Abstract: The variable vane arm mechanism can have an actuator ring defined around a main axis, a set of vanes having a plurality of vanes circumferentially distributed around the main axis, each vane having a vane axis extending from an inner end to an outer end and being rotatable around the vane axis, each vane having a vane arm, a plurality of pins circumferentially distributed around a main axis, slide blocks engaged with corresponding ones of the pins in a manner to rotate around the pins, and guide slots having a length extending away from corresponding ones of the vane axes, each guide slot slidingly receiving a corresponding slide block.

Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan forces fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and adjusts a direction of the fan exit air, and includes a plurality of outlet guide vanes and a plurality of actuation assemblies that control rotation of the outlet guide vanes about a pitch axis. The outlet guide vanes include a leading edge portion and a trailing edge portion rotatably coupled to an axially aft edge of the leading edge portion. The actuation assembly rotates the leading edge portion and the trailing edge portion to minimize losses created by distortions in fan inlet air and created by the leading edge portion redirecting the fan exit air in the first direction.

Abstract: A mechanism for driving a first member for adjusting the orientation of the blades of a first stage of a turbine engine diffuser and a second member for adjusting the orientation of the blades of a second stage of the turbine engine diffuser, including a single drive wheel which simultaneously drives the first adjustment member and the second adjustment member and a set of gears which is arranged between the drive wheel and the two adjustment members, wherein the set of gears includes a first gearwheel which is directly coupled with the drive wheel and with the first adjustment member and which is coupled with the second adjustment member with a secondary gearwheel which is directly coupled with the second adjustment member.

Abstract: Variable stator vanes with anti-lock trunnions are disclosed. An example apparatus disclosed herein includes an airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis, an outer trunnion, and an inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to an inner shroud of the gas turbine engine.

Abstract: An assembly is provided for a piece of rotational equipment. This assembly includes a first structure, a second structure and a fluid transfer assembly. The first structure is configured with an aperture. The second structure is configured as or otherwise includes a port. The fluid transfer assembly includes a fluid conduit and a slider element. The fluid conduit is configured as a monolithic tubular body that includes a first conduit end, a second conduit end, a first coupling and a second coupling. The fluid conduit extends axially along a centerline from the first conduit end, through the aperture and into the port to the second conduit end. The first coupling is mated with the first structure through the slider element. The second coupling is mated with the second structure through a cone seal interface.

Abstract: A control assembly for a stage of variable-pitch vanes for a turbine engine generally includes an actuating ring having an annular body, a vane guidance means for connecting to the cylindrical pivots of the variable pitch vanes, a rotating means for rotating the actuating ring about a casing of the turbine engine, and a centering means for cooperating with the casing to center the actuating ring. The centering means may have at least one skid bearing against the casing. At least one of the skid or the rod may be configured to cooperate by radial sliding with an inner wall of a housing. The skid may be configured to be mobile during operation by sliding between a radially internal position and a radially external position.

Abstract: A gas turbine engine, having an engine central longitudinal axis, includes at least one of a vane support, a vane stage, a blade outer air seal support, and a blade outer air seal. At least one of the vane support, the vane stage, the blade outer air seal support, and the blade outer air seal is rotatable about the engine central longitudinal axis. The gas turbine engine may further include a drive system configured to rotate at least one of the vane support, the vane stage, the blade outer air seal support, and the blade outer air seal about the engine central longitudinal axis.

Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.

Abstract: Guide vane adjusting device for a flow machine to rotate guide vanes, with a driveshaft, and a control ring that transmits rotation of the driveshaft to rotate the guide vanes. The driveshaft is directly coupled with one of the guide vanes to be directly rotatable by the driveshaft without the intermediary of the control ring. The directly driven guide vane is articulately coupled with the control ring via a transmission lever. The other guide vanes are indirectly rotatable with the intermediary of the control ring. The control ring is displaceable in circumferential and axial direction such that forces at coupling points between the control ring and the transmission levers coupled with the control ring run perpendicular to the transmission levers.

Abstract: A centrifugal compressor includes: a casing; a compression mechanism disposed inside the casing; a flow rate regulation valve disposed inside the casing and that regulates a flow rate of air sucked into the casing; a conversion mechanism disposed outside the casing and that changes a direction of the flow rate regulation valve based on an output of an actuator; and a cover that surrounds and houses the conversion mechanism, wherein dry air is supplied to an inside of the cover, and the cover forms an air reservoir that prevents dew condensation on the conversion mechanism.

