EP3502484A1 - Liaison de réglage - Google Patents

Liaison de réglage Download PDF

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Publication number
EP3502484A1
EP3502484A1 EP17208561.5A EP17208561A EP3502484A1 EP 3502484 A1 EP3502484 A1 EP 3502484A1 EP 17208561 A EP17208561 A EP 17208561A EP 3502484 A1 EP3502484 A1 EP 3502484A1
Authority
EP
European Patent Office
Prior art keywords
push rod
adjustment
compressor
coupled
vanes
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.)
Withdrawn
Application number
EP17208561.5A
Other languages
German (de)
English (en)
Inventor
Stephen Batt
David Overton
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP17208561.5A priority Critical patent/EP3502484A1/fr
Publication of EP3502484A1 publication Critical patent/EP3502484A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially 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
    • 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
    • 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
    • F05D2270/00—Control
    • F05D2270/50—Control logic embodiments
    • F05D2270/58—Control logic embodiments by mechanical means, e.g. levers, gears or cams

Definitions

  • the present disclosure relates to an adjustment linkage.
  • the disclosure is concerned with an adjustment linkage for a guide vane of a compressor for a gas turbine engine.
  • a gas turbine comprises a turbine and a compressor driven by the turbine.
  • a compressor may consist of multiple stages of stator vanes which are non-rotatable about the operational axis, and rotor blades which are rotatable about the operational axis.
  • the gas turbine is subjected to varying operating conditions resulting in different aerodynamic flow conditions within the compressor.
  • variable guide vanes In order to adapt the compressor performance to different flow conditions, it is known to provide the compressor with variable guide vanes (VGV).
  • VV variable guide vanes
  • the variable guide vanes are pivotable/rotatable about their longitudinal axis in order to adjust their angle relative to the operational axis of the engine (i.e. the axial flow direction through the compressor), and hence relative to rotor blades downstream.
  • Operational flow conditions may induce a stall condition during start-up and at off-design conditions. This may result in aerodynamic noise, loss of efficiency and excessive rotor vibration.
  • compressor stall may be reduced by rotating the variable guide vanes to increase the blade angle relative to the operational axis and reduce the compressor throat area, thus reducing the mass flow of air through the compressor.
  • the compressor (14) may comprise a casing (50) which extends along, and is centred on, an operational axis (20).
  • an adjustment drive (154) mounted to the casing (50) in a second location (204).
  • the adjustment linkage (200a) may comprise a push rod (150).
  • a first end (206) of the push rod (150) may be configured to be coupled to the adjustment ring (140).
  • a second end (208) of the push rod (150) may be configured to be coupled to an output (152) of the adjustment drive (154) via a displacement mechanism (210) configured to vary the directional output of the adjustment drive (154).
  • the push rod may have a longitudinal axis (212) which extends between its first end (206) and second end (208).
  • a push rod lever (220) may be pivotably coupled to the push rod (150) between the first end (206) and second end (208) of the push rod (150).
  • the push rod lever (220) may be configured to pivotably mount to a third location (222) on the casing (50) to thereby anchor the push rod lever (220) to the casing (50) such that the push rod (150) is pivotable about the coupling with the push rod lever (220).
  • the push rod lever (220) may be pivotable about its coupling to the casing (50) to thereby allow the push rod (150) to move in a direction along its longitudinal axis (212) and restrict the push rod (150) from moving in a direction at an angle to its longitudinal axis (212).
  • the adjustment linkage (200a) may comprise a push rod (150).
  • a first end (206) of the push rod (150) may be configured to be coupled to an adjustment ring (140) for actuation of a variable guide vane (8a).
  • a second end (208) of the push rod (150) may be configured to be coupled to an output (152) of an adjustment drive (154) via a displacement mechanism (210) configured to convert a single direction rotational input from the adjustment drive to a reciprocating linear output.
  • the push rod may have a longitudinal axis (212) which extends between its first end (206) and second end (208).
  • a push rod lever (220) may be pivotably coupled to the push rod (150) between the first end (206) and second end (208) of the push rod (150).
  • the push rod lever (220) may be configured to pivotably mount to an anchor point (221) on the compressor (14), such that: the push rod (150) is pivotable about the coupling with the push rod lever (220).
  • the push rod lever (220) may be pivotable about its anchor point coupling to thereby allow the push rod (150) to move in a direction along its longitudinal axis (212) and restrict the push rod (150) from moving in a direction at an angle to its longitudinal axis (212).
