Abstract: A compressor includes a rotor driven by a shaft and configured to compress air and a motor for driving the shaft. At least one bearing facilitates rotation of the shaft. A motor cooling loop is configured to provide motor cooling air to the motor. A bearing cooling loop is configured to provide bearing cooling air to the at least one bearing. A bearing support is configured to support the least one bearing, the bearing support includes an opening. A duct is configured to communicate air from the opening to an inlet of the compressor. A method for cooling a compressor is also disclosed.

Abstract: A clutch assembly includes a journal bracket having a center shaft, a drive feature rotatably supported on the center shaft of the journal bracket and configured to accept a torque input to the clutch assembly, a clutch pack that is controllable to selectively transmit torque between an input and an output, a housing attached to the clutch pack that includes a stub shaft, a removable connection engaged between the drive feature and the stub shaft such that torque is transmittable through the removable connection during operation of the clutch assembly, and one or more perpendicular engagement features on the stub shaft configured to accept a tool to engage and disengage the removable connection. At least one of the perpendicular engagement features is exposed to line-of-sight access from a location substantially perpendicular to an axis of rotation of the clutch pack.

Abstract: A method for manufacturing a recliner mechanism may include movably attaching a first plate of a recliner heart to a second plate of the recliner heart, positioning a gap ring onto the first plate of the recliner heart, positioning an encapsulation ring around the first and second plates such that the gap ring is disposed axially between the first plate and the encapsulation ring, and removing at least a portion of the gap ring from between the first plate and the encapsulation ring to form a clearance gap between the first plate and the encapsulation ring.

Abstract: Disclosed are a cylinder, a pump body assembly, a compressor, and a temperature adjusting device. The cylinder includes a cylinder body, and a first cavity and a second cavity are formed in an axial direction of the cylinder body, wherein the first cavity is in communication with the second cavity, and an inner diameter of the first cavity is greater than that of the second cavity; and when the cylinder body operates, the first cavity forms a first working cavity, and the second cavity forms a second working cavity. With such an arrangement, multiple working cavities are formed inside one cylinder body, which simplifies an installation process of the pump body assembly, and enables a pump body with the cylinder to be installed more conveniently and easily, thereby improving installation reliability of the pump body assembly.

Abstract: A suction passage includes: a first passage that is cylindrical and connected to a suction unit; and a second passage whose one end is connected to the first passage and other end has an opening on the inner circumference of a cylinder. The second passage is formed, from its one end to the other end, in a slit-like shape penetrating the upper side and the lower side of the cylinder, and satisfies L?W1, W1?D1×0.7, W2?D1 where the width of the second passage at the other end in a circumferential direction of the cylinder is W1, the width of the second passage at the one end is W2, the length of the second passage from the one end to the other end is L, and the inner diameter of the first passage at an area connected to the second passage is D1.

Abstract: A motor is provided in a shell. The motor includes a stator having an outer peripheral surface facing an inner peripheral surface of the shell, a rotor rotatably disposed inside the stator, and a nonmagnetic film disposed between the outer peripheral surface of the stator and the inner peripheral surface of the shell.

Abstract: A compressor rotor blade for an axial-type compressor has a blade profile having a transonic section and a profile section which extends in the transonic section and has concave and convex suction-side regions on the suction side, the convex suction-side region arranged downstream of the concave suction-side region, and has convex and concave pressure-side regions on the pressure side, the concave pressure-side region arranged downstream of the convex pressure-side region. Curvature progressions on the pressure side and on the suction side are both applied in a continuous manner over a profile chord of the profile section, the positions of the minimum values of the curvature progressions deviate from each other by not more than 10% of the length of the profile chord, and the positions of the maximum values of the curvature progressions deviate from each other by not more than 10% of the length of the profile chord.

Abstract: A rotor blade assembly for a gas turbine engine includes two aerofoil members joined together at their roots by a blade assembly attachment web. The rotor blade assembly is made from a composite material, for example an organic fiber composite material. The blade assembly attachment web is used to attach a plurality of rotor blade assemblies to the rest of the gas turbine engine in order to form a rotor stage. The rotor stage may, for example, be the fan stage of a turbofan gas turbine engine.

