Abstract: A method of controlling an aeronautical gas turbine engine may be performed with an electronic controller. The method may include determining an airfoil pitch control command for at least one of a plurality of airfoils of the aeronautical gas turbine engine based at least in part on an excitation load acting upon the aeronautical gas turbine engine, and outputting the airfoil pitch control command to one or more actuators actuatable to change a pitch angle of the at least one of the plurality of airfoils. The airfoil pitch control command may be configured to augment and/or compensate for the excitation load acting upon the aeronautical gas turbine engine. The method may be embodied by a non-transitory computer-readable medium that includes computer-executable instructions, which when executed by a processor associated with the electronic controller, cause the electronic controller to perform the method.

Abstract: A vane adjustment assembly includes vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The adjustment assembly includes a base frame mounted on the ring and including a support body having a first cavity, a first collar removably arranged within the first cavity and having a second cavity formed therein, a second collar removably arranged within the second cavity, and a roller pin coupled to the second collar. The second cavity is offset relative to the first collar and the roller pin is offset relative to the second collar. The first and second collars can be selectively arranged at rotational positions within the first and second cavities such that the roller pin can be positioned at distinct roller pin positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.

Abstract: A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a base plate coupled to the ring and having a recess, a first collar removably arranged within the recess and having a cavity formed therein, a second collar removably arranged within the cavity, and a roller pin fixedly coupled to the second collar. The cavity is offset relative to the first collar and roller pin is offset relative to the second collar. The first collar can be selectively arranged at rotational positions within the recess and the second collar can be selectively arranged at rotational positions within the cavity such that the roller pin can be positioned at distinct positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.

Abstract: A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a first inclined plate and a second inclined plate, the first inclined plate having an inclined surface facing a first inclined surface of the second inclined plate. A roller pin is coupled to a second inclined surface of the second inclined plate opposite the first inclined surface. The second inclined plate is adjustable in the circumferential direction such that the inclined surface of the first inclined plate and the first inclined surface of the second inclined plate slide against each other during adjustment of the second inclined plate so as to adjust an axial position and a circumferential position of the roller pin relative to the annular ring.

Abstract: Subsonic turbofan engines with variable outer guide vanes (OGVs) and associated methods. A subsonic turbofan engine includes an engine core configured to generate a torque, a fan configured to accelerate an air flow, an engine nacelle, and a plurality of OGVs positioned downstream of the fan. Each OGV is configured to transition among a plurality of OGV configurations defined between and including a nominal configuration and a reduced-drag configuration. The subsonic turbofan engine is configured to operate only at subsonic speeds. In examples, methods of operating a subsonic turbofan engine include transitioning each of a plurality of OGVs from a nominal configuration to a reduced-drag configuration. Transitioning each OGV from the nominal configuration to the reduced-drag configuration is performed while the subsonic engine operates at subsonic speeds.

Abstract: An air intake plenum for a gas turbine engine is provided that includes an axial centerline, first and second gas path surfaces, and a plurality of struts. The gas path surfaces are spaced apart from one another and define at least a portion of a plenum interior. The struts extend lengthwise between the gas path surfaces. Each strut has a cross-section geometry. The cross-section geometry has a center, and major and minor axes. The struts are circumferentially spaced apart from one another within the plenum. Each strut is oriented at a clocking angle theta. The clocking angle theta for each respective strut is disposed between the major axis of that strut and a line that intersects the cross-section geometry center of that strut and the axial centerline. At least one strut of the plurality of struts is oriented at a clocking angle theta that is greater than zero.

Abstract: A fan assembly includes a fan duct, an inlet fan, an outlet guide vane assembly, and a control system. The inlet fan includes fan blades adapted to rotate about a central axis to force 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 is configured to adjust a direction of the fan exit air. The outlet guide vane assembly includes a plurality of guide vanes that extend radially relative to the central axis and are configured to rotate to a first vane-pitch angle. The control system is configured to rotate the guide vanes redirect the fan exit air, vary a pressure downstream of the fan inlet, minimize intake flow distortion experienced by the inlet fan, reduce inlet fan vibratory response and/or improve fan operability margins.