  • the push rod lever (220) may be coupled to the push rod (150) at least half of the way, but no more than two thirds of the way, between the first end (206) and second end (208) of push rod (150).
  • the displacement mechanism (210) may comprise a cam plate (226).
  • One of the second end (208) of the push rod (150) and cam plate (226) may define a guide path (230).
  • the other of the second end (208) of the push rod (150) and cam plate (226) may define a guide member (232).
  • the guide member (232) may be configured to engage with the guide path (230) such that the push rod (150) is moveable relative to the cam plate (226) in a lengthwise direction and/or widthwise direction of the cam plate (226), and pivotable relative to the cam plate (226).
  • the guide path (230) may comprise at least one inflexion (240, 242) which, in use, defines a change in direction of travel of the push rod (150) relative to the cam plate (226), and thus defines a change of rotational direction of the guide vane (8a).
  • the guide path (230) may comprise two inflexions (240, 242), the first inflexion (240) defining a change in direction of the push rod (150) relative to the cam plate (226) from a first direction (D1) to a second direction (D2) thus defining a change of rotational direction of the guide vane (8a) from a first rotational direction (R1) to a second rotational direction (R2).
  • the second inflexion (242) may define a change in direction of the push rod (150) relative to the cam plate (226) from the second direction (D2) to the first direction (D1) thus defining a change of rotational direction of the guide vane (8a) from the second rotational direction (R2) to the first rotational direction (R1).
  • a compressor for a gas turbine engine comprising a casing (50) which extends along, and is centred on, an operational axis (20).
  • the compressor may comprise a rotatably mounted variable guide vane (8a) at a first location (202) on the casing (50).
  • the compressor may also comprise a vane lever arm (220) coupled at one end to the variable guide vane (8a), and coupled at its other end to an adjustment ring (140) coaxial with the casing operational axis (20).
  • the compressor may also comprise an adjustment drive (154) mounted to the casing (50) in a second location (204).
  • the compressor may also comprise an adjustment linkage (200a), according to the present disclosure where a first end (206) of the adjustment linkage (200a) is coupled to the adjustment ring (140; and a second end (208) of the adjustment linkage (200a) is coupled to an output of the adjustment drive (154).
  • a compressor (14) for a gas turbine engine comprising a casing (50) which extends along, and is centred on, an operational axis (20).
  • the compressor may comprise a rotatably mounted variable guide vane (8a) at a first location (202) on the casing (50).
  • the compressor may also comprise a vane lever arm (220) coupled at one end to the variable guide vane (8a), and coupled at its other end to an adjustment ring (140) coaxial with the casing operational axis (20).
  • an adjustment drive (154) mounted to the casing (50) in a second location (204).
  • the compressor may also comprise an adjustment linkage (200a) according to the present disclosure wherein a first end (206) of the adjustment linkage (200a) is coupled to the adjustment ring (140) and a second end (232) of the adjustment linkage (200a) is coupled to an output of the adjustment drive (152).
  • variable guide vane may be one of an array of variable guide vanes arranged around the circumference of the casing (50) to form at least part of a first flow stage (46a).
  • a second array (46b) of variable guide vanes (8b) may be arranged around the circumference of the casing (50) to form at least part of a second flow stage (46b) spaced apart from the first flow stage (46a) along the operational axis (20).
  • a vane lever arm (120) may be coupled to, and extend from at least some of the variable guide vanes (8b) of the second flow stage (46b) to a second flow stage adjustment ring (141) coaxial with the casing operational axis (20). There may be provided a second flow stage adjustment linkage (200b).
  • a first end (206b) of the second flow stage adjustment linkage (200a) may be coupled to the adjustment ring (141); and a second end (206b) of the second flow stage adjustment linkage (200a) may be coupled to the output (152) of the adjustment drive (154).
  • the second flow stage adjustment linkage (200a), and the first flow stage adjustment linkage (200a) may be configured such that for a given output of the adjustment drive (154), the vanes (8b) of the second flow stage (46b) will move by a different amount and/or in a different direction to the variable vanes of the first flow stage (46a).
  • variable guide vane may be one of an array of variable guide vanes arranged around the circumference of the casing (50) to form at least part of a first flow stage (46a).
  • a second array of variable guide vanes (8b) may be arranged around the circumference of the casing (50) to form at least part of a second flow stage (8b) spaced apart from the first flow stage (46aa) along the operational axis (20).
