plurality of rotor blades; and a casing extending over the outer drum and defining a plurality of air cavities with the outer drum, the plurality of air cavities arranged in series airflow communication along the axial direction.

Abstract: The present disclosure provides a wear liner for a stator vane that has a first hook and a second hook that are connected by a base, providing in a generally S-shaped channel. The wear liner includes an outer surface that is adapted to lie against a first component and an inner surface that is adapted to lie against a second component. The first hook of the wear liner includes a first engaging end that is adapted to engage a first component, while the second hook is adapted to engage the second component. The first component may comprise a vane foot and the second component may comprise a slot for receiving and securing the vane foot.

Abstract: A method of sealing a first component to a second component comprising the steps of locating at least one fiber reinforced polyimide resin layer against a first sealing surface on a first component and against a second sealing surface on a second component. At least one fiber reinforced polyimide resin layer is compressed against the first sealing surface and the second sealing surface prior to curing at least one fiber reinforced polyimide resin layer. At least one fiber reinforced polyimide resin layer is heated to promote flow and conformation to the first sealing surface and the second sealing surface. At least one fiber reinforced polyimide resin layer is cured to provide a fluid tight seal between the first component and the second component.

Abstract: Cleanout systems are disclosed. An example environmental control system includes an exhaust plenum to exhaust cooling fluid from a heat exchanger outlet of a heat exchanger, and a cleanout system coupled to the exhaust plenum adjacent the heat exchanger outlet. The cleanout system includes a cleanout passageway to fluidly couple a cleanout inlet accessible from an outer surface of the exhaust plenum and a cleanout outlet in fluid communication with the heat exchanger outlet. The cleanout system is to enable removal of particulate from the heat exchanger without disassembling the heat exchanger from the exhaust plenum or an air intake.

Abstract: A containment arrangement for a gas turbine engine comprises: a radially outer annular casing 12; a fan track liner 28 radially within the casing comprising: an impact region 30 comprising a cellular material having a first compressive strength; at least one elongate ridge portion 26 extending through the impact region in a direction having an axial component, the ridge portion having a second compressive strength higher than the first compressive strength; and a gas-washed layer 38 radially within the fan track liner.

Abstract: The present disclosure generally relates to an air filtration system, an air filtration device, and an air filtration module for removing ultra-fine particles (UFPs), pathogens (e.g., viruses, bacteria, etc.), volatile organic compounds (VOCs), oxides or odors. The systems, devices, and filter modules of the disclosure perform at enhanced filter and power efficiencies. An air filtration system is provides that includes a docking base for receiving a removable, portable air filtration device in fluid communication with the docking base. In certain embodiments, the air filtration system further includes the removable, portable air filtration device. The portable air filtration device may optionally include an air filtration module.

Abstract: An air circulator includes a blower unit that is provided with an airflow opening on its front side and in which a grill is provided in the airflow opening and a support unit that supports the blower unit, and the grill is provided with plural airflow guide blades in a spiral manner and their inner end portions closer to the center of the spiral of the plural airflow guide blades are protruded in an airflow direction from their outer end portions made continuous to the airflow opening.

Abstract: A compressor includes a compressor screen mounted on the outer circumferential surface of a compressor disk or the inner wall of a compressor casing. The compressor screen is positioned between a row of compressor blades and a row of compressor vanes to stabilize airflow by regulating the amount of air flowing in the compressor. The compressor screen is formed of annular plate having openings through which the compressed air flows, arranged in a pattern to smoothly regulate the flow of air. The compressor screen may be variously configured, for example, to facilitate installation or to guide the flow of air using a tapered surface or a directionality of the openings or a flow guide. A gas turbine includes a combustor, a turbine, and a compressor employing the compressor screen.