Abstract: An un-ducted turbofan engine defining a radial direction and an axial direction that includes a core engine, a fan, a plurality of variable outlet guide vanes, and a pitch change mechanism. Each of the plurality of variable outlet guide vanes are attached in a rotatable manner to the core engine of the un-ducted turbofan engine. The pitch change mechanism is positioned radially between the engine air flowpath and the plurality of variable outlet guide vanes and coupled to at least one variable outlet guide vane of the plurality of variable outlet guide vanes for changing a pitch of the at least one variable outlet guide vane.

Abstract: The present disclosure relates to multistage centrifugal high purity hydrogen compressors for compressing low molecular weight fluids. More particularly, the present disclosure relates to the multistage high purity centrifugal hydrogen compressors wherein each stage comprises an vaned diffuser having at least two rows of a plurality of blades.

Abstract: A controller operates to control a gas turbine engine which has a first variable guide vane axially spaced apart from a compressor blade array and is rotatably mounted at a first location on a casing, having a vane axis of rotation at right angles to an operational axis. An adjustment drive is operable to rotate the first variable guide vane about its axis of rotation to a range of angles relative to the operational axis. The controller is operable to control the rotation of the first variable guide vane in dependence of engine shaft speed, wherein over a first range of engine shaft speed the angle of the first variable guide vane relative to the operational axis decreases with increasing engine speed, and over a second range of engine shaft speeds, the angle of the first variable guide vane relative to the operational axis increases with increasing engine speed.

Abstract: The present invention relates to a guide vane cascade for a turbomachine, which has guide vanes that are mounted adjustably about an axis of rotation, so as to change an inflow angle each time, wherein a first guide vane and a second guide vane arranged on the pressure side thereof, referred to a longitudinal axis of the turbomachine, are arranged with an axial offset, namely, the axis of rotation of the second guide vane is offset axially toward the back, wherein the first guide vane and the second guide vane are provided such that, in an adjusted state, they form together a tandem configuration in a radially outer region but together they delimit a divergent channel in a radially inner region.

Abstract: A power generation plant including a turbine (1) of a Kaplan, bulb, diagonal flow or propeller turbine type, a water intake (4) and a water run-off (5). Additional vanes vane (8) are deployable into a water passage formed between the water intake (4) and the housing of the turbine. Eddy flows formed in the water intake (4) are reduced by the additional vanes. The vanes allow the turbine operating range to be extended to cover smaller outputs.

Abstract: An adjustment device for adjusting several guide vanes of the engine, wherein the adjustment device includes at least one adjusting element that couples with the guide vanes and is mounted in an adjustable manner, a connection element that couples with the adjusting element, as well as a crank shaft for controlling an adjusting movement of the adjusting element, and the crank shaft has at least one coupling element which couples with the connection element and at which the connection element is hinged to transform a rotational movement of the crank shaft about a longitudinal axis of the crank shaft into an adjusting movement of the adjusting element for adjusting the guide vanes. The crank shaft has a modular design with at least two shaft modules that are arranged behind each other along the longitudinal axis of the crank shaft.

Abstract: A gas turbine engine includes a harmonic drive driven by an actuator, a drive shaft driven by the harmonic drive, the drive shaft with a first drive gear and a second drive gear. A first variable vane stage with a first actuator gear to direct drive one of a multiple of variable vanes, the first actuator gear meshed with the first drive gear; and a second variable vane stage with a second actuator gear to direct drive one of a multiple of variable vanes, the second actuator gear meshed with the second drive gear.

