Abstract: A fan assembly includes a fan body, a motor-driven impeller contained within the fan body and arranged to generate an air flow, a nozzle including a nozzle body having an air inlet arranged to receive the air flow from the fan body, and one or more air outlets arranged to emit the airflow from the fan assembly. The fan assembly further includes a nozzle retaining mechanism for releasably retaining the nozzle on the fan body, and a rotation mechanism for rotating the nozzle body relative to the fan body. The nozzle rotation mechanism includes a rotation motor arranged to drive a drive member and a driven member that is arranged to be driven by the drive member to rotate around a rotation axis.

Abstract: A fan and a cleaning apparatus. The fan comprises: a fluid module for generating and guiding an airflow, the fluid module comprising a diffuser which has a first positioning mechanism; and a stator module detachably connected to the diffuser, the stator module being provided with a second positioning mechanism adaptive to the first positioning mechanism. The fan uses a modular structure, is simple to assemble, and is suitable for mechanical production.

Abstract: A guide blade (200) for a guide device (100), including a guide blade body (201) with a blade top side (210), a blade underside (220), a blade leading edge (230) and a blade trailing edge (240). The guide blade (200) also comprises a profile centerline (250) which is defined in a profile of the guide blade body (201) by the blade top side (210) and the blade underside (220) and runs between them from the blade leading edge (230) to the blade trailing edge (240), the profile centerline (250) having a turning point (IP). The blade leading edge (230) and the blade trailing edge (240) are connected by a profile chord (260). The guide blade (200) has a guide blade axis of rotation (PA). The axis of rotation (PA), starting from the blade leading edge (230) in the direction of the blade trailing edge (240), lies along the profile chord (260) between the blade leading edge (230) and the turning point (IP).

Abstract: A novel emissions control watercraft (STAXcraft) solving a long-felt but unsolved need regarding disadvantages associated with prior-art emissions servicing watercraft, the disadvantages selected from the group, but not limited to, the use of tugboats, securing or mooring servicing watercraft to a serviced vessel, additional expenses and time-delays and inefficiencies of land-based approaches, increased toxic emissions, increased greenhouse gases (GHG) emissions, danger from falling cargo, tanker safety, alongside mooring in narrow channels preventing other OGV's to pass safely, and cargo tank emissions.

Abstract: This stationary blade segment includes a first stationary blade, a second stationary blade, and a connecting implement that connects the first stationary blade and the second stationary blade. A first shroud of the first stationary blade includes a first gas path face, and a first protruding part that protrudes to a reverse-channel side at a first end section of the first shroud. A second shroud of the second stationary blade includes a second gas path face, a second protruding part that protrudes to the reverse-channel side at a first end section of the second shroud, and a third protruding part that protrudes to the reverse-channel side at a second end section of the second shroud and that is connected to the first protruding part by the connecting implement.

Abstract: Various connection units are disclosed. The connection unit can be configured to straighten a flow of air, such as to reduce the distance before the flow of air becomes substantially laminar. The connection unit can include a drag reduction unit. The drag reduction unit can be configured to redirect airflow to the center of the connection unit. The connection unit can include a wake diverting component configured to lift air away from the periphery of the connection unit and/or redirect the airflow towards a radial center connection unit.

Abstract: Tip shrouds or other shrouds with multi-slope geometries are generally implemented using segments, since performing the necessary cut for an alternative split-ring design is difficult given conventional cutting processes. However, a segmented design generally results in more leakage, relative to a split-ring design. Accordingly, a split-ring multi-slope design is disclosed that can be more easily manufactured. In particular, a continuous ring may be cut along a linear path to produce a split ring, and then the ends of the split ring may be machined to form complementary shiplap portions. The split ring may then be compressed for installation by overlapping the shiplap portions, to form a seal against leakage through the shroud.

Abstract: An outlet guide vane assembly in a gas turbine engine is presented. The outlet guide vane assembly includes an inner shroud and an outlet guide vane having an inner platform. The inner shroud has a flange arranged at aft side that is bolted to a flange of the inner platform arranged at forward side. The inner shroud flange has a protrusion that engages a recess of the inner platform flange forming a form fit connection interface between the inner shroud and the outlet guide vane. The inner platform has shiplaps arranged at two circumferential sides that overlap shiplaps of an adjacent inner platform forming a form fit connection interface between adjacent outlet guide vanes. The outlet guide vane assembly includes a plurality of segments circumferentially arranged. Each segment includes a plurality of outlet guide vanes assembled to an inner shroud.

