EP4444995B1 - Steuerungsvorrichtung für ein luftstromleitsystem, insbesondere in einer turbomaschine eines flugzeugs - Google Patents

Steuerungsvorrichtung für ein luftstromleitsystem, insbesondere in einer turbomaschine eines flugzeugs

Info

Publication number
EP4444995B1
EP4444995B1 EP22826603.7A EP22826603A EP4444995B1 EP 4444995 B1 EP4444995 B1 EP 4444995B1 EP 22826603 A EP22826603 A EP 22826603A EP 4444995 B1 EP4444995 B1 EP 4444995B1
Authority
EP
European Patent Office
Prior art keywords
control rod
connecting member
rod
angle
upstream
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP22826603.7A
Other languages
English (en)
French (fr)
Other versions
EP4444995A1 (de
Inventor
Thibaut Maxime JAVOY
Christophe Boris BAUCHEFF
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Publication of EP4444995A1 publication Critical patent/EP4444995A1/de
Application granted granted Critical
Publication of EP4444995B1 publication Critical patent/EP4444995B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/20—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/329—Application in turbines in gas turbines in helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/90—Variable geometry
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/56—Kinematic linkage, i.e. transmission of position using cams or eccentrics

Definitions

  • the present invention relates to the field of aircraft, and in particular to a device for controlling an airflow guidance system, an aircraft turbomachine comprising such a device and a single-engine helicopter comprising such a turbomachine.
  • the invention relates to controlling the position of air flow guide elements.
  • a turbomachine comprises a compressor, a combustion chamber located at the outlet of said compressor, a high-pressure turbine intended to drive the compressor in rotation and a low-pressure turbine intended to drive the blades of the aircraft in rotation.
  • the turbomachine further comprises an airflow guidance system, called “inlet guide vanes”, with the acronym “IGV” in English terms, comprising a plurality of variable-pitch inlet guide vanes or blades, positioned upstream of the compressor and making it possible to improve the efficiency of the compressor, and thus the thermodynamic cycle of the engine in cruising mode.
  • IGV airflow guidance system
  • variable timing we mean the synchronization of the angular position of all the blades of the same stage by means of a control ring or crown secured to all the blades. Each blade is connected to the control ring by a control rod.
  • the piston movement control is generally carried out by a fluid distributor, for example oil in the case of hydraulic control.
  • the document FR 3 051 830 discloses a device for controlling an air flow guidance system comprising at least one blade that can rotate about an axis of the blade between a first angle and a second angle, an actuator comprising a body inside which a piston is mounted in translation, and a control rod comprising a downstream end connected to a control ring, the actuator being configured to drive the piston in movement between a first extreme position and a second extreme position of a nominal operating range and the downstream end of the control rod between a first extreme position and a second extreme position of a nominal operating range in which the blade is movable between a first angle and a second angle.
  • WO2022/101260 state of the art referred to in Art. 54(3) EPC discloses a device for controlling an air flow guidance system comprising an actuator configured to drive a control rod in translation between a first and a second extreme position of a nominal operating range in which a blade of the flow guidance system is movable between a first and a second angle, the control rod being connected to the blade by a control lever comprising a first control rod and a second control rod articulated relative to each other.
  • the actuator is configured to bring the control rod into a safety position located beyond the second extreme position of the nominal operating range and orient the blade by a safety pitch angle between the first angle and the second angle.
  • the present invention therefore aims to overcome the drawbacks of the control devices of the aforementioned air flow guidance systems.
  • the aim of the invention is to improve safety in the event of failure of an element of the blade control kinematics and to reduce maintenance costs in the event of failure of the control device.
  • the actuator is configured to move the piston between a first extreme position and a second extreme position of a nominal operating range in which the blade is movable between a first angle and a second angle.
  • the actuator is also configured to cause the downstream end of the control rod to move between a first extreme position and a second extreme position of the nominal operating range.
  • the control device comprises a drive mechanism connecting an upstream end of the actuating rod to an upstream end of the control rod, opposite the downstream end.
  • the drive mechanism is configured to, in the event of a failure of the control device, bring the downstream end of the control rod into a safety position located between the first extreme position and a second extreme position of the nominal operating range and in which the blade is oriented at a safe setting angle between the first angle and the second angle.