Abstract: A variable geometry turbine (VGT) for turbochargers incorporates a turbine nozzle having a plurality of vanes, each vane having an airfoil with an inner disc and an outer disc. A first nozzle plate incorporates pockets to receive the inner discs with the inner discs substantially flush with a nozzle surface on the first nozzle plate. A second nozzle plate has pockets to receive the outer discs with outer discs substantially flush with a second nozzle surface. An integral actuation system rotates the plurality of vanes for variation of the nozzle geometry.

Abstract: A variable vane includes a variable vane body that has an airfoil portion. The variable vane body is formed of a first material. A trunnion is attached at one end of the variable vane body. The trunnion includes a pivot formed of a second, different material.

Abstract: The invention relates to a turbocharger (1) with variable turbine geometry (VTG), having a turbine housing (2) with a supply duct (9) for exhaust gases, having a turbine rotor (4) which is rotatably mounted in the turbine housing (2); and having a guide grate (18), which surrounds the turbine rotor (4) radially at the outside, which has a blade bearing ring (6), which has a multiplicity of guide blades (7) which have in each case one blade shaft (8) mounted in the blade bearing ring (6), which has an adjusting ring (5) which is operatively connected to the guide blades (7) by means of associated blade levers (20) fastened to the blade shafts (8) at one of their ends, with each blade lever (20) having, at the other end, a lever head (23) which can be placed in engagement with an associated engagement recess (24) of the adjusting ring (5), and which has a bearing arrangement (28) for fixing the adjusting ring (5) to the blade bearing ring (6), wherein the bearing arrangement (28) is formed as a plain bearing ar

Abstract: A variable-nozzle turbocharger includes a turbine housing and a center housing, and a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. The vanes extend between the nozzle ring and an opposite wall formed by an insert in the turbine housing. A vane sealing member is supported on the insert, and has a portion disposed between distal ends of the vanes and the insert. This portion of the vane sealing member is configured to be contacted by the distal ends of the vanes when the vanes are in the closed position, while a clearance exists between the portion of the vane sealing member and the distal ends of the vanes when the vanes are in the open position.

Abstract: A variable pitch rectifier for a compressor includes a plurality of radial vanes having respectively, at outer and inner ends of same, outer and inner pivots, the inner pivots being received between two upstream and downstream inner rings, which are assembled by a link device. The link device includes only a set of angular sectors of elastically deformable stirrups, arranged to grip together the inner peripheral edges of the upstream and downstream rings by clamping one against the other.

Abstract: A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion.

Abstract: A vane pack for a VTG turbocharger is provided. The vane pack includes a plurality of vanes pivotably positioned between an inner surface of an upper vane ring and an inner surface of a lower vane ring. Clearances are defined between opposing cheek surfaces of the vanes and the inner surfaces of the vane rings. The vane pack is configured to minimize these clearances by applying an abradable coating is to the inner surface of the upper vane ring, the inner surface of the lower vane ring and/or cheek surface(s) of one or more of the vanes. In this way, an essentially zero clearance can be established without interfering with the proper function of the vanes. As a result, there can be gains in efficiency. Further wearing of the abradable coating may occur during turbocharger operation.

Abstract: A method and system for power generation including a turboexpander with at least two expansion stages, the turboexpander being connected to a power generation unit, is provided. The system includes a controller configured to control (i) an angle of a first inlet guide vane provided at an inlet of a first expansion stage of the turboexpander for maintaining an inlet pressure of the first expansion stage in a predetermined range, and (ii) an angle of a second inlet guide vane provided at an inlet of a second expansion stage of the turboexpander. The controller is configured to determine a highest power from determined powers of the power generation unit and a corresponding angle of the second inlet guide vane and to adjust the angle of the second inlet guide vane independent of the angle of the first inlet guide vane to achieve the highest power.