Abstract: A fluid device includes a housing defining a fluid inlet and a fluid outlet. A variable displacement assembly is in fluid communication with the fluid inlet and the fluid outlet. The variable displacement assembly includes a rotor assembly, a flexible ring, and a plurality of ring supports. The rotor assembly includes a rotor having a plurality of reciprocating members. The flexible ring is disposed about the rotor assembly. The flexible ring includes an inner surface, which is adapted for engagement with the plurality of reciprocating members, and an outer surface. The plurality of ring supports is disposed about the flexible ring. Each of the plurality of ring supports includes a support portion and a pivot portion about which the ring support selectively pivots. The support portion is adapted for engagement with the outer surface of the flexible ring.

Abstract: A method and apparatus for providing a portable source of air flow. The apparatus provides a base on casters, a support member coupled to the base, and a panel connected to the support member. The panel comprises at least one plate containing a plurality of apertures to expel air traveling from the blower. The panel position is adjustable relative to the base and the apparatus is free-standing and portable. The device is effective for people in need of a constant air source. The mobility allows the device to move with the person as he or she gets dressed, returns to bed rest, or simply desires a controlled temperature while walking into another room. The device can be positioned directly next to an individual, or if necessary positioned above. The adjustable panel position allows the panel to have directional air flow in ways not possible with conventional air systems.

Abstract: A reservoir groove for storing condensate water is formed on a lower part side of a link chamber inside a turbine housing. The reservoir groove is formed such that, assuming that water vapor contained in an exhaust gas retained inside the link chamber is completely condensed and liquefied after an engine stops its operation, a height position of a reference water surface of the condensate water stored in a reservoir area, which includes a space inside the reservoir groove in the link chamber, is lower than a height position of a lowermost part of the link mechanism.

Abstract: A method for removing a twin-spool turbine including a front fan, a HP module with a HP rotor, and a LP turbine module, an intermediate casing including a support bearing for the HP rotor, the HP rotor being retained in the bearing by a link nut, the method including inserting a tool for unscrewing the link nut after having released access to the link nut, and preheating the link nut before starting the unscrewing tool.

Abstract: A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.

Abstract: This invention relates to a Dry Running Flexible Impeller Pump and Method of Manufacture designed to provide a flexible impeller pump capable of being run dry for extended periods of time without damage. The pump's components are comprised of low friction materials limiting the heat of friction created by the impeller in use. The impeller is cast of pre-molding silicone substrate containing a quantity of mold release that will not prevent the deposition of a low friction compound coating on the surface of the impeller in a mold that is treated with a low friction industrial coating. Once the impeller is removed from the mold it is solvent cleaned, vacuum baked at a temperature high enough to drive off residual traces of mold release or compounds used to maintain the silicone substrate in suspension, and then coated with a polymer of Poly Para Xylylene by vacuum deposition.

Abstract: A hydraulic rotary actuator including a stator housing having a through bore to position a rotor assembly. A rotor assembly includes an output shaft and at least a first rotary piston member disposed radially about the output shaft. The rotary piston member includes an vane element. A continuous seal is disposed on peripheral longitudinal faces and lateral end faces of the rotary piston element. The bore through the stator housing includes an interior cavity with surfaces adapted to receive the rotor assembly and contact the continuous seal. With rotation fluid ports blocked, the housing cavity is sealed with the continuous piston seal for hydraulic blocking, preventing actuator displacement by external forces. A method of operation and method of assembly is disclosed.