  • the actuator is configured to overtravel the piston into a safety position located beyond said second extreme position of the piston in which the blade is oriented at a safe setting angle between the first angle and the second angle.
  • the overtravel of the piston ensures that the downstream end of the control rod moves to a safety position.
  • the drive mechanism is thus integrated directly between the connection of the control rod and the actuating rod, which improves its accessibility in the event of maintenance.
  • the drive mechanism comprises a first connecting member comprising a first end secured to the upstream end of the actuating rod and a second end connected to the control rod via a second connecting member.
  • the second connecting member comprises a first end articulated relative to the second free upstream end of the control rod, and a second end articulated relative to the second end of the first connecting member.
  • the drive mechanism may further comprise a guide casing fixed to the body of the jack and comprising at least one guide rail cooperating with at least one guide pin carried by the second connecting member.
  • two guide rails could be provided cooperating with one or two guide pins carried by the second connecting member.
  • the guide rail comprises a rectilinear main portion, substantially parallel to the axis of the turbomachine and a curved end portion, said guide pin being in a collection position inside said end portion in the safety position of the control rod.
  • the cylinder rod and thus the control rod is movable in translation in the cylinder chamber between the two extreme positions of the nominal operating range of the turbomachine.
  • the guide casing comprises two opposite guide rails each cooperating with a bearing carried by the second connecting member.
  • bearings makes it possible to improve reliability, and in particular to limit wear and tear in the movement of said second connecting member.
  • the second end of the control rod articulated relative to the first end of the second connecting member is located upstream of the end of the actuating rod secured to the first connecting member.
  • the attachment of the first connecting member to the actuating rod is located downstream of the upstream end of the control rod.
  • the second upstream end of the control rod articulated relative to the first end of the second connecting member is located downstream of the upstream end of the actuating rod secured to the first connecting member.
  • the attachment of the first connecting member to the actuating rod is located upstream of the upstream end of the control rod.
  • the actuating rod is tubular and is axially traversed by the control rod, the latter being configured to be able to move inside the actuating rod.
  • the invention relates to an aircraft turbomachine comprising, from upstream to downstream in the direction of flow of the air flow, an inlet sleeve receiving air, a centrifugal compressor, an annular combustion chamber, located downstream of the compressor, a high-pressure power turbine intended to rotate the compressor, an outlet turbine intended to rotate an output shaft, an air flow guidance system positioned upstream of the compressor and a device for controlling said air flow guidance system as described previously.
  • the invention relates to a single-engine helicopter comprising a turbomachine as defined above.
  • upstream and downstream are defined in relation to the direction of air flow in the turbomachine.
  • FIG. 1 is shown very schematically an axial section of a turbomachine 10, with central axis XX' which corresponds to the axis of a power shaft (or low pressure shaft) of the turbomachine.
  • the turbomachine can equip, by way of non-limiting example, single-engine helicopters.
  • the turbomachine 10 comprises, from upstream to downstream in the direction of flow of the air flow, an inlet sleeve 11 receiving air, a centrifugal compressor 12, for example with one or two stages, configured to suck in the air flow F.
  • the turbomachine 10 further comprises an annular combustion chamber 13, for example with reverse flow, located downstream of the compressor 12, a high-pressure power turbine 14 intended to rotate the compressor 12 by a high-pressure shaft 15 and an outlet turbine 16, for example, with a single stage, intended to rotate an outlet shaft 17 by means of a low-pressure shaft 18, coaxial with the high-pressure shaft 15, and a reduction system 19.
  • the output shaft 17 is connected to the blades of the aircraft.
  • the turbomachine 10 further comprises an air flow guidance system 20, called “inlet guide vanes”, with the acronym “IGV” in English terms, comprising a plurality of variable-pitch guide vanes or blades 21, positioned upstream of the compressor 12.
  • IGV air flow guidance system
  • the plurality of variable-pitch blades 21 comprises a main blade controlled in rotation around its axis 21a, and a plurality of secondary blades whose movement is synchronized with the movement of the main blade.
  • the blading consisting of the blades 21 is called “stator”, that is to say that each blade is mobile in rotation around its own axis of rotation.