Abstract: There is provided a fan assembly comprising a fan body, a motor-driven impeller contained within the fan body and arranged to generate an air flow, a nozzle comprising a nozzle body having an air inlet arranged to receive the air flow from the fan body and one or more air outlets arranged to emit the airflow from the fan assembly. The fan assembly further comprises a nozzle retaining mechanism for releasably retaining the nozzle on the fan body, and a rotation mechanism for rotating the nozzle body relative to the fan body. The nozzle rotation mechanism comprises a rotation motor arranged to drive a drive member and a driven member that is arranged to be driven by the drive member to rotate around a rotation axis, wherein the nozzle body comprises the driven member and the fan body comprises the rotation motor and the drive member.

Abstract: Provided is a wind power generation system including: a wind power generation apparatus that includes at least a duct having a longitudinal cross section formed in a substantial streamline shape, the longitudinal cross section being cut along a central axis, an impeller placed in the duct, and a power generator that generates power by rotation of the impeller; an anemovane installed so as to be able to measure a wind direction and/or wind power in a vicinity of the wind power generation apparatus; a rotating pedestal that supports the wind power generation apparatus so as to be rotatable along a supporting surface; and a control device that controls a rotational angle of the rotating pedestal based on the wind direction and/or the wind power measured by the anemovane.

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

Abstract: An airfoil incudes an airfoil section that defines an internal cavity. The airfoil section is formed of a fiber-reinforced composite that is comprised of fiber plies. The fiber plies include core fiber plies and an overwrap fiber ply that wraps around the core fiber plies. The core fiber plies are arranged as first and second tubes. each of the first and second tubes defines a plurality of windows therein. The windows of the first tube align with the windows of the second tube so as to form radially-spaced ribs that extend across the internal cavity. At least one of the first or second tubes has at least one tab that is radially between the radially-spaced ribs. The at least one tab interlocks the first and second tubes.

Abstract: An optical analysis device for determining particulate matter includes three light sources having different wavelengths, an apparatus for combining the three transmitted light beams on a common optical path, a measurement volume, an optical axis in the forward scattering direction that defines the scattering angle 0°, a light absorption apparatus at 0° that absorbs unscattered light, and six detectors arranged at different specified angles which are as close as possible to 0° directly next to the light absorption apparatus, at a second scattering angle between 7° and 40°, at a third scattering angle between 41° and 70°, at a fourth scattering angle between 71° and 115°, at a fifth scattering angle between 116° and 145°, at a sixth scattering angle between 146° and 180°. A control and evaluation unit controls the light sources such that the scattered light is detected in a wavelength selective manner by the detectors.

Abstract: In a vacuum pump, an outer diameter of a spiral plate disposed on a downstream side is set smaller than an outer diameter of a spiral plate disposed on an upstream side. Specifically, a stepped portion is provided by setting a blade length of the spiral plate disposed on the downstream side shorter than a blade length of the spiral plate disposed on the upstream side. In addition, in a spacer provided in the stepped portion, a relief formation portion is provided to allow a contact surface in contact with an upstream spacer (i.e., spacer opposed to the spiral plate having the unreduced outer diameter) and a contact surface in contact with a downstream spacer (i.e., spacer opposed to the spiral plate having the reduced outer diameter) in the stepped portion to have an equal inner diameter.

Abstract: A stator wheel of a turbomachine configured to be mounted in an aircraft, the turbomachine extending along an axis, the turbomachine comprising a core flow stream for a first air flow and a bypass flow stream for a second air flow, wherein the stator wheel is configured to be mounted along the axis, the stator wheel comprising a plurality of vanes extending radially from the axis, each vane comprising a leading edge and a trailing edge that together define a chord in a plane of revolution defined relative to the axis, at least two vanes having different chords at a same radial distance, the difference in chords between two adjacent vanes being less than or equal to 25%.

Abstract: A method and apparatus for breathing, in which a blower is mounted in a specific part made of silicone, which reduces blower immissions and emissions. Moreover, the conducting structure influences the flow of the respiratory gas in order to reduce interference when measuring the volumetric flow.

