Abstract: A cover system selectively allows a gas flow through a heat exchanger duct upstream of an exhaust duct in an aircraft engine. A fluid is at a first pressure during an engine operating condition and a second pressure lower than the first during shutdown. A plate extends across the heat exchanger duct with aperture(s) extending therethrough. A closure is movable between an open position with gas flowing through the apertures into the exhaust duct, and a closed position with the closure closing the apertures. A biasing member operatively connected to the closure closes the closure with a biasing force. During the engine operating condition, the first pressure creates a first force acting against and greater than the biasing force to urge the closure open. At shutdown, the second pressure creates a second force acting against and lower than the biasing force, the biasing force biasing the closure closed.

Abstract: A propulsion system is provided including an unducted rotating fan defining a fan axis; and a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough; wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine.

Abstract: A valve structure includes: a valve unit including a valve body, a shaft portion extending from the valve body, and a separating portion provided on the shaft portion and spaced apart from the valve body; a mounting plate located between the valve body and the separating portion and including an insertion hole into which the shaft portion is inserted; a holding portion including a first holding surface provided on the mounting plate, and a second holding surface provided on the valve unit and spaced apart from the first holding surface; a protrusion provided on one of the valve unit and the mounting plate, an end of the protrusion protruding beyond the first and second holding surfaces; and an elastic body including a contact portion located between the first and second holding surfaces, and a pressed portion located inside or outside the contact portion and contacting the protrusion.

Abstract: A hydroelectric power generation system is included in a channel control system. The channel control system includes a command section that outputs a command value of a flow rate or pressure of a fluid, an opening degree control unit that calculates a target opening degree based on the command value, and a motor-operated valve installed in a channel through which the fluid flows. The valve opens and closes in accordance with the target opening degree. The hydroelectric power generation system includes a water turbine disposed in the channel, a generator driven by the water turbine, and a generator control unit that controls at least one of a torque and a number of rotations of the generator based on opening degree information that indicates a measured value of an actual opening degree of the valve or an opening degree estimated.

Abstract: An air management system with a set of compressed air sources for selectively supplying pressurized air to air consumer equipment according to an aircraft operation condition. Low pressure air, high pressure air, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.

Abstract: A gas turbine engine includes a compressor section, a turbine section and an intermediate combustor. The compressor section has a plurality of rotating compressor blades rotating about an axis of rotation, and static stator vanes positioned axially intermediate the rotating compressor blades. There are a plurality of bleed holes extending through a compressor outer housing positioned radially outwardly of the rotating compressor blades, and allowing air compressed by the compressor blades to move into a bleed chamber. There is a bleed chamber outer housing positioned radially outwardly of the compressor outer housing, and defining the bleed chamber in part in combination with the compressor outer housing. A flow discourager is positioned radially intermediate the bleed holes and the bleed outer housing, such that air leaving the bleed hole impacts upon the flow discourager before reaching the bleed chamber outer housing.

Abstract: A nacelle forward part of an aircraft propulsion assembly, includes an air inlet lip at the front end, an internal structure and an external panel extending the lip, and an annular stiffening frame formed around an axis of revolution and comprising an internal peripheral edge linked to the internal structure and an external peripheral edge linked to the external panel. The stiffening frame presents an inclination relative to the axis of revolution, its slope being oriented towards the front end of the nacelle forward part. The stiffening frame is configured to deviate, outside the nacelle of the propulsion assembly, an object striking the stiffening frame. The stiffening frame so configured is capable of withstanding the impacts of objects without breaking while enabling the object striking the stiffening frame to be deviated towards the exterior of the nacelle.

Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

Abstract: This invention relates to a compressor 100 for a supercharger 10. The compressor 100 comprises a compressor housing 110 with a compressor inlet 112 and a compressor outlet 114. The compressor 100 furthermore comprises an adjustment mechanism 200 and an actuator device 300. The adjustment mechanism 200 comprises an adjustment ring 210 and a plurality of shutter elements 220 for changing an inlet cross section 112a of the compressor inlet 112. The actuator device 300 comprises a drive unit 310 and a coupling unit 320. The actuator device 300 is thus coupled, via the coupling unit 320, to the adjustment mechanism 200 in order to move the adjustment mechanism 200 between a first position and a second position.