  • the compressor may further comprise a second flow stage (46b) adjustment linkage (200b), a first end (206b) of the second flow stage adjustment linkage (200b) coupled to the second array of variable guide vanes (8b); and a second end (208b) of the second flow stage adjustment linkage (200a) is coupled to the output (152) of the adjustment drive (154).
  • the second flow stage adjustment linkage (200b), and the first flow stage adjustment linkage (200a) may be configured such that for a given output of the adjustment drive (154), the vanes (8b) of the second flow stage (46b) will move by a different amount and/or in a different direction to the variable vanes (8a) of the first flow stage (46a).
  • the vanes (8b) of the second flow stage (46b) may be operable to move by a different amount and/or in a different direction to the variable vanes of the first flow stage (46a) at a predetermined flow condition in the compressor (14).
  • the predetermined flow condition may be in the range of 80% to 95% maximum engine speed.
  • a mechanism which combines a cam and a constrained push rod in order to transpose rotating movement driving the cam to longitudinal movement of the push rod, where the displacement mechanism is designed to induce one or several changes of direction of the push rod, and hence induce opening and closing of the variable guide vanes without changing the rotational direction of the cam.
  • the push rod lever is coupled to the casing and push rod so as to allow the push rod to operate substantially only along its longitudinal axis with little or no lateral movement.
  • the cam plate and push rod are coupled so that the angle of the variable vane stage to which they are connected can be varied differently to other variable guide vane stages (where provided) driven by the same actuator. This provides sufficient control to the air flow to avoid stall.
  • the displacement mechanism e.g. cam plate
  • the displacement mechanism may be fixed to a single distributor shaft, driven by a single actuator, which drives multiple stages of variable guide vanes (where provided). This is particularly advantageous as it reduces part count, cost, control complexity and maintenance.
  • the present disclosure relates to an adjustment linkage 200a for a guide vane 8 of a compressor 14 for use in a turbomachine, such as a gas turbine engine 10.
  • a turbomachine such as a gas turbine engine 10.
  • the present disclosure also relates to a compressor for a gas turbine engine comprising the linkage 200a, and a gas turbine engine comprising the compressor.
  • Figure 1 shows a known arrangement to which features of the present disclosure may be applied.
  • FIG. 1 shows an example of a gas turbine engine 10 in a sectional view.
  • the gas turbine engine 10 comprises, in flow series, an inlet 12, a compressor or compressor section 14, a combustor section 16 and a turbine section 18 which are generally arranged in flow series and generally about and in the direction of a rotational axis 20.
  • the rotational axis may also be termed the "operational axis", the direction of flow through the compressor being generally aligned with the operational/rotational axis.
  • the gas turbine engine 10 further comprises a shaft 22 which is rotatable about the rotational axis 20 and which extends longitudinally through the gas turbine engine 10.
  • the shaft 22 drivingly connects the turbine section 18 to the compressor section 14.
  • air 24 which is taken in through the air inlet 12 is compressed by the compressor 14 and delivered to the combustion section or burner section 16.
  • the burner section 16 comprises a burner plenum 26, one or more combustion chambers 28 extending along a longitudinal axis 35 and at least one burner 30 fixed to each combustion chamber 28.
  • the combustion chambers 28 and the burners 30 are located inside the burner plenum 26.
  • the compressed air passing through the compressor 14 enters a diffuser 32 and is discharged from the diffuser 32 into the burner plenum 26 from where a portion of the air enters the burner 30 and is mixed with a gaseous or liquid fuel.
  • the air/fuel mixture is then burned and the combustion gas 34 or working gas from the combustion is channelled through the combustion chamber 28 to the turbine section 18 via a transition duct 17.
  • This exemplary gas turbine engine 10 has a cannular combustor section arrangement 16, which is constituted by an annular array of combustor cans 19 each having the burner 30 and the combustion chamber 28, the transition duct 17 has a generally circular inlet that interfaces with the combustor chamber 28 and an outlet in the form of an annular segment.
  • An annular array of transition duct outlets form an annulus for channelling the combustion gases to the turbine 18.
  • the turbine section 18 comprises a number of blade carrying discs 36 attached to the shaft 22.
  • two discs 36 each carry an annular array of turbine blades 38 are shown.
  • the number of blade carrying discs could be different, i.e. only one disc or more than two discs.
