Abstract: A turbomachine component includes a body having a first end that extends to a second end. One of the first and second ends includes a mounting element, and a mounting component. A cover plate is arranged at the one of the first and second ends to establish an interface region. The cover plate includes a mounting member configured to align with the mounting element, and a mounting portion configured to align with the mounting element. A fastener member is configured and disposed to cooperate with the mounting element and the mounting member to constrain the cover plate to the body along at least two axes with the interface region being devoid of a metallurgical bond.

Abstract: The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure (4) comprising an inner panel (10) for surrounding a downstream part of the turbojet engine, an annular flow channel for a so-called secondary flow. The invention is characterized in that the exhaust means (11) are arranged in the inner panel in such a way that any inopportune surge is exhausted in the annular channel.

Abstract: During engine braking of a turbocharged internal combustion engine, the exhaust gas pressure increases and this is used to pressurize the seals between the turbocharger shaft and the bearing housing so as to prevent oil leakage into the compressor housing. Immediately after engine braking, stored exhaust gas pressure is used to pressurize the seals at the turbine end so as to prevent oil leakage into the turbine housing. In an alternative arrangement the exhaust gas is used to generate a reduced pressure in the bearing housing to increase the pressure gradient across the seals.

Abstract: Hydroelectric turbines in confined spaces depend heavily on nozzles and relationships involving nozzles and related turbine components in order to obtain maximal efficiencies for a wide range of flow conditions.

Abstract: A selective rotation arrangement for a shaft, the arrangement including a housing mountable spaced from the shaft and an engagement member with distal and proximal ends which is selectively movable relative to the housing towards or away from the shaft between an operating position towards the shaft and a rest position clear of the shaft, the engagement member having a gear member at the distal end thereof which is engageable with the shaft in the operating position to permit turning of the shaft by the engagement member, but is disengaged from the shaft in the rest position.

Abstract: A blower apparatus comprises a box-like main frame provided with a main-frame inlet port and a main-frame outlet port in positions confronting each other, and a plurality of centrifugal blower units for suctioning through a blower inlet port air taken inside of the main frame from the main-frame inlet port and discharging the air from a blower air outlet toward the main-frame outlet port. The main frame is provided with a maintenance opening in one of the surfaces other than the surfaces having the main-frame inlet port and the main-frame outlet port for the purpose of checking the inside of the main frame, and the plurality of centrifugal blower units are disposed one another in a direction toward the maintenance opening so that a difference in discharging spatial distances from the blower air outlets of the adjoining centrifugal blower units to the main-frame outlet port is equal to or greater than an outer diameter of an impeller of the centrifugal blower unit located nearest to the maintenance opening.

Abstract: A method and a device for counteracting wear from particle bearing drive water in a runner (4) in a water turbine (1), the runner (4) comprising a runner hub (16) and a vane (18), or a runner hub (16), a vane (18) and a runner band (20), the vane (18) being attached to the runner hub (16) in a first attachment area (22) and to the runner band (20) in a second attachment area (24), and where the method comprises: —routing a supply channel (40) for water cleaner than the drive water to at least the first attachment area (22) or the second attachment area (24) and—leading water cleaner than the drive water to flow over at least a portion of the vane (18) surface.

Abstract: A fan assembly includes a rack, a shield, and a fan. The rack defines a first vent opening and a second vent opening aligned with the first vent opening. The shield is mounted in the rack and aligned with the first vent opening. The shield defines a circular opening corresponding to the first vent opening. A plurality of shielding pieces are pivotally mounted in the circular opening. The plurality of shielding pieces together form a circular shield in themselves to cover the circular opening by gravity. The fan is mounted in the rack and aligned with the second vent opening and the shield. The fan blows air towards the plurality of shielding pieces and rotates the shielding pieces to define an air passage between each two adjacent shielding pieces. The air passage allows air to flow therethrough only when the fan is operating.

Abstract: Provided is a vane tip clearance management structure for a gas turbine which allows a vane tip clearance to be confirmed easily at the time of completing assembly. For this purpose, there are provided: a casing (3) rotatably supporting a rotor (2); stator vane retainer rings (11, 12, and 13) and a turbine vane ring (16) provided to have predetermined clearances from tips of rotor vanes (10 and 15) fitted in multiple steps to the rotor (2) inside in the radial direction of the casing (3); guide frames (26) penetrating the casing (3), the stator vane retainer rings (11, 12, and 13) and the turbine vane ring (16) in the radial direction and being supported by stepped portions (21a, 22a, 23a, and 24a); and rods (25) movably supported by the guide frames (26) and abutting on the tips of the rotor vanes (10 and 15). Clearances (C1 and C2) are measured based on the amounts of movement of the rods (25) relative to the guide frames (26).