Abstract: The invention relates to a rectifier (1) for an aircraft turbomachine compressor, the rectifier comprising an inner ferrule (24), an outer ferrule (26), and stator blades (28) secured to the inner and outer ferrules, the rectifier also comprising a flange (34) secured to a downstream end of the outer ferrule (26) and designed to be fixed to a compressor housing (36), the flange being provided with air extraction openings (50) arranged at a distance from each other in a peripheral direction (52). According to the invention, at least one of the air extraction openings (50) has a stretched form in the peripheral direction (52).

Abstract: Provided is a centrifugal compressor, including: an impeller including blades; a main flow passage including a narrowing portion, which is formed on a front side of the impeller and has a diameter smaller than a diameter of each of the blades; an auxiliary flow passage, which has one end communicating to the main flow passage on the impeller side with respect to the narrowing portion and another end communicating to the main flow passage on a side away from the impeller with respect to the narrowing portion; and a movable portion which is movable between a first position and a second position, the second position being different from the first position in position in a rotation axis direction and a rotation direction of the impeller and in opening degree of the auxiliary flow passage.

Abstract: A method of regulating a temperature associated with a heat exchanger assembly of a turbine engine, the method includes, in a single cycle: measuring the temperature of an air stream at the outlet from a heat exchanger; receiving a setpoint temperature for the air stream at the outlet from the heat exchanger; estimating a theoretical temperature for the air stream at the outlet from the heat exchanger as a function of an estimate of the shutter position of a controlled valve bleeding off a cooling air stream for the heat exchanger; determining a correction current from the difference between the measured temperature and the theoretical temperature; and determining a control current for the shutter from the difference between the measured temperature and the setpoint temperature and the correction current determined during the preceding cycle, the shutter position being determined from the control and correction currents determined during the preceding cycle.

Abstract: A wastegate assembly for controlling flow of exhaust gas includes a valve element having a valve body and a valve shaft. The wastegate assembly further includes a spindle having a head defining an opening and including a flat surface. The wastegate assembly further includes a washer coupled to the valve shaft and spaced from the spindle for securing the spindle to the valve shaft. The washer defines a bottom washer surface facing the flat surface of the spindle head, with the bottom washer surface including a flat region and a beveled region. A biasing member is disposed between the flat surface of the spindle and the flat and beveled regions of the washer. The beveled region extends oblique relative to the flat region for minimizing contact between the washer and the biasing member beyond the flat region.

Abstract: A gas expander includes: a casing where a swirl chamber for a gas to be expanded is formed; a turbine wheel that is housed in the casing and rotationally driven by the expanded gas; a diffuser that is mounted to the casing in a direction of a rotating shaft of the turbine wheel and includes a flow path for the expanded gas to flow in the direction of the rotating shaft; a swirl stopper that is disposed in the diffuser, faces a downstream front end surface of a boss of the turbine wheel that faces the flow path, and includes a closed swirl stopping surface that is disposed to face the downstream front end surface of the boss with a gap between the closed swirl stopping surface and the downstream front end surface; and a swirl preventing plate that circumferentially partition the flow path in the diffuser.

Abstract: A turbocharger includes a turbine housing that defines a flow passage for a fluid. The turbine housing includes a turbine shroud member. The turbocharger also includes a turbine wheel supported for rotation within the turbine housing relative to the turbine shroud member. The turbine wheel is configured to rotate as the fluid flows through the flow passage. Moreover, the turbocharger includes a port extending through the turbine shroud member. The port is configured to receive a portion of the fluid flowing through the flow passage.

Abstract: A method of applying a wear-resistant coating to aluminum sliding contact wear surfaces is disclosed. The method includes providing a plurality of parts having sliding contact wear surfaces and thermal spray coating at least one of a composite aluminum oxide and PTFE or a blend of aluminum oxide and PTFE. The disclosed method may be used to repair aluminum parts subject to sliding contact wear as well as in the design of new aluminum parts subject to sliding contact wear. Improved compressor bleed valves for gas turbine engines and improved fan exit case assemblies are also disclosed.