  • the axis of rotation 21a of each blade 21 is here perpendicular to the central axis X-X' of the turbomachine 10.
  • the turbomachine 10 further comprises a device 30 for controlling the air flow guidance system 20.
  • the control device 30 of the airflow system 20 comprises an actuator 31 and a control rod 34 connected by its first end 34a to a control lever 35 of a main blade of the plurality of variable-pitch blades 21.
  • variable pitch blades we mean the synchronization of the position of all the secondary blades relative to a main blade.
  • the control rod 34 is driven in translation by said actuator 31 via a drive mechanism 40.
  • the actuator 31 may be, in a non-limiting manner, a jack comprising a body 32 fixed to a casing (not referenced) and delimiting a cylindrical chamber 32a inside which is mounted in translation a piston 32a secured to a tubular jack rod 33 or actuating rod.
  • the tubular cylinder rod 33 comprises an upstream end 33a connected to a second upstream end 34b of the control rod 34, opposite the first downstream end 34a connected to the blade 21, via the drive mechanism 40.
  • the control rod 34 is mounted in translation in the tubular cylinder rod 33.
  • the control rod 34 is connected to the axis of the main blade 21 by the control lever 35 articulated relative to the first free end 34a of the control rod 34 opposite the end 34b connected to the actuator 31.
  • the control lever 35 will not be described further in the remainder of the description.
  • the body 32 of the cylinder may comprise two orifices (not shown) opening into the chamber for the entry and exit of a fluid, intended to slide the piston inside said cylinder body along an axis of movement substantially parallel to the central axis X-X' of the turbomachine 10.
  • the cylinder chamber is supplied with fluid, for example oil, by an external energy source conveying the fluid into the cylinder chamber via the first port.
  • fluid for example oil
  • the latter moves axially along the displacement axis X-X', together with the control rod 34.
  • the external energy source can be a hydraulic control system including a distributor or servo valve configured to distribute the fluid in the cylinder chamber. Depending on the servo valve, it is possible to know the piston stroke.
  • the piston of the cylinder 32a, and thus the control rod 34, is movable in translation in the chamber of the cylinder between two extreme positions P1', P2'; P1, P2 of a nominal operating range of the turbomachine.
  • the main blade 21 is movable continuously between a first angle and a second angle defined respectively between the main blade 21 and the horizontal axis parallel to the axis of movement X-X'.
  • the control device 30 is configured to guide the piston 33, and thus the control rod 34, to a safety position PS', PS in which the stroke of the piston is known, and thus the opening angle of the blades 21.
  • the safety position PS', PS corresponds to an opening position of the blades in which the turbomachine can operate safely.
  • the main blade 21a is moved to a safe angle between the first and second angles of nominal operation.
  • the safety position P'S of the cylinder rod 33 is far from one of the positions P1' , P2' of the nominal operating range.
  • the cylinder rod 33 is configured to perform an overtravel beyond one of its extreme positions P2'.
  • the drive mechanism 40 comprises a first connecting member 42 comprising a first end 42a secured to the upstream end 33a of the tubular cylinder rod 33 and a second end 42b connected to the control rod 34 via a second connecting member 44.
  • the second connecting member 44 or connecting rod comprises a first end 44a articulated relative to the second free end 34b of the control rod 34, and a second end 44b articulated relative to the second end 42b of the first connecting member 42.
  • the first and second connecting members 42, 44 are two separate parts connected to each other by a pivot connection.
  • the second end 34b of the control rod 34 articulated relative to the first end 44a of the second connecting member 44 is located upstream of the end 33a of the tubular cylinder rod 33 secured to the first connecting member 42.
  • the attachment of the first connecting member 42 to the tubular cylinder rod 33 is located downstream of the upstream end 34b of the control rod 34.
  • the drive mechanism 40 further comprises a guide casing 46 fixed to the body 32 of the jack and comprising a guide rail 47 cooperating with a guide pin 44c carried by the second guide member 44.
  • a guide casing 46 fixed to the body 32 of the jack and comprising a guide rail 47 cooperating with a guide pin 44c carried by the second guide member 44.
  • two guide rails could be provided cooperating with one or two guide pins carried by the second connecting member 44.
  • the guide rail 47 comprises a rectilinear main portion 47a, substantially parallel to the axis XX' of the turbomachine and an end portion 47b at one end of said rail.
  • the end portion 47b here has a curved shape.
  • the cylinder rod 33 and thus the control rod 34 is movable in translation in the cylinder chamber between the two extreme positions P1', P2'; P1, P2 of the nominal operating range of the turbomachine.