  • guiding vanes 40 which are fixed to a stator 42 of the gas turbine engine 10, are disposed between the stages of annular arrays of turbine blades 38. Between the exit of the combustion chamber 28 and the leading turbine blades 38 inlet guiding vanes 44 are provided and turn the flow of working gas onto the turbine blades 38.
  • the combustion gas 34 from the combustion chamber 28 enters the turbine section 18 and drives the turbine blades 38 which in turn rotate the shaft 22.
  • the guiding vanes 40, 44 serve to optimise the angle of the combustion or working gas 34 on the turbine blades 38.
  • the turbine section 18 drives the compressor 14, i.e. particularly a compressor rotor, via the shaft 22.
  • the compressor 14 comprises an axial series of vane stages 46, or guide vane stages 46, and rotor blade stages 48.
  • the rotor blade stages 48 comprise a rotor disc supporting an annular array of blades.
  • the compressor 14 also comprises a casing 50 that surrounds the rotor blade stages 48 and supports the guide vane stages 46.
  • the casing 50 extends along, and is centred on, the operational axis 20.
  • the guide vane stages 46 include an annular array of radially extending guide vanes 7 that are mounted to the casing 50.
  • the guide vanes 7, hereinafter also referred to as the vanes 7, are provided to present gas flow at an optimal angle for the blades of the rotor blade stage 48 that is present adjacent to and downstream of, with respect to a flow direction of the air 24 along the compressor 14 at a given engine operational point.
  • the casing 50 defines a radially outer surface 52 of the passage 56 of the compressor 14.
  • the guide vane stages 46 and the rotor blade stages 48 are arranged in the passage 56, generally alternately axially.
  • the passage 56 defines a flow path for the air through the compressor 14 and is also referred to as an axial flow path 56 of the compressor 14.
  • the air 24 coming from the inlet 12 flows over and around the guide vane stages 46 and the rotor blade stages 48.
  • a radially inner surface 54 of the passage 56 is at least partly defined by a rotor drum 53 of the rotor which is partly defined by the annular array of blades.
  • Some of the guide vane stages 46 have variable guide vanes 8 (shown as vanes 8a, 8b, 8c, 8d), where the angle of the guide vanes 8, about their own longitudinal axis, can be adjusted for angle according to air flow characteristics that can occur at different engine operations conditions.
  • Some of the other guide vane stages 46 have stationary guide vanes 9 where the angle of the guide vanes 9, about their own longitudinal axis, is fixed and thus not adjustable for angle.
  • the present method and system is described with reference to the above exemplary turbine engine having a single shaft or spool connecting a single, multi-stage compressor and a single, one or more stage turbine.
  • the present system and method is equally applicable to two or three shaft engines and which can be used for industrial, aero or marine applications.
  • the cannular combustor section arrangement 16 is also used for exemplary purposes and it should be appreciated that the present technique is equally applicable to gas turbine engines 10 having annular type and can type combustion chambers.
  • the pitch or the angular offset for the individual stages of variable guide vanes 8a-d inside of the compressor wall 50 is controlled via a linkage mechanism 100 which is applied from the outside of the wall.
  • Each individual vane 8a (first stage 46a), 8b (second stage 46b), 8c (third stage 46c), 8d (fourth stage 46d) is mounted on a spindle 122 to allow angular movement of the vane 8a, 8b.
  • Figure 3 shows an individual vane 8a of the first stage, e.g. the most upstream stage of the compressor and a corresponding lever 120.
  • the lever 120 connects the spindle 122 to a driving ring 140, provided as an adjustment ring, the so called unison ring.
  • a driving ring 140 provided as an adjustment ring, the so called unison ring.
  • Each vane 8 of each stage 46 is connected to its respective unison ring via a lever 120. That is to say, the lever 120 connects the spindle 122 of each vane to a respective driving ring 140, 141, 142, 143.
  • All vanes 8 in a single stage are connected to the same ring so that all vanes 8 on one stage 46 are adjusted at the same time and with the same angle.
  • Each of the driving rings 140, 141, 142, 143 is rotated via a push rod 150, one per ring, from a common adjustment drive shaft 152 which is coupled to (and/or is the output shaft 152 of) a adjustment drive 154.
  • the adjustment drive shaft 152 may be coupled to and be driven by the adjustment drive 154 in any suitable manner.