Abstract: An example method to extract bleed air from an aircraft engine includes extracting, via a plenum positioned in a compressor of the aircraft engine, bleed air from a first bleed port associated with a first stage of a compressor and a second bleed port associated with a second stage of the compressor. The plenum is configured to combine the extracted bleed air from the first and second bleed ports and fluidly couple the extracted bleed air to one or more systems of an aircraft. The method includes regulating a pressure of the extracted bleed air in the plenum by adjusting a flow of bleed air through the first bleed port via a first valve associated with the first bleed port and adjusting a flow of bleed air through the second port via a second valve associated with the second bleed port.

Abstract: An exhaust manifold for an internal combustion piston engine having a first row of at least two cylinders inclined relative to a vertical plane and a second row of at least two cylinders inclined relative to the vertical plane, where the two rows of cylinders form a V configuration with the vertical plane being approximately equidistant between the two rows. The exhaust manifold in one aspect comprises plural exhaust stack assemblies for receiving exhaust gas from the first row of cylinders, an elongate manifold plenum having a terminal portion defining an exhaust gas passageway, and an exhaust gas routing circuit joined to the manifold plenum. The routing circuit comprises a turbocharger support column and a bypass pipe. The turbocharger support column is joined at a first junction with the manifold plenum, extends in a generally perpendicular direction from the elongate manifold plenum and terminates in a first exhaust gas outlet adapted for connection to a turbocharger.

Abstract: A turbine (3) includes: a turbine impeller chamber (43) having a tubular outflow portion (432), from which an exhaust gas flows out in an outflow direction (F) substantially parallel to an axis (C) of a turbine impeller (5); a bypass flow passage (491) bypassing the inside of the turbine impeller chamber; an outer duct (47) having an inner peripheral surface (475) that expands in diameter in the outflow direction from the outflow portion; and an inner duct (48) that extends in the outflow direction from the outflow portion. A diffuser flow passage (483) that expands in diameter in the outflow direction is disposed in the inner duct at least in a portion between the outflow portion and a distal end portion (481a). An outlet (492) of the bypass flow passage and a waste gate valve (493) that opens and closes the outlet are disposed on the inner peripheral surface.

Abstract: A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.

Abstract: The invention discloses a compressor. The compressor includes a first primary cylinder, a second primary cylinder and a secondary cylinder, which are stacked, a separator is provided between two adjacent cylinders. The first primary cylinder is provided with a first air entry, the second primary cylinder is provided with a second air entry, and the secondary cylinder is provided with an air outlet. The first primary cylinder and the second primary cylinder are connected in serial to the secondary cylinder after being connected in parallel. A refrigerant entering the first air entry and the second air entry is discharged from the air outlet after primary or/and secondary compression. The two separators are divided into a first separator and a second separator. Any one or two of the first separator, the second separator and a lower flange may be provided with a slide piece control device.

Abstract: A wellhead assembly for use with a well that includes a production tree, a production line for carrying produced fluid from the production tree, and a choke in the production line. The choke assembly includes a turbine member that rotates in response to fluid flowing through the production line. The kinetic energy of the rotating turbine is converted into electricity by a generator that is coupled with the turbine member. Selectively impeding turbine rotation with a brake system introduces a pressure drop in the production line fluid, and which regulates flow of the production line fluid. The turbine member can be disposed in a straight run of the production line, or adjacent a bend in the production line.

Abstract: A bleed of valve comprises a ring axially translatable between a retracted position in which the ring is configured to close an annular bleed off opening defined in a converging portion of a radially outer annular wall of a gas turbine engine gaspath and a deployed position in which the ring protrudes into the gaspath to mechanically scoop out incoming air and water/hail particles.

Abstract: The present application proposes an axial turbomachine compressor comprising a rotor with at least one annular row of rotor blades, a stator casing surrounding the row of rotor blades, the casing including a device for generating counter-vortexes. During operation of the compressor, the movement of the blades creates leakage vortexes at the blade tip. The generating device in turn injects counter-vortexes rotating in the opposite direction to the leakage vortexes in order to counter the leakage vortexes. This improves the surge margin of the compressor. The present application also provides a method for controlling the stability of a turbomachine compressor by counter-vortex injection.