Abstract: A device includes a resilient member having a first end for blocking an access hole and a second end for attachment to a support surface, an opening extending through the resilient member and located between the first and second ends, and a bolt connection location positioned at the second end of the resilient member. The first end of the resilient member blocks the access hole and can be deflected to provide tool access to the bolt connection location through the first opening.

Abstract: An underwater generator for generating electricity including: a casing, a turbine propeller assembly configured within the casing; a platform, where the platform provides a mechanism to hold the casing; a cover member, where the cover member protects the turbine propeller assembly; and a power cable for transmitting electrical energy from the underwater generator to a user thereof. The casing may include a slit at a bottom portion, where the slit allows the removal of sediments, sand particles and similar materials. The turbine propeller assembly includes a plurality of blades. In one exemplary embodiment, the blades may turn in two directions.

Abstract: A vane for a gas turbine engine includes a cap arrangement having a cap insert and a cap adapted to receive the insert. The cap insert has a wall defining a through passage from top to bottom of the cap insert for receiving a cable or the like therethrough. The wall has a slot with a convoluted profile.

Abstract: A method for cooling a component of a turbine is provided, wherein a fluid with a pressure below 1 bar is guided away from the component. Moreover, a turbine is described comprising a component, a conduit which is connected to the component so that a fluid can be guided away from the component, and a fluid discharge which is connected to the conduit. The fluid discharge is constructed so that it removes a fluid with a pressure below 1 bar.

Abstract: A system is provided that includes a turbo machine service assembly. The turbomachine service assembly includes a cover configured to couple with a port of a turbomachine. Additionally, the turbo machine includes a vane configured to guide a fluid flow along a fluid flow path in the turbomachine. A connection system connects the vane with the cover, and blocks movement of the vane relative to the cover in an axial direction, a radial direction, and a circumferential direction relative to a rotational axis of the turbomachine.

Abstract: A closure device for a casing having at least one access opening wherein the closure device includes a cover member movably disposed within an interior chamber of the casing so as to be slidably displaceable along or in the direction of a casing central axis between an open and a closed position, the cover member being spaced at least partially axially from the access opening in the open position so as to permit access to the interior chamber and generally extending across and substantially obstructing the at least one access opening in the closed position.

Abstract: A plug for an inspection hole of a gas turbine engine is disclosed. The plug may have a stem including a first shaft, wherein a first seal is located circumferentially about the first shaft. The plug may have a swivel seal including a second seal spaced from a ball by a second shaft, and the swivel seal may be rotatably connected to the stem by the ball. The ball and the second seal may be fixed to the second shaft.

Abstract: A slider seal assembly for a gas turbine engine includes a housing, a seal plate moveable relative to the housing and a retaining ring. The housing includes an outer surface, an inner surface, and a recessed opening between the outer surface and the inner surface. The seal plate is received within the recessed opening. The inner surface of the housing includes a curved portion which is curved in an outward direction toward the outer surface.

Abstract: The present invention relates to a pump arrangement (10) having a housing (12) and cover (14). The housing (12) and cover (14) form part of a pump mechanism (16). A first inlet or a housing inlet (26) is formed in the housing (12) and is connected to the pump mechanism (16). A second inlet or a cover inlet (28) is formed in the cover and is connected to the pump mechanism. The cover (14) also has a cover outlet (34) formed in the cover (14) that is connected to the pump mechanism (16) and is where fluid medium such as air flows out of the housing (12) arrangement. The use of two inlets increases the flow efficiency.

Abstract: A remote adjustment and measurement system for a steam turbine nozzle assembly is disclosed. In one embodiment, a steam turbine casing segment is disclosed including: a horizontal joint surface; a pocket having a first opening at the horizontal joint surface and a second opening facing substantially radially outward; and a port accessible from a radially outward surface of the steam turbine casing segment, the port fluidly connected to the second opening of the pocket.

Abstract: The present invention provides an omnidirectional wind collection apparatus. The wind collector includes an outer housing with a peripheral wind inlet circumferentially formed therein. An inner housing disposed within the outer housing has an inner surface with a first opening at a lower end thereof to guide the collected wind to a smaller second opening at the top end. The inner surface is curved between the bottom and top openings to form a progressively narrower passage. The configuration of the inner surface creates a Venturi effect such that the wind is accelerated toward the second opening. A wind pass-through portion is formed above the second opening in the inner housing. Based on the Bernoulli effect, the passage of uncollected wind through this portion creates a low pressure region that expedites flow of collected wind through the first and second openings of the inner housing.