Abstract: A structure that mounts to a rotation shaft a lever that causes this rotation shaft to rotate, including a plurality of engaging members that are provided in the lever so as to be offset from the center axis of the rotation shaft, and that are capable of advancing toward and retracting from the outer periphery of the rotation shaft, and a plurality of abutted faces that are provided on the outer periphery of the rotation shaft so that the distal end faces of the plurality of engaging members respectively make contact, in which, when at least one of the engaging members and the abutted face that corresponds to that engaging member are in contact, relative rotation of the rotation shaft about the axis thereof in one direction with respect to the lever is restricted, and when another engaging member and another abutted face corresponding to the engaging member are in contact, relative rotation of the rotation shaft about the axis thereof in the other direction with respect to the lever is restricted.

Abstract: The nozzles include inlet ports circumferentially arranged into a group and an opening and closing valve disposed so as to be commonly functioned. This arrangement realizes a gas turbine with no deterioration of efficiency against fluctuation of gas inflow rate by only one heat-resistant moving component additionally installed. The variable nozzle number turbine according to this invention also realizes a turbine compressor with no surge limit when used as a regenerator. These turbines further realizes a small-sized gas turbine with improved fuel economy under partial load conditions and a turbocharger for regenerating electric power as well as improving efficiency of a displacement engine.

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 variable stator vane in a gas turbine engine has a journal provided with a circumferential recess. An aperture extends from the recess to a face of the journal directed towards the aerofoil portion of the vane. In operation of the engine, heated air, for example from a downstream compressor stage of the engine is admitted to the recess and flows through the aperture to, for example, the pressure surface of the aerofoil portion. The aerofoil portion is thereby heated, so preventing ice accretion on the vane.

Abstract: Certain example embodiments of this invention relate to techniques that harness air/wind power to charge and/or re-charge a battery of a vehicle that is at least partially electrically powered. In certain example embodiments, air/wind enters into a channel formed in a vehicle and turns a turbine which, in turn, generates electricity that may be used to charge and/or re-charge a battery of the vehicle. In certain example embodiments, the velocity of the air/wind may be increased within the channel by virtue of features including, for example, retractable and/or directional vanes and/or side wall elements that help create constricting locations (or choke points). In certain example embodiments, the velocity of the air/wind may be increased within the channel by virtue of features that produce the Coanda effect. Thus, for instance, both the Venturi effect and the Coanda effect may be used to increase the efficiency of the overall system.

Abstract: The flow path of exhaust gas to the turbine wheel (70) of a turbocharger is influenced by relative motion between two rings of vanes, at least one of which being provided on a vane ring. The outer ring of vanes contains a plurality of vanes (92, 122), the inner ring of vanes contains a plurality of vanes (93, 121), and the inner and outer vanes in registry forming a single generic vane shape. The aerodynamic effect of relative displacement of the outer ring of vanes to the inner ring of vanes produces a modulate-able control of exhaust flow to the turbine wheel.

Abstract: A fluid flow machine has a main flow path which is confined by a hub (3) and a casing (2) and in which at least one row of variable stator vanes (1) is arranged. The stator vanes (1) are rotatably borne around a rotary axis 4. On at least one of the hub (3) and the casing (2), at least one arrangement with at least two stator vanes (1) connected to a common rotary base (5) is provided, such that the at least two stator vanes (1) are rotatable around the rotary axis (4) when this multi-vane variable stator unit is varied.

Abstract: The present disclosure provides an improved multistage cryogenic liquefied gas expander for transforming the energy of a pressurized liquefied gas into electric energy, capable of operating at variable speeds, the improvement being a multistage cryogenic liquefied gas expander having at least two stages where only the first stage has a non-rotating nozzle ring having a plurality of adjustable position guide vanes.

Abstract: A continuous-flow machine, especially an axial compressor, having at least one guide vane ring that includes at least one row of adjustable guide vanes, whereby each guide vane is tapered relative to its vane body in the direction of its longitudinal axis as seen in a side view of the guide vane. In order to increase the stability of the flow in the continuous-flow machine, each row of guide vanes comprises first guide vanes and second guide vanes, whereby, as seen in a combined side view of a first guide vane and of a second guide vane, each first guide vane is tapered along its vane body in the lengthwise direction, and each second guide vane is tapered in the opposite direction.