Abstract: Separation device comprising a swirler (1, 20, 30) of a sheet material comprising a plurality of vanes (4) with a flow entrance side edge (6) defining an entrance angle (?) and a flow exit side edge (8) defining an exit angle (?). The flow entrance side edge and flow exit side edge extend from a center section (3) to a peripheral edge (9), which extends between end points of the flow entrance edge and the flow exit edge. The entrance angle is larger than the exit angle. The swirler can me made from a blank (10) by cutting out cutting lines defining the peripheral edges, the flow entrance edges and flow exit edges of a plurality of vanes (4) of a swirler. The vanes are subsequently bent to define the exit and entrance angles. Optionally, the swirler can be stacked with one or more correspondingly cut and bent swirlers to form a single stacked swirler (20, 30).

Abstract: A sealing device between two axisymmetric coaxial parts, includes an elastic segment, two holding elements located on each side of the annular segment, an annular spacer arranged between the two holding elements, wherein the annular spacer has a notch around its peripheral rim; the annular elastic segment has a hooking element at each of its free ends, adapted to cooperate with the notch of the annular spacer, and to hold the elastic segment in a pre-holding position by elastic return force.

Abstract: A diffuser for an air cycle machine defines airflow both to a compressor rotor from the inlet and from the compressor rotor through a plurality of vanes that define radially extending airflow passages. The size and shape of both the inlet and the vanes of the diffuser define and tailor the character of airflow presented to and leaving the compressor rotor to provide a desired change in air flow.

Abstract: A drill powered pump is provided. The pump includes a housing, an impeller mounted within the housing and a pair of bushings that support opposite ends of the support shaft of the impeller. The bushings are carried by the housing. Anti-rotation arrangements are provided to prevent rotation of the bushings relative to the housing.

Abstract: The present invention relates to a rotary motor, comprising a plurality of vanes, an inner rotary member housing the plurality of vanes projecting from a central rotation axis of the inner rotor, a multi lobe member encompassing the inner rotary member and the plurality of vanes, where the multi lobe member comprises at least two lobes wherein each of the lobes comprises an inlet and an outlet for a working medium, and a plurality of chambers wherein each of the chambers is encompassed by an inner surface of the multi lobe member and an outer surface of the inner rotary member. Such devices in accordance with some embodiments of the invention provide that a plurality of inlets and outlets amplify the output torque of the motor, that any side load is absent or minimized, and that a faster and stronger rotational force is achieved compared to a conventional hydraulic motor having a single pair of inlet and outlet.

Abstract: A vacuum pump has a working space, a bearing space, a dividing wall arranged between the working space and the bearing space and at least one rotor shaft which extends through the dividing wall and which forms a gap with the dividing wall and having a blocking device for blocking between the working space and the bearing space. The blocking device is formed by a Siegbahn pump stage which is configured for providing a pump action passing through the gap between the working space and the bearing space.

Abstract: A system includes a multi-stage turbine that includes a first turbine stage having a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel. The turbine also includes a second turbine stage having a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel. The turbine also includes a seal assembly extending axially between the first and second turbine stages. The seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first air director. The seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate comprises a second air director. The seal assembly also includes an interstage seal. The first coverplate, the second coverplate, or both are configured to support the interstage seal.

Abstract: A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage with a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage with a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal assembly extending axially between the first and second turbine stages. The interstage seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first seal. The interstage seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate includes a second seal. The interstage seal assembly also includes a spacer wheel extending from a rotor shaft and configured to engage with the first coverplate and the second coverplate.

Abstract: A controller for varying flow rate of a fluid from a fixed displacement pump is provided. The controller includes a pump speed control gear set, a ratio control pump, and a relief valve. The pump speed control gear set includes a sun gear configured to be driven by a prime mover, a planet carrier including one or more planet gears meshed with the sun gear, and a ring gear meshed with the planet gears. The ring gear is configured to connect to an input shaft of the fixed displacement pump. The ratio control pump includes a stationary body, and a rotor coupled to the planet carrier of the pump speed control gear set. The rotor is configured to co-act with the body to pump fluid. The relief valve is connected to the ratio control pump and configured to restrict fluid egress from the ratio control pump.