Abstract: A rotation driving device includes: a casing; a stator holding part; a cylindrical member; a flange extending from an end of the cylindrical member in the axial direction toward a rotating shaft, and facing an end of the stator holding part in the axial direction; and a fastening member fastened to the end of the stator holding part in the axial direction via the flange. The flange has a through-hole extending through the flange in the axial direction, and in which the fastening member is inserted. The through-hole has a diameter smaller than that of a head of the fastening member, and larger than that of a screw part of the fastening member. The rotating shaft, the rotor, the stator, the stator holding part, and the cylindrical member are arranged in this order in the radial direction in the casing, and are concentrically arranged.

Abstract: An encased wind turbine has a casing, rotationally symmetrical in relation to the longitudinal axis and has the cross-section of an airfoil. The radially inner upper side delimits a flow channel. A guide element is rotationally symmetrical in relation to the longitudinal axis projects by part of its length, contrary to the direction of flow, over the casing. The propeller drives a generator, arranged in the housing, for generating electrical energy. The propeller viewed in the direction of flow, is located at least approximately at the guide-element trailing edge. Impinged on by the main flow of the wind, while a bypass flow, owing to the airfoil profile, generates a negative pressure downstream from the guide element and thus accelerates the main flow, is generated between the casing and the guide element. The propeller may be located downstream from the guide element and arranged to be adjustable in its longitudinal position.

Abstract: A method of assembling a portion of a gas turbine engine, includes assembling a plurality of static structure rings; attaching a plurality of support straps to an outer diameter of the plurality of static structure rings to form a cartridge; inserting the cartridge at least partially into an outer case assembly along an engine axis.

Abstract: A variable vane assembly for a gas turbine engine, the variable vane assembly including: a plurality of vanes arranged into a plurality of stages, each one of the plurality of vanes being configured for rotation about an axis through movement of a vane arm secured to each one of the plurality of vanes at one end and a sync ring of each one of the plurality of stages at another end; and a plurality of bell cranks operably coupling the sync ring of each one of the plurality of stages to a self-retained linkage via a stud of each one of the plurality of bell cranks, the stud of each one of the plurality of bell cranks being rotatably received in a corresponding opening of the self-retained linkage in an alternating fashion such that only a single shear interface is provided between each one of the plurality of bell cranks and the self-retained linkage.

Abstract: A diffuser-augmented wind turbine may include an annular diffuser that may encompass a rotor such that the rotor and the annular diffuser may be coaxial about a main axis. A diffuser-augmented wind turbine may further include a flared diffuser assembly that may be connected to the annular diffuser such that an air stream discharged from the annular diffuser may enter the flared diffuser assembly. A flared diffuser assembly may include a fixed flared diffuser that may include a number of flared petals extending from a leading edge of the fixed flared diffuser toward the trailing edge thereof. A flared diffuser assembly may further include a rotatable flared diffuser that may be disposed coaxially within the fixed flared diffuser and rotatable about the main axis. A rotatable flared diffuser may include a number of flared petals extending from an annular leading edge of the rotatable flared diffuser toward a trailing edge thereof.

Abstract: An inflatable device, having an air flow path having a circumference and including an air diverter comprising a central motor receiver and a plurality of air deflectors extending radially from the motor receiver and located to define a plurality of air flow chambers surrounding the motor receiver; a motor mounted within the central motor receiver and having an output shaft rotatable by the motor and extending below the air diverter, the motor generating heat during use of the motor; a fan connected to the output shaft of the motor and located below the air diverter for rotating in response to rotation of the output shaft by the motor to generate a flow of air, the air diverter cooperating with the flow of air generated by the fan to create a turbulent air flow directed to flow through the air flow chambers and past the motor, the flow of air providing cooling to dissipate heat from the motor; and an inflatable body in flow communication with the air flow path and located above the air diverter for receiving t

Abstract: A return stage through which a process fluid is designed to flow along a throughflow direction of a radial turbomachine, wherein the return stage extends in annular fashion about an axis and is defined radially inwardly by an inner delimiting contour and radially outwardly by an outer delimiting contour. At least one guide vane stage including guide vanes extends at least along a part of the third section and segments the return stage in the circumferential direction into flow channels, wherein in each case a profile midline of a profile cross section defines an inner track on the side of the inner delimiting contour and an outer track on the side of the outer delimiting contour. A radial turbomachine includes at least one such return stage.