Abstract: A turbomachine compressor, including an air bleed device including a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor is disclosed. A screen sheet of annular shape is mounted radially inside the casing facing a portion of the suction end of the duct so as to make the bleeding of air uniform over 360° around the axis of the compressor.

Abstract: An impeller device (10) for centrifugal fans (1), having comprising a center wheel (40), at least one side disc (20, 30) and fan blades (50). The center wheel (40) and the side disc(s) (20, 30) are equipped with attachment devices (24, 44) for attaching the blades and the center wheel's (40) attachment device (44) comprises a protrusion (45) extending substantially in the center wheel's radial direction and arranged to abut against the second side end (54) in the fan blades (50).

Abstract: Apparatus for the ventilation of a rotor hub of a wind energy plant, with a cup-shaped ventilation cap, which has a circumferential side wall and a base portion, wherein the side wall has at least one bore for draining water and the base portion has at least one bore for ventilation, a pipe-shaped connection piece, which has an air entrance opening which runs out into an interior space of the rotor hub, wherein the ventilation cap is arranged before the air entrance opening and the at least one bore for ventilation is arranged in the ventilation cap outside of the air entrance opening of the pipe-shaped connection piece such that the air entrance opening is covered up by the ventilation cap.

Abstract: A stacked pump arrangement for mixed-media flow includes a first, self-priming, centrifugal pump with a volute having an inlet and an outlet and a second straight centrifugal pump mounted to an upper portion of the first centrifugal pump, the second straight centrifugal pump also having a volute with an inlet and an outlet. A transition chamber is connected, at one end, to the first centrifugal pump volute outlet and is connected, at another end, to the second straight centrifugal pump volute inlet.

Abstract: An engine cooling fan shroud structure (20) for a vehicle includes a skirt (12?) defining a frame. The frame has a certain wall thickness and defines an opening (22) therein constructed and arranged to permit air to pass through the skirt. The skirt includes motor mount structure (14) supported in the opening and constructed and arranged for mounting a fan motor thereto. The frame defines passageways (18) there-through to reduce an amount of material of the skirt. A film material (28) has a wall thickness substantially less than the certain wall thickness and covers the passageways such that air may flow mainly through the opening.

Abstract: A stacked pump arrangement for mixed-media flow includes a first, self-priming, centrifugal pump with a volute having an inlet and an outlet and a second straight centrifugal pump mounted to an upper portion of the first centrifugal pump, the second straight centrifugal pump also having a volute with an inlet and an outlet. A transition chamber is connected, at one end, to the first centrifugal pump volute outlet and is connected, at another end, to the second straight centrifugal pump volute inlet.

Abstract: A bulkhead for a wind turbine is provided. The wind turbine includes a rotor hub and a rotor blade operatively attached to the rotor hub. The rotor blade includes a blade root. The bulkhead includes multiple access openings with closable hatches and is arranged in or on the blade root or in the area between the blade root and the rotor hub.

Abstract: A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area.

Abstract: A closure device for a compressor having at least one access opening, wherein the closure device includes a plug portion disposeable at least partially within and configured to substantially obstruct the at least one access opening, a head portion having a shoulder surface extending generally radially outwardly with respect to the plug portion, wherein the head portion is generally disposeable against an inner surface of the compressor and configured to maintain the plug portion disposed within the at least one access opening during compressor operation, and a retainer member having a bracket engageable with an outer surface of the compressor and a threaded rod extending between the bracket and the plug portion, wherein the retainer member is configured to retain the plug portion disposed within the at least one access opening.

Abstract: An inspection port plug device is provided for sealing three or more oppositely placed inspection ports in a multi-chambered gas turbine engine. An embodiment of the inspection port plug device includes a cap and at least two shafts coupled end-to-end. A first shaft includes a first end coupled to the cap and a second end having a first sealing plug, wherein the first sealing plug includes a recess. A second shaft includes a third end coupled to the first sealing plug within the recess and a fourth end having a second sealing plug. The first shaft and the second shaft also include a first biasing mechanism and a second biasing mechanism, respectively, for maintaining the seals at the first and second sealing plugs when the inspection port plug device is installed.

Abstract: The invention provides a nacelle for a bypass turbojet, the nacelle comprising: an aerodynamic fairing; a maintenance cover fastened to the aerodynamic fairing by means of at least one connection hinged about a longitudinal axis of the nacelle; a cold stream inner shroud and a cold stream outer shroud placed concentrically inside the aerodynamic fairing so as to define between them a flow passage for a cold stream, the inner shroud having at least one opening closed by a removable access hatch; and the outer shroud includes at least one opening closed by a removable access hatch that is fastened on the maintenance cover.