Abstract: According to one embodiment, a rotary compressor includes a compressing unit provided with a cylinder having a flared portion to provide a vane groove. In the compressing unit, a piston revolves along a cylinder inner wall, and an operation chamber is formed between the cylinder inner wall and the piston. A vane protrudes from the vane groove into the operation chamber and comes in contact with the annular piston to partition the operation chamber into an inlet chamber and a compression chamber. A spring inserted in a spring hole formed in the back of the vane groove presses the back of the vane. A spring holder pin is inserted in a pin hole located on the outer circumferential side of an end of the vane groove and crossing the spring hole to prevent the spring from coming off the spring hole when the compressing unit is installed in the housing.

Abstract: Techniques are generally described for a progressive cavity pump and a methods for making and using a progressive cavity pump. In an example, a progressive cavity pump may include a stator, a rotor and/or a bearing. The stator may include a helical shaped interior with a first pitch. The rotor may be inside the stator. The rotor may include a helical shaped exterior with a second pitch. The second pitch may be different from the first pitch. The rotor may be effective to rotate with respect to the stator and effective to move eccentrically within the stator to define at least one cavity inside the stator. At least one bearing may be between the rotor and the stator. The bearing may be sized and shaped so that the rotor is effective to rotate inside the bearing and the bearing is effective to move eccentrically along with the rotor.

Abstract: A pump insert (50) for supporting a rotor (14) of a pump comprises an annular resilient support (52) for engaging the body (26) of the pump, the support (52) extending about a rolling bearing (10) having an inner race (12) for engaging the rotor (14), an axially preloaded outer race (16) fixed to the support (52), and a plurality of rolling elements (18) located between the races. During assembly, the rolling bearing (10) can be accurately positioned within the support (52) so that there is a very low tolerance stack-up when the insert (50) is fitted to the rotor (14). Consequently, the position of the rotor (14) will hardly change, if at all, when the rolling bearing (10) is replaced during servicing of the pump.

Abstract: A protective housing is provided for a heating, ventilation, and air conditioning (HVAC) unit having a fan therein. The fan comprises a plurality of blades, each blade having a proximal and distal end. The housing comprises a plurality of side panels, each side panel comprising openings enabling airflow into the housing. The housing further comprises an access panel that is coupled between two of the plurality of side panels wherein the access panel and the plurality of side panels form an enclosure. An orifice ring is mounted within the housing, wherein a running clearance between the distal end of the fan blades and the orifice ring has a first spacing. A cover fastens atop the enclosure, the cover comprising a grill having a plurality of grill members, wherein the grill members are separated by a second spacing, the second spacing being smaller than the first spacing.

Abstract: A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of radially extending fan blades integral with the hub to form an integrally bladed rotor. Each fan blade defines a leading edge. A hub radius (RHUB) is the radius of the leading edge at the hub relative to a centerline of the fan. A tip radius (RTIP) is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is at least less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than or equal to 0.25.

Abstract: The present invention relates to a balancing body (1) for fastening to a ring (4, 5) of a continuous blade arrangement of a compressor or turbine stage of a gas turbine, wherein the balancing body has a first stop (11) for the form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder (6; 7) of the ring.

Abstract: A low pressure turbine, in particular for a gas turbine engine, extends along an axis, has an annular conduit for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the advancement direction of the gas flow, has a plurality of blades, which define a plurality of spaces between them in circumferential direction; the spaces are split by respective splitters into a radially outer conduit and into a radially inner conduit; the radial position of the splitters is in the neighborhood of a radial reference position such that at least one acoustic mode is of the cut-on type in the radially inner conduit.

Abstract: A compressor that includes a rotor assembly, a stator assembly and a heat sink assembly. The rotor assembly includes a shaft to which a bearing assembly and a rotor core are secured. The heat sink assembly is then secured to the bearing assembly and to the stator assembly.