  • the extreme position P1', P2' of the cylinder rod 33 is defined by the cylinder. Indeed, in a manner known per se, any cylinder has internal stops which define the stroke of the piston in the body of the cylinder. Thus, the end portion 47b does not serve as a stop before a stop of the cylinder, at the risk of damaging an element of the drive mechanism 40.
  • the drive mechanism 40 is configured to bring the control rod 34 into a safety position PS in the event of a failure of the control device 30.
  • the safety position PS of the control rod 34 is located between the two extreme positions P1, P2 of the control rod 34 in nominal operation.
  • the guide pin 44c is in a collection position inside said end portion 47b in the safety position PS of the control rod 34.
  • the drive mechanism 40 is integrated directly between the control rod connection and the cylinder rod, which improves its accessibility in the event of maintenance.
  • the control rod 34 is configured to move in translation along the movement axis X-X' and along an axis perpendicular to said movement axis X-X' during the movement of the cylinder rod 33.
  • the control rod 34 has two degrees of freedom.
  • control rod 34 The movement of the control rod 34 is illustrated in the Figures 3A, 3B and 3C .
  • FIG. 3A represents the first extreme position P1 of the free end of the control rod 34 when the cylinder rod 33 is in the first extreme position P1' of the nominal operating range of the turbomachine 10.
  • the main blade 21 is open by a first angle (not shown), for example between 45° and 75°, for example greater than or equal to 60°.
  • FIG. 3B represents the second extreme position P2 of the free end of the control rod 34 when the cylinder rod 33 is in the second extreme position P2' of the nominal operating range of the turbomachine 10.
  • the drive mechanism 40 When moving the cylinder rod 33 from the first extreme position P1' to the second extreme position P2' of the nominal operating range, the drive mechanism 40 is guided in translation in the guide rail 47, in particular on its main portion 47a.
  • the main blade 21 When moving the control rod 34 from the first extreme position P1 to the second extreme position P2, the main blade 21 is progressively movable from the first angle to a second angle (not shown) for example equal to 0°.
  • the flow rate is maximum in this second extreme position P2.
  • FIG. 3C represents the safety position PS of the free end of the control rod 34 when the cylinder rod 33 overtravels or extends beyond the second extreme position P2 of the nominal operating range of the turbomachine 10.
  • the drive mechanism 40 When the cylinder rod 33 moves from the first extreme position P1' to the second extreme position P2' of the nominal operating range, the drive mechanism 40 is guided in translation in the guide rail 47 towards the end portion 47b.
  • the second connecting member 44 then performs a rotational movement around its second end 44a articulated relative to the upstream end 34b of the control rod 34. It is the overtravel of the cylinder 32a which ensures the movement of the control rod 34 into the safety position.
  • the main blade 21 When moving the control rod 34 from the second extreme position P2 to the safety position PS, the main blade 21 is progressively movable from the second angle to a safety pitch angle between the first and second end angles of the nominal operating range, for example between 5° and 15°, for example equal to 8°.
  • the pitch angle safe position is linked to the safety position PS' defined by the overtravel of the cylinder rod 33.
  • an additional overtravel of the cylinder rod 33 would also allow an overtravel of the control rod 34 in the opposite direction so as to move the safety position PS. This would bring the safe setting angle back to a value less distant from the first end angle of the nominal operating range.
  • the safety position makes it possible to ensure the operation of the turbomachine, even in the event of a failure of an element of the blade control kinematics.
  • the second upstream end 34b of the control rod 34 articulated relative to the first end 44a of the second connecting member 44 is located downstream of the upstream end 33a of the tubular cylinder rod 33 secured to the first connecting member 42.
  • bearings improves reliability, and in particular the limitation to wear of the movement of said second connecting member 44.
  • control device 30 is not limited to a turbomachine and can be used to ensure the movement of the control rod and thus the orientation of vanes mounted upstream of a steerable wheel towards a safety position in the event of failure of an element of said control device.
  • the safe setting angle of the vanes is included in the setting angle range useful for the nominal operation of the steerable wheel. This safe setting angle is reached during an overtravel of an actuator rod or cylinder of the control device.
  • the invention it is possible to bring the control rod and thus the blade pitch angle to a reliable safety position, while facilitating maintenance in the event of failure of the drive mechanism.
  • the drive mechanism 40 is integrated directly between the connection of the control rod and the cylinder rod, which improves its accessibility in the event of maintenance.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Fluid-Pressure Circuits (AREA)