Abstract: A device for adjusting the pitch of at least one annular row of stator vanes for a turbine engine module. The device includes a first control ring mounted to rotate freely about an axis of the turbine engine. The device also includes connecting rods for connecting the first control ring to the vanes and a second control ring mounted to rotate freely about the axis. Each vane of the at least one row is simultaneously connected to the first and second control rings by a set of at least two connecting rods. The device is suitable for use as part of a module and is suitable for use in a turbine engine.

Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.

Abstract: A cable drive system for variable vane operation comprising an actuator, a harmonic drive driven by the actuator, a cable drive system driven by the harmonic drive; and a unison ring driven by the cable drive system.

Abstract: To provide a variable stator vane mechanism, for an axial flow compressor, which is excellent in durability, has a simple structure, and is realized at low cost. The variable stator vane mechanism for adjusting a mounting angle of a stator vane of an axial flow compressor includes: an arm coupled to the stator vane; a rotation ring coupled to one end portion of the arm and located at an outer surface of a casing of the axial flow compressor; a driving machine configured to rotate the rotation ring to cause the stator vane to pivot via the arm; and a friction pad mounted on the casing. The rotation ring is in frictional contact with the friction pad.

Abstract: A drive mechanism is provided for driving at least two adjusting members used to adjust the orientation of the blades of a turbomachine rectifier vane associated therewith, where the drive mechanism simultaneously drives the displacement of at least two adjusting members in the turbomachine. A single threaded rod drives several levers, each lever being associated with an adjusting member. A first part of each lever engages with the threaded rod and one end of an arm of the lever is connected to the adjusting member associated therewith so that the rotation of the threaded rod causes a simultaneous rotation of the levers associated with the adjusting members.

Abstract: An axially divided inner ring for a turbomachine, for fastening to guide vanes of the turbomachine. The inner ring comprises at least one first, solid ring segment disposed upstream, and a second, solid ring segment disposed downstream, wherein the first ring segment is joined to the second ring segment in a detachable manner by means of at least one fastening element. The first ring segment and/or the second ring segment is joined to at least one sealing segment. The inner ring comprises a securing element for securing the fastening element, wherein the securing element is joined to the first ring segment and/or to the second ring segment. In addition, the present invention relates to a guide vane ring of a turbomachine having guide vanes, which have an axially divided inner ring according to the invention.

Abstract: A runner assembly includes a runner with an aperture, a cradle, and a fastener. The cradle includes a planar base with an aperture, a tab extending from the base, and fingers extending from the base. The fastener extends through the apertures for attaching the runner to the cradle, and the fingers are adjacent to the runner and constrain the runner with respect to the cradle and the fastener.

Abstract: The present invention relates to a stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least two radial planes, as well as at least two stator vane adjusting rings connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device, characterized in that the actuating device is connected to the stator vane adjusting rings by means of a first transmission device and that a second transmission device, which is not coupled to the actuating device, is arranged essentially opposite to the first transmission device, with the second transmission device being connected to the stator vane adjusting rings.

Abstract: A jet engine actuation system includes a first ring gearbox, a second ring gearbox and an actuator. The first ring gearbox includes a first ring driveshaft coupled to a first portion of a synchronization ring included in a jet engine. The second ring gear box includes a second ring drive shaft coupled to a second portion of the synchronization ring. The actuator has a first actuator gearbox configured to generate a first rotational output and a second actuator gearbox configured to generate a second rotational output. A first drive shaft transfers the first rotational output to the first ring gearbox and a second drive shaft transfers the second rotational output to the second ring gearbox. The actuator simultaneously controls the first and second actuator gearboxes such that the first and second rotational outputs are simultaneously transferred to the first and second ring gearboxes to rotate the synchronization ring.

Abstract: An inner bushing assembly (280) to provide a biasing force between a guide vane (260) and an inner ring half (261) of a gas turbine engine compressor (200) is disclosed. The inner bushing assembly (280) includes a first bushing (281), a second bushing (282), and a biasing element (283). The first bushing (281) is configured to be installed about an inner vane shaft (267) of the guide vane (260) adjacent to an airfoil (265) of the guide vane (260). The second bushing (282) is configured to be installed about the inner vane shaft (267) distal to the airfoil (265). The biasing element (283) is configured to be installed about the inner vane shaft (267) between the first bushing (281) and the second bushing (282).