  • the adjustment drive may comprise only a single actuator (i.e. a drive). Hence a single drive may provide an input to act on all of the push rods 150, unison rings 140-143 and hence guide vanes.
  • the linkage mechanism 100 includes several adjustment linkages 200a, 200b, 200c, 200d for control of vanes 8a (first stage 46a), 8b (second stage 46b), 8c (third stage 46c) and 8d (fourth stage 46d).
  • Figure 5 shows an example of an adjustment linkage 200a, which may be provided on the first stage 46a of the compressor.
  • variable guide vane 8a is rotatably mounted at a first location 202 on the casing 50, the vane lever arm 120 coupled at one end to the variable guide vane 8a.
  • the vane lever arm 120 is coupled at its other end to the adjustment (unison) ring 140 (see Figure 5 ) which is coaxial with the casing operational axis 20.
  • variable guide vane 8a pivotably coupled to the adjustment ring 140 via the lever arm 120.
  • the adjustment drive 154 is mounted to the casing 50 in a second location 204 spaced apart from the first location 202, the adjustment drive operable to actuate the adjustment ring 140 and hence rotate the vane(s) 8a via the adjustment linkage 200a.
  • the adjustment linkage 200a comprises a push rod 150.
  • a first end 206 of the push rod 150 is configured to be pivotably coupled to the adjustment ring 140.
  • a second end 208 of the push rod 150 is configured to be coupled to an output 152 (for example the shaft 152 coupled to the adjustment drive 154) of the adjustment drive 154 via a displacement mechanism 210.
  • the displacement mechanism 210 is configured to vary the directional output of the adjustment drive 154. That is to say the cam mechanism 210 is configured to convert a single direction rotational input from the adjustment drive to a reciprocating linear output.
  • the push rod has a longitudinal axis 212 which extends between its first end 206 and second end 208.
  • a push rod lever (or “member”) 220 is pivotably coupled to the push rod 150 between the first end 206 and second end 208 of the push rod 150.
  • the push rod lever 220 is substantially rigid and/or stiff to, in use, resist forces induced upon it as the push rod 150 is acted upon by the adjustment drive and displacement mechanism 226.
  • the push rod lever 220 is configured to pivotably mount to an anchor point 221 on the compressor 14.
  • the push rod lever 220 is configured to pivotably mount to a third location 222 on the casing 50 to thereby anchor the push rod lever 220 to the casing 50.
  • the third location 222 is spaced apart from the first location 202 and second location 204.
  • the first stage push rod 150 is pivotable about the coupling with the push rod lever 220, and the push rod lever 220 is pivotable about its coupling to the casing 50.
  • This arrangement is operable to allow the push rod 150 to move in directions along its longitudinal axis 212 while at the same time restrict (i.e. inhibit) the push rod 150 from moving in a direction at an angle to its longitudinal axis 212.
  • the directions the push rod 150 may move along its longitudinal axis 212 are shown in Figure 5 by arrows D1, D2.
  • D1, D2 are the only directions the push rod 150 can move by virtue of its constraint to the unison ring 140 and push rod lever 220.
  • the push rod lever 220 may be coupled to the push rod 150 at least half of the way, but no more than two thirds of the way, between the first end 206 and second end 208 of the push rod 150.
  • the displacement mechanism 210 comprises a cam plate 226.
  • the cam plate is engaged with, and hence rotatable by, the adjustment drive 154 (for example via the distributor shaft 152).
  • the adjustment drive 154 drives the drive shaft 152, which thus drives the cam plate 226 around an axis centred on the drive shaft 152.
  • One of the second end 208 of the push rod 150 and cam plate 226 define a guide path 230.
  • the other of the second end 208 of the push rod 150 and cam plate 226 define a guide member 232, the guide member 232 configured to engage with, move along and be constrained by the guide path 230.
  • the cam plate 226 comprises the guide path 230 and the push rod comprises the guide member 232 in form of a pin 232 which extends into, slides along and engages with (i.e. is guided by) the path 230.
  • the guide path 230 and pin 232 are configured such that the push rod 150 is moveable relative to the cam plate 226 in a lengthwise direction (indicated by arrow L1-L2 in Figure 5 ) and/or widthwise direction (indicated by arrow W1-W2 in Figure 5 ) of the cam plate 226, and such that the cam plate 226 is pivotable relative to the push rod 150. That is to say, the guide path allows for the push rod 150 to move relative to the cam plate 266 in a lengthwise L1-L2 direction and/or widthwise direction W1-W2 of the cam plate 226, and allows for the cam plate 226 to pivot relative to the push rod 150.