Abstract: A closed loop thermal cycle expander bypass flow control is described. An expander is positioned within and surrounded by a housing to receive a working fluid and rotate in response to expansion of the working fluid flowing through the expander. A bypass channel is positioned within and surrounded by the housing to define a fluid flow path that bypasses the expander. A fluid flow control sub-assembly is fluidically coupled to the expander and the bypass channel, and attached to the housing. The fluid flow control sub-assembly can receive the working fluid at a housing inlet and either flow the working fluid through the expander and block the working fluid from flowing through the bypass channel, or flow the working fluid through the housing bypassing the expander, flow the working fluid out via a housing outlet, and block the working fluid from flowing through the expander.

Abstract: A hybrid variable bleed valve includes a static bleed slot disposed in a transition duct defining a flow path for a core air flow, a variable bleed valve door disposed radially outwardly of the transition duct and the static bleed slot, a radially inward bleed cavity defined radially outwardly of the transition duct and radially inward of the variable bleed valve door for collection of a plurality of particulates and a pressure recovery return duct in fluid communication with the radially inward cavity and the transition duct. The hybrid variable bleed valve apparatus operable to open and close the variable bleed valve door to a booster bleed flow, flowing radially outwardly from the static bleed slot, for extraction of the particulates and provide a pressure recovery flow into the core air flow via the pressure recovery return duct. The hybrid variable bleed valve configured for use in a gas turbine engine.

Abstract: A gas turbine unit having a compressor section, a combustion chamber section containing at least one combustion chamber, and a turbine section, wherein, starting from a compressor inlet, a flow path extends. The gas turbine unit is equipped with at least one first and one second cooling air path. The first cooling air path draws off compressed air from the flow path upstream of the at least one combustion chamber. The first cooling air path has a higher pressure level than the second cooling air path and feeds the cooling air. The second cooling air path has a draw-off point in the compressor section, and extends from the compressor section to the turbine section, bypassing the at least one combustion chamber. After components have been cooled, the first cooling air path feeds the cooling air into the second cooling air path at an infeed point as additional cooling air.

Abstract: Exemplary compact wind power generation systems are configured to be suitable for residential and other locations where concealed moving parts are desirable. The wind power generation systems utilize a propeller disposed behind a contracting inlet. The propeller blades may be oriented “into the wind” to develop consistent torque across a variety of wind speeds. The propeller may rim-drive power generation components, further reducing vibration, or may share a common rotational axis with the power generation components.

Abstract: A compressor for a gas turbine engine includes a stator and a rotor. The stator includes first and second stator vanes attached to first and second vane platforms, respectively. The rotor includes a plurality of rotor blades that rotate with respect to the stator. An inner stator casing supports the first and second vane platforms and encloses the stator and the rotor. An outer stator casing encloses the inner stator casing, and a bleed cavity is disposed therebetween. At least one diffuser is disposed between the first vane platform and the second vane platform, and is configured to allow air communication between the inner stator casing and the bleed cavity. An exit opening of the diffuser is disposed within the bleed cavity at a location separate from the inner stator casing and the outer stator casing.

Abstract: A turbocharger for an internal combustion engine has a housing (12) in which elements (18, 44) are arranged. An optical duct (24) is formed in the housing (12) and is assigned to at least one of the elements (18). The optical duct (24) is assigned an infrared detector (28) that is designed to detect infrared radiation (30) from the at least one element (18) through the optical duct (24) to determine a temperature (T) of the at least one element (18).

Abstract: A multistage centrifugal pump includes a foot part (1) and a head part (7), between which several pump stages are arranged. Each of the pump stages includes an impeller (4) and a housing (5) surrounding the impeller (4). The housings (5) are arranged over one another. The housings (5) together with an outer casing (9) form an annular channel (8). The housings (5) together with an outer casing (9) are clamped via clamping bolts (11) which are fastened on the head part (7) and the foot part (1). The clamping bolts (11) are arranged within the annular channel (8).

Abstract: A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies.