Claims (11)

  1. Vorrichtung (30) zur Steuerung eines Luftstromleitsystems (20), umfassend:
    - wenigstens eine Schaufel (21), die um eine Achse (21a) der Schaufel zwischen einem ersten Winkel und einem zweiten Winkel rotatorisch beweglich ist,
    - einen Aktuator (31), der einen Körper (32) umfasst, in dessen Innerem ein Kolben (32a) translatorisch angebracht ist, der mit einer Betätigungsstange (33) fest verbunden ist,
    - eine Steuerstange (34), die in der Betätigungsstange (33) translatorisch angebracht ist und ein mit der Achse (21a) der Schaufel verbundenes nachgelagertes Ende (34a) umfasst, wobei der Aktuator (31) ausgelegt ist, um den Kolben (32a) zwischen einer ersten Endposition (P1') und einer zweiten Endposition (P2') eines Nennbetriebsbereichs und das nachgelagerte Ende (34a) der Steuerstange (34) zwischen einer ersten Endposition (P1) und einer zweiten Endposition (P2) eines Nennbetriebsbereichs verlagernd anzutreiben, in dem die Schaufel (21) zwischen einem ersten Winkel und einem zweiten Winkel beweglich ist, wobei die Vorrichtung einen Antriebsmechanismus (40) umfasst, der ein vorgelagertes Ende (33a) der Betätigungsstange (33) mit einem vorgelagerten Ende (34b) der Steuerstange (34), das dem nachgelagerten Ende (34a) gegenüberliegt, verbindet, wobei der Aktuator (31) ausgelegt ist, um bei Ausfall der Steuervorrichtung einen Überhub des Kolbens (32a) in eine Sicherheitsposition (PS') auszuführen, die sich jenseits der zweiten Endposition (P2') des Kolbens befindet und beim Überhub des Kolbens (32a) in die Sicherheitsposition (PS'), wobei der Antriebsmechanismus (40) ausgelegt ist, um das nachgelagerte Ende (34a) der Steuerstange (34) in eine Sicherheitsposition (PS) zu bringen, die sich zwischen der ersten Endposition (P1) und einer zweiten Endposition (P2) des Nennbetriebsbereichs befindet, und in der die Schaufel (21) in einem Sicherheits-Einstellwinkel zwischen dem ersten und dem zweiten Winkel ausgerichtet wird.
  2. Vorrichtung (30) nach Anspruch 1, wobei der Antriebsmechanismus (40) ein erstes Verbindungselement (42) umfasst, das ein erstes Ende (42a) umfasst, das mit dem vorgelagerten Ende (33a) der Betätigungsstange (33) fest verbunden ist, und ein zweites Ende (42b), das über ein zweites Verbindungselement (44) mit der Steuerstange (34) verbunden ist.
  3. Vorrichtung (30) nach Anspruch 2, wobei das zweite Verbindungselement (44) ein erstes Ende (44a) umfasst, das in Bezug auf das vorgelagerte freie zweite Ende (34b) der Steuerstange (34) gelenkig ist, und ein zweites Ende (44b), das in Bezug auf das zweite Ende (42b) des ersten Verbindungselements (42) gelenkig ist.
  4. Vorrichtung (30) nach Anspruch 2 oder 3, wobei der Antriebsmechanismus (40) ferner ein am Körper (32) des Zylinders befestigtes Führungsgehäuse (46) umfasst und mindestens eine Führungsschiene (47) umfasst, die mit mindestens einem Führungsstift (44c) zusammenwirkt, der von dem zweiten Führungselement (44) getragen wird.
  5. Vorrichtung (30) nach Anspruch 4, wobei die Führungsschiene (47) einen geraden, im Wesentlichen parallel zur Achse (X-X') der Turbomaschine verlaufenden Hauptabschnitt (47a) und einen gebogenen Endabschnitt (47b) umfasst, wobei sich der Führungsstift (44c) in einer Aufnahmeposition innerhalb des Endabschnitts (47b) in der Sicherheitsposition (PS) der Steuerstange (34) befindet.
  6. Vorrichtung (30) nach Anspruch 4 oder 5, wobei das Führungsgehäuse (46) zwei gegenüberliegende Führungsschienen (47, 48) umfasst, die jeweils mit einem Lager (50) zusammenwirken, das von dem zweiten Verbindungselement (44) getragen wird.
  7. Vorrichtung (30) nach einem der Ansprüche 2 bis 6, wobei das zweite Ende (34b) der Steuerstange (34), das in Bezug auf das erste Ende (44a) des zweiten Verbindungselements (44) gelenkig ist, sich stromaufwärts zum vorgelagerten Ende (33a) der Betätigungsstange (33) befindet, das mit dem ersten Verbindungselement (42) fest verbunden ist.
  8. Vorrichtung (30) nach einem der Ansprüche 2 bis 6, wobei das vorgelagerte zweite Ende (34b) der Steuerstange (34), das in Bezug auf das erste Ende (44a) des zweiten Verbindungselements (44) gelenkig ist, sich stromabwärts zum vorgelagerten Ende (33a) der Betätigungsstange (33) befindet, das mit dem ersten Verbindungselement (42) fest verbunden ist.
  9. Vorrichtung (30) nach einem der vorhergehenden Ansprüche, wobei die Betätigungsstange (33) rohrförmig ist und axial von der Steuerstange (34) durchquert wird, wobei letztere ausgelegt ist, um sich innerhalb der Betätigungsstange (33) bewegen zu können.
  10. Luftfahrzeug-Turbomaschine (10), umfassend, von stromaufwärts nach stromabwärts in Strömungsrichtung des Luftstroms, einen Luft aufnehmenden Einlassstutzen (11), einen Zentrifugalverdichter (12), eine ringförmige Brennkammer (13), die sich stromabwärts zum Verdichter (12) befindet, eine Hochdruck-Leistungsturbine (14) für den Rotationsantrieb des Verdichters (12), eine Ausgangsturbine (16) für den Rotationsantrieb einer Ausgangswelle (17), ein Luftstromleitsystem (20), das stromaufwärts zum Verdichter (12) positioniert ist und eine Vorrichtung (30) zur Steuerung des Luftstromleitsystems (20) nach einem der vorhergehenden Ansprüche.
  11. Einmotoriger Hubschrauber, der eine Turbomaschine (10) nach Anspruch 10 umfasst.
EP22826603.7A 2021-12-07 2022-12-02 Steuerungsvorrichtung für ein luftstromleitsystem, insbesondere in einer turbomaschine eines flugzeugs Active EP4444995B1 (de)