Abstract: An inertial inlet particle separator system for a vehicle engine is provided. A separator assembly and collector assembly are coupled to the scavenge flow path and configured to receive the scavenge air. The collector inlet has a throat defining a cumulative throat area at each position along the throat length from the first throat end to the second throat end. The collector body defines a cross-sectional area associated with each position along the throat length between the first throat end and the second throat end. The collector outlet is coupled to the collector body such that scavenge air flows into the collector inlet, through the collector body, and out through the collector outlet. At a first position between the first throat end and the second throat end, the respective cross-sectional area of the collector body is greater than or equal to the respective cumulative throat area.

Abstract: The invention relates to a holding system for a fan comprising a wall ring and a protective grille. A holding system according to the invention for a fan with a protective grille having at least one protective-grille strut arranged in the circumferential direction and comprising a wall ring having a first end face is characterized in that the wall ring has at least one first connecting element on the first end face and the protective grille has at least one second connecting element, whereby the first connecting element can be operatively connected to the second connecting element, and the second connecting element is arranged so as to be sunk in the first end face of the wall ring.

Abstract: An air intake unit for an engine of an aircraft and having: a housing, inside which a plenum is defined, which can be connected to the engine of the aircraft; a main intake opening; an air filter which engages the main intake opening; a bypass intake opening; a shutter device, which is coupled to the bypass intake opening and has two partitions, which are mounted so as to rotate around respective rotation axes parallel to and spaced apart from one another; and an actuator, which moves the shutter device between a closed position and an open position. In the open position of the shutter device, an upper partition is arranged transversely to the wall of the housing and in a central area of the bypass intake opening, and a lower partition is arranged parallel to the wall of the housing and overlaps said wall.

Abstract: A cooling device includes a fan; an intake-side intrusion-preventing member that is provided on an intake side of the fan and prevents an object from entering the fan; an exhaust-side intrusion-preventing member that is provided on an exhaust side of the fan and prevents an object from entering the fan. The intake-side intrusion-preventing member and the exhaust-side intrusion-preventing member have different shapes.

Abstract: Method (S) for protecting against fire a fan casing (1) comprising a roughly cylindrical barrel (10) having a main direction extending along a longitudinal axis (X) and an upstream flange (20) extending radially with respect to the longitudinal axis (X) from an upstream end of the barrel (10), the fan casing (1) being made of a composite comprising a fibrous reinforcement densified by a matrix, said matrix being polymerized, the protection method(S) comprising the following steps:?—laying (SI) widths containing glass fibre pre-impregnated with a resin capable of affording the fan casing with thermal protection against fire on an upstream radial face (22) of the upstream flange (20), and ?—polymerizing (S2) the resin in order to obtain a protective layer (2).

Abstract: An indoor unit includes axial-flow fans, which are provided on downstream of an air inlet. Further, a plurality of first bars are provided to the air inlet. In plan view, leading edge portions of blades of the axial-flow fan are inclined in a direction of rotation of the axial-flow fan from a rotary shaft side of the axial-flow fan to an outer peripheral side. Further, in plan view, the plurality of the first bars are inclined in a direction opposite to the direction of rotation of the axial-flow fan from the rotary shaft side of the axial-flow fan to the outer peripheral side.

Abstract: A discharge valve system of a bypass turbine engine compressor includes a flow deflector. The flow deflector has a wall provided with a plurality of ejection channels configured to discharge a discharge airflow from the compressor in a duct of the turbine engine in which an airflow circulates. The ejection channels are disposed in a plurality of concentric rows around a center and are oriented at an angle defined between a straight line normal to the wall and the axes of the ejection channels. The angle of the ejection channels vary by increasing from the peripheral edge towards the center of the wall so that the discharge airflow passing through the ejection channels is guided in a gyratory movement around the center.

Abstract: Disclosed are multiple stage rotating coalescer devices comprising a first stage and a second stage. The first stage may include a rotating coalescing element comprising coalescing media. The second stage is positioned either upstream or downstream or the first stage. The second stage may include one of: (i) a rotating cone stack separator, or (ii) a separate rotating coalescing element comprising coalescing media.

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.