Abstract: A method for operating an engine system is provided. The method includes during a first condition, flowing exhaust gas from a first exhaust gas conduit to a first turbine inlet of a turbine and flowing exhaust gas from a second exhaust gas conduit to a turbine bypass conduit and during a second condition, flowing exhaust gas from the first exhaust gas conduit to the first turbine inlet and exhaust gas from the second exhaust gas conduit to a second turbine inlet.

Abstract: A valve device of a turbocharger includes: a valve seat disposed on an entrance of a fluid passage divided into at least two branches, and an opening/closing valve coupled to a rotary shaft rotatably disposed adjacent to the valve seat. The valve seat has a contact surface which is flat and a dividing section which extends across the entrance and divides the entrance into two entrance sections. The opening/closing valve closes the entrance of the fluid passage disposed in the valve seat. The bottom surface of the opening/closing valve is in surface contact with the contact surface of the valve seat. The central portion of the opening/closing valve corresponding to the dividing section is spaced apart from the dividing section at a predetermined distance.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft, a first bearing structure and a second bearing structure that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.

Abstract: A control line operating system includes a first piston having a first pressure face and a second pressure face, a first control line in operable communication with the first pressure face of the first piston, a second piston having a third pressure face and a fourth pressure face and a second control line in operable communication with the third pressure face of the second piston. Both the first piston and the second piston are in operable communication with a tool such that pressure increases in either the first control line or the second control line can cause actuation of the tool, the first control line is in operable communication with the fourth pressure face of the second piston and the second control line is in operable communication with the second pressure face of the first piston.

Abstract: A turbocharger system is disclosed, including a turbine and compressor and a rotary valve unit. The rotary valve unit comprises a fixed valve seat and a rotary valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. The valve unit includes a valve housing that defines a first flow passage and a second flow passage, and the valve member and valve seat are disposed in the second flow passage. A turbocharger system is also disclosed, including a turbine and compressor and the rotary valve unit. The rotary valve unit is coupled with the turbine such that exhaust gas that has passed through the turbine wheel is fed into the first flow passage of the rotary valve unit, and exhaust gas that has bypassed the turbine wheel is fed into the second flow passage of the rotary valve unit.

Abstract: Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example apparatus for bleeding air from a multi-stage compressor of an aircraft engine includes a compressor case having a plurality of bleed ports. A first bleed port is associated with a first stage of a compressor, and a second bleed port is associated with a second stage of the compressor. The apparatus includes a plenum connected to the compressor case to define a plenum cavity. The plenum fluidly coupling the first and second bleed ports to a fluid conduit for providing bleed air to one or more systems of an aircraft. The apparatus also includes a bleed port selection mechanism located within the plenum cavity. The bleed port selection mechanism including a first portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port.

Abstract: A pressure supply system for a fresh water system is provided. The pressure supply system includes a water reservoir having a bleed air inlet and a water outlet. The pressure supply system also includes a water pump so as to load water, which is loaded with bleed air pressure, with a further pressure downstream until a predetermined nominal operating pressure range is achieved. As a result, the pressure supply system provides an increased redundancy by pressure generator assemblies which are based on different pressure generation principles.

Abstract: A gas turbine engine variable bleed apparatus includes a variable bleed valve door disposed in a bleed inlet in a transition duct, rotatable about two or more separate pivot points, operable to open and close an aft bleed slot extending outwardly from transition duct, and operable to open and close a forward bleed slot extending inwardly into transition duct. Door is operable to transition between a first position with aft bleed slot open and forward bleed slot closed to a second position with aft bleed slot closed and forward bleed slot open without fully closing door. Door is rotatable about an axis translatable between the two or more separate pivot points. Transition duct having a transition duct conical angle at least about 10 degrees greater than a booster conical angle of a booster outer shroud upstream of transition duct.

Abstract: A unique compressor includes a rotating compressor blade having a blade tip; a compressor case having a blade track disposed opposite the blade tip; and a tip clearance control system including a fluid impingement structure. This structure has a plurality of openings to impinge a fluid received from a diffuser onto the compressor case. The tip clearance control system is configured to control a clearance between the blade tip and the blade track by impinging the fluid onto the compressor case and modulating the same with a valve in fluid communication with the diffuser. A further form includes a unique gas turbine engine having a compressor with a compressor blade tip, a compressor case disposed opposite the blade tip, and a fluid impingement structure having openings to impinge a fluid onto the case. Also included are other apparatuses, systems, devices, hardware, methods, and combinations for compressor blade tip clearance control.