Abstract: The invention relates to a fluid pump, in particular to a liquid pump having a rotor with at last one rotor blade for conveying the fluid, the rotor being variable with respect to its diameter between a first, compressed state and a second expanded state. In order to produce a simple compressibility and expandability of the rotor of the pump, it is provided according to the invention that at least one rotor blade is deformable between a first state which it assumes in the compressed state of the rotor and a second state which it assumes in the expanded state of the rotor by means of a fluid counterpressure during a rotation of the rotor during pump operation.

Abstract: A valve timing adjusting device for and engine includes a sprocket configured to rotate by receiving drive power from a driving shaft, a vane rotor fixed to a driven shaft so as to be rotatable relative to the sprocket, a housing that includes an oil chamber housing the vane rotor and is fixed to one end in a thickness direction of the sprocket, a bolt fixing the sprocket to the housing, and a knock pin inserted into a sprocket hole formed in the sprocket at one end thereof and into a housing hole formed in the housing at the other end thereof to restrict relative relation between the sprocket and the housing. The knock pin abuts against an inner wall of the sprocket hole at one end thereof, and abuts against an inner wall of the housing hole at the other end thereof.

Abstract: A supersonic compressor rotor that includes a rotor disk that includes a substantially cylindrical endwall, a radially inner surface, and a radially outer surface. The endwall extends between the radially inner surface and the radially outer surface. A plurality of vanes are coupled to the endwall. The vanes extend outwardly from the endwall. Adjacent vanes form a pair and are spaced a circumferential distance apart such that a flow channel is defined between each pair of circumferentially-adjacent vanes. The flow channel extends generally radially between an inlet opening and an outlet opening. A first supersonic compression ramp is coupled to the endwall. The first supersonic compression ramp is positioned within the flow channel to facilitate forming at least one compression wave within the flow channel.

Abstract: Vane pump mechanical losses are reduced by removing vane friction losses and replacing them with lower magnitude journal bearing fluid film viscous drag losses. A freely rotating cam ring is supported by a journal bearing. A relatively low sliding velocity is imposed between the cam ring and the vanes). This permits the use of less expensive and less brittle materials in the pump by allowing the pump to operate at much higher speeds without concern for exceeding vane tip velocity limits.

Abstract: A synchronizing assembly for a gas turbine engine has a synchronizing ring. A bumper assembly has a cradle and a bumper held within the cradle. The cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper. An engine is also disclosed.

Abstract: A wind turbine includes a tower having an interior, an exterior, a lower end and an upper end; a nacelle coupled to the tower adjacent the upper end and movable to define at least two yaw positions of the nacelle; a rotor coupled to the nacelle; and an access apparatus disposed about the tower adjacent the upper end thereof, the access apparatus defining a passageway into the nacelle that is exterior of the tower, and the access apparatus providing access to the nacelle in the at least two yaw positions of the nacelle. A method for transporting equipment and personnel to the nacelle using the access apparatus is disclosed. A method for assembling a wind turbine having such an access apparatus is also disclosed.

Abstract: Provided is a compression system including: at least one impeller; a gear train configured to the at least one impeller; a main drive shaft configured to drive the gear train; and a housing comprising an impeller container configured to house the at least one impeller and a gear train container configured to house the gear train.

Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.

Abstract: In one aspect, a motor assembly is provided. The motor assembly includes a fan housing having an air inlet and an air outlet, and a motor coupled to the fan housing and positioned within the air inlet. The motor includes a first end, a second end, and a shaft. The motor assembly further includes a fan coupled to the shaft proximate the motor second end. The motor first end includes a contoured surface having a stagnation point and a plurality of points along the contoured surface downstream of the stagnation point.

Abstract: A system may include a blade track or blade shroud and a gas turbine blade that includes a blade tip. The blade track or blade shroud may include a substrate and an abradable layer formed over the substrate. The abradable layer may include at least one of zirconia or hafnia; ytterbia; samaria; and at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia. The abradable layer may include a porosity between about 25 vol. % and about 50 vol. %. The blade track or blade shroud and the gas turbine blade may be configured so the blade tip contacts a portion of the abradable layer during rotation of the gas turbine blade, and the abradable layer may be configured to be abraded by the contact by the blade tip.