Abstract: A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox.

Abstract: An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes: a flexible element that follows the curved profile of the door between two remote anchoring points, at least one safety index including a latch pivotable around an axis of rotation, and connected to the door so as to occupy a locked position in which the end of the latch rests against the inside surface of an edge upstream from the door, and an unlocked position in which the end of the latch is offset relative to the edge, whereby in the locked position, the latch prevents the scooping phenomena by limiting movements of the door in the radial direction toward the outside of the nacelle, and elements for stretching the flexible element between the two anchoring points and for controlling the pivoting in the locked position of the latch.

Abstract: Wind energy systems comprise a wind accelerator having a support assembly and an outer structure surrounding the support assembly. The wind accelerator has a front region and a rear region. The rear region is substantially wider than the front region, and the outer structure tapers from the rear region to the front region. One or more turbines are mounted on the support assembly at or near the rear region of the wind accelerator or at or near the widest point of the wind accelerator.

Abstract: A paneling (30) of a nacelle (12) of a wind energy installation (10), in which an upturned panel ceiling (40) is provided in installation position, is created with a hatch opening (46), that is provided in the panel ceiling (40). The hatch opening (46) is advantageously provided so large, that components of the entire area of a drive train (24) of the wind energy installation (10) can be removed upwards, or inserted from above into the nacelle (12) through the hatch opening (46). Furthermore, such a hatch opening (46) is choosingly closable by means of a hatch cover (44).

Abstract: A nacelle, a part of which is the fairing device, surrounds a gas turbine engine (4) and a support pylon (7) on an aircraft fuselage (15). The pylon extends into a substantially horizontal plane of symmetry containing the longitudinal axis of the propulsion power unit (1), and comprises a central compartment (7b) that is open on the top and on the bottom and provided for housing devices. The pylon is attached to the fuselage (5) by a distal edge (7d) extending parallel to the longitudinal axis of the propulsion power unit (1). The fairing device consists of an upper half-cowl (2) and a lower half-cowl (3) substantially symmetrical relative to said plane of symmetry, and lockable therebetween, in a closed position. The upper half-cowl (2) and lower half-cowl (3) are individually pivotably mounted on the distal edge (7d) of the pylon (7) such that, in an open position, access is provided at the same time to the engine (4) and to the central compartment (7b) of the pylon (7).

Abstract: A method for forming a pressure measurement hole in a component includes the step of forming a hole in a body of the component, the hole extending from a body surface of the component. An insert having a longitudinal passage is fitted into the hole such that the insert protrudes from the body surface. The protruding end of the insert is machined to define an insert surface profile matched to the body surface profile and displaced from the body surface by a distance substantially equal to a thickness of a covering layer that is to be bonded onto the body surface. A blocking pin is inserted into the insert passage. The covering layer is then bonded to the body surface in the region of the hole and insert after which the blocking pin is removed from the insert to open the pressure measurement hole.

Abstract: Various “contactless” bearing mechanisms including hydrodynamic and magnetic bearings are provided for a rotary pump as alternatives to mechanical contact bearings. In one embodiment, a pump apparatus includes a pump housing defining a pumping chamber. The housing has a spindle extending into the pumping chamber. A spindle magnet assembly includes first and second magnets disposed within the spindle. The first and second magnets are arranged proximate each other with their respective magnetic vectors opposing each other. The lack of mechanical contact bearings enables longer life pump operation and less damage to working fluids such as blood.

Abstract: A plug for an inspection hole of a gas turbine engine is disclosed. The plug may have a stem including a first shaft, wherein a first seal is located circumferentially about the first shaft. The plug may have a swivel seal including a second seal spaced from a ball by a second shaft, and the swivel seal may be rotatably connected to the stem by the ball. The ball and the second seal may be fixed to the second shaft.

Abstract: A turbo machine airfoil, such as a blade or a vane in a compressor, in which the airfoil root portion includes screw threads having a dove tail cross sectional shape, and the rotor disk includes holes having similar screw threads such that a blade or vane can be easily replaced by unscrewing the old blade or vane and screwing in a new blade or vane. A locking pin biased by a spring is located in the root of the airfoil to lock the airfoil in the threaded hole to prevent the airfoil from loosening due to vibrations and to lock the airfoil in place at a desired angle of attack for maximum efficiency of the turbo machine. The removable cover plate is located on the casing and over the rotor disk such that the blade can be removed through the opening without the need to disassemble the turbo machine.