Abstract: A system for controlling at least two variable geometry apparatuses of a gas turbine engine that includes at least a first body and a second body, the first apparatus including a stator blade stage with a variable setting angle of a compressor of the first body capable of switching between a closed position in an idle mode and an open position in a high-speed mode, and the second apparatus including at least one discharge valve of a compressor of the second body capable of switching between an open position in an idle mode and a closed position in a high-speed mode. The system further includes an actuator for actuating the two apparatuses.

Abstract: A turbine section of a gas turbine engine is described, which includes an aftmost rotor extending, an aftmost stator located upstream of the aftmost rotor, and a second to last aftmost rotor located upstream of the aftmost stator. The second to last aftmost rotor being spaced apart a first axial distance from the aftmost stator. A turbine exhaust case is located downstream of the aftmost rotor and includes an inner radial wall and an outer radial wall defining a main gas path duct downstream of the aftmost rotor. The turbine exhaust case being axially spaced apart from the aftmost rotor a second axial distance that is greater than the first axial distance.

Abstract: A system for controlling at least two sets of variable geometry equipment of a turbine engine. The turbine engine includes at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. The actuator drives the second set of equipment by an actuating part that is actuated over part of the course of the actuator and idle on an abutment over the rest of the course, and by a sliding joining element providing a backlash in the actuation of the second set of equipment.

Abstract: A system for controlling at least two sets of variable geometry equipment of a gas turbine engine including at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. An actuator actuates the two sets of equipment.

Abstract: A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.

Abstract: A control system for controlling at least two variable-geometry devices of a turbomachine, and a turbomachine including such a control system, the system including an actuator that actuates both devices; one of the devices including at least one stage of variable-pitch stator vanes, and the other device being an air-bleed valve for a turbomachine body. The system is configured to control progression opening of the vane stage and progressive closing of the air-bleed valve as an actuation parameter of the actuator increases. As a result, the control system serves advantageously to control two devices using a single control system.

Abstract: A variable vane assembly for a gas turbine engine having a casing, including: a variable vane including a platform and a vane stem extending outwardly from the platform; a bushing surrounding the vane stem; a lever for moving the vane between a closed position and an open position; and, a mechanism for incrementally rotating the bushing to a new circumferential position with respect to the vane stem as the vane is cycled each time between the closed and open positions.

Abstract: A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a movable actuation rod and a first linkage arrangement which includes a first bell crank connecting the actuation rod to a first component. Movement of the actuation rod produces an output motion of the first bell crank which in turn drives movement of the first component. The control mechanism further comprises a second linkage arrangement which includes a second bell crank connecting the actuation rod to a second component. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component. The first and the second linkage arrangements are configure so that over a predetermined range of movement of the actuation rod the first component is moved which the second component is not moved.

Abstract: A system for controlling at least two variable-geometry equipments of a gas turbine engine is disclosed. The engine includes at least a first core rotating at a first speed and a second core rotating at a second speed. The first equipment includes at least one variable-pitch stator blade of a compressor of the first core and the second equipment includes at least one air bleed valve of a compressor of the second engine core moving between an open position at idle speed and a closed position at high speed. The system includes an actuator which actuates both equipments.

Abstract: A system for controlling at least two variable-geometry equipments of a gas turbine engine is disclosed. The engine includes at least a first core rotating at a first speed and a second core rotating at a second speed. The first equipment includes at least one variable-pitch stator blade of a compressor of the first core and the second equipment includes at least one air bleed valve of a compressor of the second engine core moving between an open position at idle speed and a closed position at high speed. The system includes an actuator which actuates both equipments.

Abstract: A system for controlling at least two variable-geometry equipments of a turbomachine, in which the first equipment is a variable pitch stator blade stage of a compressor of a first core moving between a closed position at idle speed and an open position at high speed, and the second equipment is at least one bleed valve of a compressor of a second core moving between an open position at idle speed and a closed position at high speed, is disclosed. The actuator operates over a portion of its travel a first branch of an angle transmission member which actuates the first equipment and leaves this branch at rest on an abutment over the rest of its travel. The actuator operates the second equipment via a sliding junction member arranging a free travel in the actuation of said second equipment.