Abstract: A diffuser for a compressor includes a body having a ring shape and including: a fluid inflow face extending along a radial direction of the diffuser; and a rim bent from the fluid inflow face; main vanes formed on the fluid inflow face and the rim to guide fluid; and at least one splitter vane disposed between adjacent main vanes of the main vanes to guide the fluid.

Abstract: A fan motor is provided that includes an inner housing having an inner space formed therein; a rotational shaft assembly supported in the inner housing and having a rotor and a bearing mounted on a rotational shaft thereof; a stator disposed to surround the rotor in the inner housing; an impeller connected to the rotational shaft; and an outer housing that surrounds an outer periphery of the inner housing and having an inlet body that guides air to the impeller. At least one heat dissipation vane is provided on an outer peripheral surface of the inner housing to guide air which passes between the inner housing and the outer housing after being suctioned into the inlet body, and thus, when being guided by the at least one heat dissipation vane, the air having been moved by the impeller may efficiently absorb heat transferred from the stator to the at least one heat dissipation vane and more stably flow than when colliding against the stator and the rotor, and thus, may be quickly discharged.

Abstract: A fan shroud, in which air flows from a suction port to an outlet port, includes: a bell mouth part having a circular wall, the outlet port being formed by the bell mouth part; and a rectangle part having a proximity wall located adjacent to the circular wall and a distal wall distant from the circular wall than the proximity wall, the suction port being formed by the rectangle part. The proximity wall has a most close area that is most close to the circular wall. The circular wall has an extended wall part extended in an axial direction of a propeller fan than a residual portion of the circular wall. The extended wall part is provided along a rotational direction of the propeller fan from a position opposing the most close area.

Abstract: A flow path includes a return bend portion which guides a working fluid to an inside in the radial direction by reversing the working fluid discharged to an outside in a radial direction from an upstream-side impeller, and a guiding flow path which is connected to a downstream side of the return bend portion and leads the working fluid to the inside in the radial direction so as to guide the working fluid to the downstream-side impeller. In a return vane which is provided in the guiding flow path, a trailing edge is formed such that a second end portion on a second side in an axial direction is positioned closer to an inside in a radial direction than a first end portion on a first side in the axial direction.

Abstract: The present disclosure concerns an assembly of a turbomachine or of a combustion chamber test bench, generally including an annular outer housing, inside which a combustion chamber is housed, and a ferrule downstream from the housing. The ferrule may be attached to said housing by a connection comprising a radial flange rigidly connected to one of the housing and the ferrule, an annular groove being provided in the radial flange, and an axial tab rigidly connected to the ferrule or to the housing. The tab is generally housed in the groove, and the tab and the annular groove may be arranged relative to each other in such a way that, at assembly, they are in contact and centered relative to each another.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.78-0.91 inch (19.7-23.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.49-0.62 inch (12.5-15.6 mm). The airfoil element includes at least two of a first mode with a frequency of 3533±15% Hz, a second mode with a frequency of 8291±15% Hz, a third mode with a frequency of 17362±15% Hz and a fourth mode with a frequency of 23365±15% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.55-0.65 inch (14.0-16.5 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.76-0.86 inch (19.3-21.8 mm). The airfoil element includes at least two of a first mode with a frequency of 3335±10% Hz, a second mode with a frequency of 5715±10% Hz and a third mode with a frequency of 41797±10% Hz.

Abstract: An inter-compressor case for a gas turbine engine is disclosed. The inter-compressor case comprises: an outer casing and an inner casing radially spaced apart relative to a longitudinal axis; a gas path extending from a plurality of radial inlets arranged in a circumferentially spaced apart array around the outer casing to an annular outlet defined by an axially extending downstream portion of the outer casing and an axially extending downstream portion of the inner casing; a plurality of struts having a gas path surface extending across the gas path between the outer casing and the inner casing; and a plurality of flow separators extending from the adjacent radial inlets. The flow separators have trailing edges disposed upstream of the annular outlet and include a plurality of full length flow separators and a plurality of truncated flow separators.