Abstract: Disclosed is a shroud for a turbomachine including at least one support structure and at least one inner shroud disposed at a gas path of a turbomachine. The at least one inner shroud and the at least one support structure have at least one gap therebetween. The at least one gap alternates between at least one restrictive gap and at least one unrestrictive gap and is capable of creating at least one pressure loss mechanism to reduce a hot gas flow in the at least one gap. Further disclosed is a turbomachine and a method for reducing ingestion of hot gas in a turbomachine.

Abstract: Twin-flow turbo-jet engine, comprising a cylindrical casing externally defining an annular flow space for a secondary flow, wherein the cylindrical casing is formed from a lattice framework and from removable cowling panels fixed to the framework, said framework comprising an upstream annular flange for fixing to an intermediate housing, a downstream annular flange for connecting to an exhaust housing and rigid beams parallel or inclined relative to the axis of the turbo-jet engine, connecting the two flanges to one another.

Abstract: The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with an inner concentric structure (9) for surrounding the downstream portion of the turbojet, an annular flow channel (8), characterised in that a portion at least of said inner structure (9) is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.

Abstract: A gas turbine engine includes an engine core extending along a core axis, a cooling-air delivery duct on the engine core, and a removable nacelle cowl overlying the engine core. A cooling-air nacelle-cowl duct delivers cooling air to the cooling-air delivery duct. At least a portion of the length of the cooling-air nacelle-cowl duct is integral with the nacelle cowl and not directly supported on the engine core.

Abstract: An inspection port plug device is provided for sealing three or more oppositely placed inspection ports in a multi-chambered gas turbine engine. An embodiment of the inspection port plug device includes a cap and at least two shafts coupled end-to-end. A first shaft includes a first end coupled to the cap and a second end having a first sealing plug, wherein the first sealing plug includes a recess. A second shaft includes a third end coupled to the first sealing plug within the recess and a fourth end having a second sealing plug. The first shaft and the second shaft also include a first biasing mechanism and a second biasing mechanism, respectively, for maintaining the seals at the first and second sealing plugs when the inspection port plug device is installed.

Abstract: One form of the present invention contemplates an apparatus comprising a gas turbine engine core, a gearbox accessory mounted to the engine core and substantially enclosed by an inner fairing; a nacelle having a plurality of panels, wherein the nacelle panels substantially enclose and overlap at least a portion of the inner fairing; and a bypass duct defined between an exterior surface of the inner fairing and an interior surface of at least some of the nacelle panels.

Abstract: Some embodiments of the present invention provide a pump including a pump housing having an inlet adapted to fluidly couple with an inlet conduit, and an outlet adapted to fluidly couple with an outlet conduit. The pump also includes a pump shaft rotatably supported in the pump housing and a plurality of impellers coupled for rotation with the pump shaft. The pump further includes a motor removably coupled to the pump housing. The motor has an output shaft drivably coupled to the pump shaft. The pump also includes a spacer positioned between the plurality of impellers and the motor. The spacer includes at least one aperture to access and de-couple the output shaft and the pump shaft. The motor, spacer, pump shaft, and the plurality of impellers are removable from the pump housing as a single unit without disconnecting the inlet conduit and the outlet conduit from the pump housing.

Abstract: An assembled pump compressor arrangement of an air-conditioning system having a housing enclosing an impeller with a thrust collar positioned thereon. The arrangement includes a tool for applying torque to the impeller having an outer cylindrical element and a plurality of arcuate sections. The arrangement further includes a releasable clamp for interconnecting the arcuate sections and the outer cylindrical element with the impeller clamped between the outer cylindrical element and the arcuate sections. A torque bar is provided which extends through the outer cylindrical element in a spaced relation to the impeller through which the torque is applied to effect disassembly of the high-speed thrust collar and removal of the impeller from the housing of the air-conditioning system.

Abstract: Methods and apparatus for a balance weight access assembly are provided. The assembly includes an access cover, and an access tube including a first opening, a second opening, and a substantially hollow body extending therebetween. The first opening is positioned proximate to a balance weight retainer, the second opening is positioned proximate to the access cover, and the body is positioned in substantial alignment with an installation axis of the balance weight retainer.

Abstract: An adapter to permit borescope access inside a gas turbine engine including a compressor stator having a plurality of compressor stator segments comprises a body portion defining a bore extending longitudinally therethrough from a first end to be disposed adjacent to outside surfaces of adjacent compressor stator segments to a second end to be disposed adjacent to inside surfaces of adjacent compressor stator segments. The bore permits a borescope to enter therethrough. The adapter further comprises an attachment portion for circumferentially coupling at least one compressor stator segment to an outer casing of the gas turbine engine.