Abstract: A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.

Abstract: A valve includes a body with bleed ports and a ring. The ring surrounds the body and includes two adjacent ring segments. The ring is movable between an open position and a closed position, the latter of which prevents flow through the ports.

Abstract: A system and method for engaging a slide-in mountable fuel pump assembly with a fan cover of an internal combustion engine is disclosed. The fuel pump assembly includes a fuel pump configured to pump fuel from a fuel source to the engine and a mounting bracket affixed to or formed integrally with the fuel pump and configured to slidingly engage a fan cover of the engine so as to enable selective mounting and removal of the fuel pump assembly to and from the fan cover. The mounting bracket further includes a main plate affixed to or formed integrally with the fuel pump and a track formed on each of opposing sides of the main plate, with the track configured to slidingly engage a mating feature formed on the fan cover of the engine so as to selectively mount the fuel pump assembly to the fan cover.

Abstract: A splitter apparatus for a gas turbine engine includes: a splitter including: an annular outer wall which defines a convex-curved leading edge at a forward end thereof; an annular floorplate positioned radially inboard of the outer wall; and an annular first bulkhead spanning between the outer wall and the floorplate. The outer wall, the floorplate, and the bulkhead collectively define an annular splitter plenum positioned adjacent the leading edge of the outer wall. At least one exhaust passage formed in the outer wall extends past the floorplate and communicates with the exterior of the splitter. At least one jumper tube assembly passes through the first bulkhead, each configured to pass air flow from the exterior of the splitter into the plenum.

Abstract: A splitter apparatus for a gas turbine engine includes: a splitter including: an annular outer wall which defines a convex-curved leading edge at a forward end thereof; an annular floorplate positioned radially inboard of the outer wall; and an annular first bulkhead spanning between the outer wall and the floorplate. The outer wall, the floorplate, and the bulkhead collectively define an annular splitter plenum positioned adjacent the leading edge of the outer wall. At least one exhaust passage formed in the outer wall extends past the floorplate and communicates with the exterior of the splitter. At least one jumper tube assembly passes through the first bulkhead, each configured to pass air flow from the exterior of the splitter into the plenum.

Abstract: In a gas turbine of the invention, a first blade ring portion to which first vanes are attached and a second blade ring portion to which second vanes are attached are integrally formed to form an integrated blade ring. A second upstream pressing member is arranged on the upstream side of a second upstream isolation ring which attaches a first ring segment and a second vane stage which is arranged on the downstream side of the first ring segment to the integrated blade ring. By attaching the pressing member to the blade ring portion, the pressing member pushes and fixes the isolation ring to the downstream side, and the sealing performance of a packing is maintained.

Abstract: The invention relates to an improved multi-stage centrifugal compressor (10) comprising at least four centrifugal compression stages (11,12,13,14), each including an impeller. The impellers of one pair of the stages (12,13) are mounted on a first shaft (23) coupled to a first high speed direct drive motor (16), and the impellers of another pair of the stages (11,14) are mounted on a second shaft (24) coupled to a second high speed direct drive motor (15). The speed of the first and second motors is controlled by at least one drive (25) such that the impellers are all driven at the same speed.

Abstract: A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis is substantially perpendicular to the ring bore axis.

Abstract: An exhaust-gas turbocharger (1), with: a turbine housing (2) which has a turbine housing inlet (8) and a turbine housing outlet (9) for exhaust gas, and which has a wastegate duct between the turbine housing inlet (8) and the turbine housing outlet (9), and a flap arrangement (10) comprising a pivotable flap lever (12), a flap plate (11), which is connected to the flap lever (12), for opening and closing the wastegate duct, and having a spring element (17) which is arranged between the flap lever (12) and a disc (18) fastened to the flap plate (11). The spring element (17) has an outer circumferential region (23) which is supported on a sliding contact surface (20), which is of curved form, of the flap lever (12).