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FR2113090A FR3129971B1 (fr) 2021-12-07 2021-12-07 Dispositif de commande d’un système de guidage du flux d’air, notamment dans une turbomachine d’aéronef
PCT/FR2022/052231 WO2023105143A1 (fr) 2021-12-07 2022-12-02 Dispositif de commande d'un système de guidage du flux d'air, notamment dans une turbomachine d'aéronef

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GB1083156A (en) * 1965-05-17 1967-09-13 Gen Electric Improvements in control mechanism
US3535605A (en) 1968-06-17 1970-10-20 Cutler Hammer Inc Static shunt motor crane hoist control system with limit stop backout control
US3779665A (en) * 1972-09-22 1973-12-18 Gen Electric Combined variable angle stator and windmill control system
FR2928979B1 (fr) * 2008-03-19 2015-05-01 Snecma Dispositif de commande d'aubes a calage variable dans une turbomachine.
EP2881595B1 (de) * 2013-12-03 2018-08-22 Ansaldo Energia IP UK Limited Vorrichtung für Notbetrieb von Aktuatoren
FR3051830B1 (fr) * 2016-05-30 2019-12-27 Safran Aircraft Engines Dispositif d'actionnement d'un element mobile d'une turbomachine
GB201717091D0 (en) * 2017-10-18 2017-11-29 Rolls Royce Plc A variable vane actuation arrangement
EP3502484A1 (de) * 2017-12-19 2019-06-26 Siemens Aktiengesellschaft Verstellgestänge
DE102018217435B4 (de) * 2018-10-11 2021-04-01 Rolls-Royce Deutschland Ltd & Co Kg Verstelleinrichtung mit wenigstens einer Führungseinrichtung für die Verstellung mehrerer Leitschaufeln eines Triebwerks
FR3116080B1 (fr) * 2020-11-10 2022-11-04 Safran Helicopter Engines Dispositif de commande d’un système de guidage du flux d’air, notamment dans une turbomachine d’aéronef

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CN118355178A (zh) 2024-07-16
FR3129971B1 (fr) 2024-11-29
US12486782B2 (en) 2025-12-02
US20250027426A1 (en) 2025-01-23
CA3238900A1 (fr) 2023-06-15
WO2023105143A1 (fr) 2023-06-15
FR3129971A1 (fr) 2023-06-09

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