Abstract: An apparatus 100 for conducting chemical reactions in a process fluid is provided, comprising a central shaft 1 with a number of axial-radial rotors 3 mounted thereon, a plurality of stationary vanes 2 disposed upstream the rotor and a mixing space 4 disposed downstream of the rotor, wherein the mixing space is configured to convert mechanical energy imparted to the process fluid by the rotor into internal energy of said process fluid and to establish conditions for an at least one chemical reaction in the process fluid to occur. Related arrangement, method and uses of the apparatus are further provided.

Abstract: An air blowing device includes a motor, a ring-shaped cover, an impeller, and an impeller housing. The impeller includes a base portion and moving blades. The impeller housing includes an exhaust air guide portion. The ring-shaped cover includes a ring-shaped cover upper face portion and a ring-shaped cover outer edge portion having faces disposed across a gap that configures a flow path through which a fluid is guided. The gap has a first width where a distance between the faces is shortest, and which is smaller than a flow-in opening width where the fluid flows into the gap and a flow-out opening width where the fluid flows out.

Abstract: The present disclosure provides an exhaust diffuser for a gas turbine engine. The exhaust diffuser may include a hub, a casing, and a strut extending between the hub and the casing. The hub may include an angled configuration about the strut and a substantially flat configuration downstream of the angled configuration.

Abstract: A vane stage assembly includes an airfoil including a leading edge and a trailing edge. An inner shroud extends from the leading edge to the trailing edge for supporting the airfoil. The shroud includes a forward portion including an axial width and a forward thickness extending in a radial direction. A ratio of the forward radial thickness divided by the forward axial thickness is between 0.64 and 1.11 for defining a natural frequency of the airfoil. A gas turbine engine and method are also disclosed.

Abstract: A turbine section is provided for a gas turbine engine. The turbine section is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least a first splitter blade disposed within the inter-turbine duct. The first splitter blade includes a pressure side facing the shroud, a suction side facing the hub, and at least one vortex generating structure positioned on the suction side.

Abstract: The disclosure describes a flow conditioning device for dampening pulses and improving performance of a compressor. In one approach, a diffuser device includes a housing member having a first end and a second end, the housing member coupled to an outlet of a compressor, and a diffuser member disposed within the housing member. The diffuser member is in fluid communication with a working fluid delivered from the compressor, and includes a core member extending along a longitudinal axis of the diffuser member, and a plurality of flutes extending radially from the core member. In some approaches, the plurality of flutes and an inner surface of the housing define a plurality of fluid channels for delivering the working fluid from the first end to the second end of the housing member. In some approaches, the diffuser member is rotatably coupled to the housing member.

Abstract: A propeller fan includes a rotary blade hub driven in rotation about a rotation axis, and a rotary blade installed at an outer periphery of the rotary blade hub. The rotary blade includes a rotary blade body protruding from an outer peripheral surface of the rotary blade hub, and a rib formed on an outer peripheral edge portion of a pressure surface of the rotary blade body so as to extend along an outer peripheral edge of the rotary blade body.

Abstract: A turbine power unit for a power tool having a turbine housing with an interior space configured to receive therein a fluid powered turbine supported for rotation on a bearing within the turbine housing. A service opening through the turbine housing into the interior space thereof, the service opening configured to permit installation and removal of a bearing into and out of the interior space of the turbine housing. A removable cover releasably securable to the turbine housing over the service opening and transitionable between an open configuration in which a bearing can be installed into and removed from the interior space of the turbine housing through the service opening and a closed configuration in which an installed bearing within the interior space is secured for operation in the turbine housing.

Abstract: A contoured turbine airfoil assembly including an end wall (30a) formed by platforms (30) located circumferentially adjacent to each other, and a row of airfoils (34a, 34b) integrally joined to the end wall (30a) and spaced laterally apart to define flow passages (46) therebetween for channeling gases in an axial direction. A trough (62) is defined between a pressure side ridge (48) and a suction side ridge (58) located forward of each pair of airfoils (34a, 34b). Each trough (62) has a direction of elongation aligned to direct flow into the flow passage (46) centrally between each pair of airfoils (34a, 34b).