Abstract: A compressor of a gas turbine system includes at least one inlet row having a plurality of inlet guide vanes. Also included is at least one stator row having a plurality of stator vanes. Further included is a first actuation mechanism operably connected to the at least one stator row, wherein the first actuation mechanism is configured to positionally manipulate the at least one stator row. Yet further included is a second actuation mechanism operably connected to the at least one stator row, wherein the second actuation mechanism is configured to positionally manipulate the at least one stator row.

Abstract: A system and a method for adjusting an angle of at least one stator vane of a low pressure compressor (LPC) of a two spool gas turbine engine is disclosed. Variable stator vanes are rotatably coupled to a stationary case in one of the stages of the LPC. An actuator is coupled to at least one of the variable stator vanes for imparting rotation of the stator vane about a radius of the case. Various coupling or linkage arrangements may be made so that rotation of one vane results in rotation of the other vanes disposed along the case. The controller includes the stored constraints, the ability to estimate operating condition, and the ability to estimate optimum targets.

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 variable vane actuation system is disclosed herein. The variable vane actuation system includes a ring member disposed for pivoting movement about a centerline axis. The ring member is engaged with a plurality of vanes in a turbine engine such that the plurality of vanes pivot in response to the pivoting movement of the ring member. The variable vane actuation system also includes a ring moving device engaged with the ring member at first and second positions spaced from one another about the centerline axis. The ring moving device is operable to apply first and second forces, respectively, at the first and second positions to pivot the ring member.

Abstract: A device is provided for pivoting at least one pivotable element in a gas turbine engine between a first and a second position in order to influence a gas flow in an annular gas duct in at least one of the positions. The device includes a moveable annular member which is arranged externally around the gas duct and is connected to the pivotable element in order to effect the pivoting of the pivotable element. The annular member is more specifically arranged to be displaced in a substantially axial direction and arranged to pivot the pivotable element when it is displaced axially.

Abstract: An inlet guide vane assembly includes an active control feedback system and a plurality of inlet guide vanes. The inlet guide vanes are variable between a plurality of positions. Each of the plurality of inlet guide vanes is positioned in response to an output of the activate control feedback system.

Abstract: A turbo chiller equipped with a high-efficiency two-stage turbo compressor is provided. In a turbo chiller including a control unit for controlling the degrees of opening of first inlet guide vanes of a first impeller and second inlet guide vanes of a second impeller, the control unit has a slave mode in which the second inlet guide vanes are operated so as to be dependent on the first inlet guide vanes in a slave-mode priority region, and an independent mode in which the degree of opening of the second inlet guide vanes is increased independently of the first inlet guide vanes in an independent-mode priority region.

Abstract: Disclosed herein is a turbine variable position guide vane actuation system. The system includes, a plurality of variable position guide vanes, a plurality of actuators with each actuator in operable communication with one of the plurality of variable position guide vanes, and each of the plurality of actuators having a pin. The system further having at least one structure, movable parallel to an axis of the turbine, having a plurality of slots and each of the plurality of slots is in operable communication with one of the pins.

Abstract: Method and nozzle adjustment mechanism for adjusting a flow of a fluid. The nozzle adjustment mechanism includes a fixed ring; at least a vane connected to the fixed ring by a pivot pin and configured to rotate with the pivot pin; an adjusting ring rotatably connected to the fixed ring and configured to rotate around a longitudinal axis of the nozzle adjustment mechanism; and a connection mechanism connecting the at least a vane to the adjusting ring and configured to move the at least a vane when the adjusting ring is rotated, the connection mechanism including a lever component and a link component connected to each other. The lever component is connected to the at least a vane and the link component is connected to the adjusting ring.