Abstract: An anti-torsion assembly for positioning and securing a thermally conforming liner within a fan containment case is provided. The anti-torsion assembly minimizes the amount of machining that must be done prior to assembly. The anti-torsion assembly comprises a torque block with outwardly-opposing side surfaces and a pair of L-brackets. Each L-bracket has a bracket surface that faces one of the outwardly-opposing side surfaces of the torque block. A wear pad is affixed to each bracket surface. The L-brackets are positioned onto the thermally conforming liner using a spacer having a spacer width within a predetermined tolerance. A method of assembling a fan case assembly is also provided.

Abstract: Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.

Abstract: To provide a method of setting a performance characteristic of a pump for setting a performance characteristic of a pump, the pump including an impeller that takes in fluid from a suction port and that sends out the fluid toward a discharge port, and a diffuser provided in a flow passage between the impeller and the discharge port, where the diffuser includes a hub arranged in a central portion of the flow passage, a shroud arranged around a periphery of the hub, and a plurality of diffuser vanes radially arranged from an outer peripheral surface of the hub toward an inner peripheral surface of the shroud, and the method includes a mounting-position setting step of setting a mounting position of each of the diffuser vanes to be mounted on the hub according to the performance characteristic of the pump in a direction perpendicular to a radial direction extending from the hub toward the shroud.

Abstract: The compressor includes a first constituent element and a first slider. The first constituent element is capable of being laser welded. The first slider is composed of cast iron capable of being laser welded and having a carbon content of from 2.0 wt % or more to 2.7 wt % or less. This first slider is joined to the first constituent element by laser welding without using a filler.

Abstract: There is disclosed a rotary compressor which delays a pressure rise on a high pressure chamber side in a cylinder of a rotary compression element to decrease a high pressure load applied to a roller and a rotary shaft, thereby improving performance. In the rotary compressor including a sealed container in which an electromotive element (a driving element) and first and second rotary compression elements driven by a rotary shaft of the electromotive element are included, each of the rotary compression elements being constituted of a cylinder, a roller fitted into an eccentric portion formed on the rotary shaft to eccentrically rotate in the cylinder, and a vane which abuts on the roller to partition the inside of the cylinder into a low pressure chamber side and a high pressure chamber side, the inner diameter of a suction passage formed in each cylinder is 59% or more and 70% or less of the thickness of the cylinder.

Abstract: An assembly for increasing air flow to a vehicle cooling system includes a portion of a cooling fan shroud, the portion having a face defining an opening therethrough, and a plurality of support members extending from the face. A flap includes a plurality of apertures proximal to an edge. Each aperture of the plurality of apertures is formed to receive one of the plurality of support members for coupling the flap thereto. A clearance fit formed between the apertures and the support members permits movement of the flap from a first position generally parallel to the face to a second position in response to a flow of air.

Abstract: A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core engine section includes a primary nozzle including a primary outer diameter at a primary nozzle trailing edge and a primary maximum inner diameter forward of the primary trailing edge. A bypass passage is defined between an inner nacelle surrounding the core engine section and an outer nacelle and includes a secondary nozzle. The secondary nozzle includes an outer diameter at a secondary nozzle trailing edge and a secondary maximum inner diameter forward of the secondary trailing edge. A ratio between the maximum inner diameter of the primary nozzle and an outer diameter at the trailing edge of the primary nozzle and a ratio between the maximum inner diameter of the secondary trailing edge and the outer diameter at the trailing edge of the secondary nozzle are both less than about 0.700.

Abstract: Disclosed is a gas turbine engine configured to include a propulsor section having a fan drive geared architecture. The gas turbine engine includes a gas generator section that includes a compressor section having a first rotor rotationally mounted to a first spool. The engine further includes a bearing package adapted for rotationally supporting the first spool. The bearing package is configured for supporting the first rotor during at least one of (1) a period prior to installation of the fan drive geared architecture into the engine and (2) a period after removal of the fan drive geared architecture from the engine.