Abstract: An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing.

Abstract: A system for controlling at least two variable geometry apparatuses of a gas turbine engine that includes at least a first body and a second body, the first apparatus including a stator blade stage with a variable setting angle of a compressor of the first body capable of switching between a closed position in an idle mode and an open position in a high-speed mode, and the second apparatus including at least one discharge valve of a compressor of the second body capable of switching between an open position in an idle mode and a closed position in a high-speed mode. The system further includes an actuator for actuating the two apparatuses.

Abstract: A wind turbine engine comprising rotor blades disposed within an outer casing and a half-spherical head located in front of the rotor blades and blocking the inner 50% of the radius of the rotor blades, the casing and head creating an acceleration chamber wherein incoming wind is speeded up and redirected around the head, and the accelerated wind then rotates the wind turbine rotor blades to generate power.

Abstract: A controllable variable length link device is disclosed. The device includes a first half-link having a first end connected to a driving system and a second end, a second half-link having a first end connected to a driven system and a second end, a rotary displacement member including a rotator shaft and a rotary head cooperating with the second ends of the half-links to bring about opposite movement of the half-links, a bearing unit in which the rotator shaft is mounted, respective guiding units which guide the two half-links in translation in at least two parallel directions, the guiding units being mechanically connected to the bearing means; and a driving unit which drives the shaft in rotation in both directions in accordance with a predetermined relationship.

Abstract: A fluid flow machine has a flow path provided by a casing (1) and a rotating shaft (2), in which rows of rotor blades (3) and stator blades (4) are arranged, and includes at least one annular groove-type recess (5) being disposed in a blade (3, 4) tip area in an annulus duct wall of the casing (1) and/or the shaft (2). An upstream end point (E) of the recess (5) in a flow direction is set at a distance (e)>0 forward of a forward blade tip point (A), and a downstream end point (F) of the recess (5) is set at a distance (f) rearward of point (A), where: 0.5 L>(f)>0, and L is a distance between point (A) and a rearward blade tip point (B).

Abstract: The pitch control mechanism (controlling the angular position) for stator blades in a turbojet may be adjusted separately for two adjacent stages of blades controlled by a common actuator 10. To achieve this, the synchronization bar 9 located between the mechanisms leading to the two stages is inclined, this inclination being determined by a pin 22 and groove 23 connection with the casing, while another pin 26 and groove 27 connection is arranged between the synchronization bar 9 and one of the mechanisms. Strongly non-linear displacement laws between the two mechanisms may thus be controlled depending on the shapes and directions of the grooves.

Abstract: A torque shaft assembly includes a hollow tube with a central axis disposed between and fixedly connected to first and second crankshafts at first and second distal ends, respectively, of the tube for movement of an array of connecting members such as push rods. A hollow interior of tube between the first and second crankshafts is filled with a sufficient quantity of flowable inertia material or damping media to absorb vibratory energy by friction during operation of the engine. The hollow interior is preferably filled with a quantity of damping media to a level by volume of about 98% and a preferred flowable inertia material is round steel shot. A plurality of spaced-apart clevises are fixedly attached to a tube wall on an outer surface of the tube wall surrounding the hollow interior. Each clevis includes connection means disposed away from the wall outer surface for connection with an actuator for movement of the array of adjustable devices such as variable stator vanes.

Abstract: Gas turbine starting method is improved to start operation with bleed valves being first throttled, then fully opened on the way and then fully closed at 90% speed, thereby fluid unstableness phenomenon is suppressed and starter motor power is reduced. While inlet guide vane (11) and variable stator vanes (C1 to C5) are set to predetermined opening from starting to rated speed, bleed valves (1, 2, 3) are set to predetermined opening until 52% speed for the bleed valve (1) and until 51% speed each for the bleed valves (2, 3), then the bleed valves (1, 2, 3) are fully opened until the speed exceeds 90%, when they are fully closed for rated operation. In the prior art, starting operation is done with bleed valves being first fully opened until the speed is elevated to 90% and then fully closed, but in the present invention, air discharged into ambient air in vain can be reduced and thereby starter motor power can be also reduced.