Abstract: A fluid flow turbine having a turbine rotor with a plurality of blades (also known as “vanes”) for converting the kinetic energy of a flowing fluid into mechanical rotational energy of the turbine rotor is provided by this invention. The plurality of blades are defined by a continuously sinuous curve outer edge that results in the lateral surface of the blades having a lower concave portion for scooping up the horizontal incoming fluid flow and redirecting it to a substantially vertical fluid flow along the lateral surface of the blade. The upper portion of the lateral surfaces of the blades is convex, causing the upper edge of the blades to tail off laterally so that the fluid flow exits the turbine in a substantially vertical direction, instead of turning back upon itself to reduces turbulence of the fluid flow inside the turbine. The fluid flow turbine can comprise a small wind turbine that will produce electrical power at low wind speeds, and can be mounted to the top of a building.

Abstract: A strut assembly for a bearing compartment of a gas turbine engine includes an inner case, an outer case, and a first plurality of struts. The inner case is disposed within the bearing compartment and includes a first axis. The outer case defines an exterior of the bearing compartment and includes a second axis disposed co-axially with the first axis. The inner and outer cases define a flowpath between the inner and outer cases. Each strut of the first plurality of struts extends between and is connected to the inner and outer cases. The first plurality of struts is configured to maintain concentric positioning between the inner and outer cases and to allow relative changes in size between the inner and outer cases without deforming the inner case.

Abstract: A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.

Abstract: A turbine engine is disclosed and includes an airflow passage including an inner surface defined by a main shroud and a shroud extension. A flow splitter is disposed radially outward of the inner surface and axially overlapping the shroud extension. The turbine engine further includes a rotor including a blade proximate the shroud extension and an annular gap defined between the shroud extension and the blade of a first axial length less than a second axial length between the blade and an end of the flow splitter.

Abstract: A case assembly for a gas turbine engine comprising annular case components each having a central axis. Radial struts each have a radial axis and intersect the annular case components. A stress dissipation mass projecting from a continuous surface of at least one of the struts at the intersection with a corresponding annular case component, the stress dissipation mass being on either side of a plane passing through the radial axis of the strut and the central axis of the corresponding annular case component. A method for dissipating thermal and mechanical stresses on a strut in a case assembly for a gas turbine engine is also provided.

Abstract: A series fan inclination structure includes an inclined frame body assembly, a first rotor assembly and a second rotor assembly. The inclined frame body assembly has a receiving space. The receiving space includes a first space, a second space and a flow guide passage. A first base seat is obliquely disposed in the first space. A second base seat is obliquely disposed in the second space. The flow guide passage is formed between the first and second base seats in communication with the first and second spaces. The first and second rotor assemblies are correspondingly rotatably disposed on the first and second base seats. The series fan inclination structure is able to greatly reduce the vibration and lower the noise caused by the interaction of the dipole.

Abstract: A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body, a bore defined in a radially inward portion of the disk body and configured to be radially adjacent to a shaft, and a thermal regulation aperture defined in the disk body, radially inward of the rim, for allowing flow to pass axially through the disk body when disposed in a stage of a turbomachine, and a thermal regulation aperture defined in the disk body for allowing flow to pass through the disk body when disposed in a stage of a turbomachine.

Abstract: A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.

Abstract: An axial-flow fan includes a boss and a plurality of blades integrally resin-molded with a hub. An axial hole of the boss has a shaft of a drive motor inserted. The axial hole is formed at an axial center of the hub. The hub includes an outer perimeter cylinder and a lid. The outer perimeter cylinder has an opening formed at the axial center, and the blades are formed so as to project from the outer perimeter cylinder. The lid extends from the outer perimeter cylinder toward the boss so as to cover the opening of the outer perimeter cylinder. The lid connects the boss and the outer perimeter cylinder together. Reinforcing ribs are integrally resin-molded together with the hub and the boss on both axial-direction sides of the lid. The reinforcing ribs reinforce the connection between the hub and the boss.

Abstract: A method for controlling an inlet-adjustment mechanism in an air inlet for a compressor so as to switch the mechanism in a binary fashion between two positions P1 and P2 for adjusting a flow area of the inlet. The method includes identifying a threshold line on a compressor map of pressure ratio versus corrected flow rate for the compressor. The threshold line is a line on which the pressure ratio and flow rate of the compressor are the same for the P1 and P2 positions of the inlet-adjustment mechanism at equal speeds. When the operating point of the compressor on the compressor map crosses the threshold line, the inlet-adjustment mechanism is switched from one of its binary positions to the other.