Abstract: A compressor assembly has a fluid inlet positioned to facilitate the passage of a fluid. The compressor assembly includes a compressor housing defining a compressor inlet and an impeller rotatably supported at least partially within the compressor housing. The impeller includes an inducer portion. A fluid treatment member is disposed adjacent the compressor housing and between the compressor inlet and the inducer portion and an inlet vane assembly I disposed adjacent the compressor inlet and includes a plurality of vanes. Each of the vanes is movable between a first position and a second position to control the quantity of fluid that passes to the impeller.

Abstract: A gas turbine compressor presents a first fixed stage having a plurality of first adjustable vanes and a further fixed stage, which has an inner ring extending about a first axis; an outer ring arranged about the inner ring and coaxial with the inner ring; and a plurality of second adjustable vanes, each of which extends along a second axis in an essentially radial direction with respect to the first axis between the inner ring and the outer ring; and it is adjustable about the corresponding second axis independently from the first adjustable vanes.

Abstract: A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) at least one step that defines sealing surfaces positioned to be substantially abutted by airfoil surfaces of the vanes in the closed position of the vanes and to be spaced from the airfoil surfaces in positions other than the closed position. This substantial abutment between the airfoil surfaces and the sealing surfaces serves to substantially prevent exhaust gas from leaking past the ends of the airfoil portions. At the same time, clearances between the nozzle ring face and the end faces of the airfoil portions can be sufficiently large to prevent binding of the vanes under all operating conditions.

Abstract: A variable-nozzle assembly comprises a nozzle ring and an array of vanes circumferentially spaced about the nozzle ring and rotatably mounted to the nozzle ring such that the vanes are variable in setting angle, and an insert having a tubular portion and an annular nozzle portion extending generally radially out from one end of the tubular portion. A plurality of axially extending holes extend through a thickness of the nozzle portion. A plurality of spacers have first ends joined to the nozzle ring, opposite second ends of the spacers being engaged in the holes and secured to the nozzle portion by welds formed at the second surface. An annular groove is defined in the second surface of the nozzle portion radially inward of and proximate to the holes. Alternatively or additionally, discrete recesses are formed in the second surface adjacent the holes. The groove and/or recesses facilitate weld penetration.

Abstract: A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window.

Abstract: A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a moveable actuation rod. The control mechanism further comprises a first linkage arrangement which includes a first bell crank and which operatively connects the actuation rod to a first component of the gas turbine engine. 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 and which operatively connects the actuation rod to a second component of the gas turbine engine. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component.

Abstract: Guide vanes are supported in a two-part or multipart housing (32, 33). Housing separation takes place radially in the region of the bearing point (25) of the vane shaft so that the separating joint (36) between the housing parts (32, 33) leads through the bearing openings (34) which are designed to hold the vane shafts. The completely round opening (34) leads to the bearing point of the vane shaft having large-area support in any position. Thus high surface pressures can be avoided.

Abstract: The invention relates to a system for controlling at least two variable-geometry equipments of a gas turbine engine. The engine comprises at least a first core rotating at a first speed and a second core rotating at a second speed, the first equipment (10b) comprising at least one variable-pitch stator blade (14) of a compressor of the first core, the second equipment (110) comprising 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; it comprises an actuator (24) which actuates both equipments. Thanks to the invention, the control system makes it possible to reduce the number of parts of the gas turbine engine while retaining said equipments on distinct cores, thereby allowing them to fulfill their function.

Abstract: The invention relates to a system for controlling at least two variable-geometry equipments of a gas turbine engine. The engine comprises at least a first core rotating at a first speed and a second core rotating at a second speed, the first equipment (10b) comprising at least one variable-pitch stator blade (14) of a compressor of the first core, the second equipment (110) comprising 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; it comprises an actuator (24) which actuates both equipments. Thanks to the invention, the control system makes it possible to reduce the number of parts of the gas turbine engine while retaining said equipments on distinct cores, thereby allowing them to fulfill their function.