  • the guide path 230 comprises at least one inflexion 240, 242 which, in use, defines (and causes) a change in direction of travel D1, D2 of push rod 150 relative to the cam plate 226, and thus defines a change of rotational direction R1, R2 of the guide vane 8a.
  • the guide path 230 comprises two inflexions 240, 242.
  • the guide path comprises a first region 250 which extends from a start point 241 to the first inflexion 240.
  • the first region 250 which defines a direction of travel D1 of the push rod 150 relative to the cam plate 226 as shown in Figures 5 , 7a , and direction of rotation R1 of the vane 8, as shown in Figure 4 .
  • the second inflexion 242 is spaced apart from the first inflexion 240 along the guide path 230 by a second region 252.
  • the first inflexion 240 defines a change in direction of the push rod 150 relative to the cam plate 226 from the first direction D1 to the second direction D2 thus defining a change of rotational direction of the guide vane 8a from the first rotational direction R1 to the second rotational direction R2 (as shown in Figure 4 ).
  • the second inflexion 241 defines a change in direction of the push rod 150 relative cam plate 226 from the second direction D2 to the first direction D1, thus defining a change of rotational direction of the guide vane 8a from the second rotational direction R2 to the first rotational direction R2 (as shown in Figure 2 ).
  • a third region 254 extends from the second inflexion to an end point 256, which defines a direction of travel D1, and direction of rotation R1.
  • the first direction D1 is opposite to the second direction D2, and as shown in Figure 4 the first rotational direction R1 is opposite to the second rotational direction R2.
  • variable guide vane 8a may be one of an array of variable guide vanes 8a arranged around the circumference of the casing 50 to form at least part of the first flow stage 46a.
  • More than one of the stages 46a, 46b, 46c, 46d may be provided with an adjustment linkage as described in relation to the first stage 46a.
  • the adjustment linkage 200a of the first stage 46a comprises a push rod 150 joined to a push rod lever 220 and displacement mechanism 210 herein described.
  • the remaining adjustment linkages 200b, 200c, 200d may be of a conventional kind, with push rods 150 coupled to the adjustment drive 154 such that an output from the displacement drive 154 is directly proportional to the direction of movement of the push rods 150 and vanes 8b, 8c, 8d.
  • a first end 206b of a second flow stage adjustment linkage 200b is coupled to the second array 46b of variable guide vanes via the vane lever arm 120 and second flow stage adjustment ring 140 as described above generally and in relation to the first array 8a of variable guide vanes 8a.
  • the second flow stage adjustment linkage 200b has a first end 206b of the second flow stage adjustment linkage 200b coupled to the adjustment ring.
  • a second end 208b (distal to the first end 206b) of the second flow stage adjustment linkage 200a is coupled to the output 152 of the adjustment drive 154.
  • the second flow stage adjustment linkage 200b, and the first flow stage adjustment linkage 200a are configured such that for a given output of the adjustment drive 154, the vanes 8a of the second flow stage 46b will move by a different amount and/or in a different rotational direction (R1, R2) to the variable vanes 8a of the first flow stage 46a.
  • variable guide vanes 8a, 8b do not provide sufficient compression to enable the air flow to pass through the rear (downstream) vane stages 46c, 46d which become “choked”.
  • flow can separate from aerofoil surfaces causing "stall” and flow reversal in all stages of the compressor 14.
  • surge Normally surges will occur repeatedly until the engine is stopped.
  • Figure 6 illustrates the relative movements of the different the first stage 46a to later stages 46b, 46c, 46d in an arrangement according to the present disclosure which has been determined to affect air flows such that stall or other deleterious air flow conditions will be inhibited from occurring by virtue of a the first stage 46a being restricted compared to the other stages at predetermined engine conditions.
  • variable guide vanes 8a, 8b, 8c, 8d are moved by the single actuator 152, with the mechanical linkage 100 enabling successive stages 46a, 46b, 46c, 46d to move by different amounts and in concert with each other.
  • the first stage 46a is operated in concert with the later stages 46b, 46c, 46d.
  • stages 46b, 46c, 46d are in synchronisation with each other, where stage 46a is configured to open and close to a different schedule.
  • the opening/closing of the stages 46b, 46c, 46d is synchronous in that they all open and close at the same time, whereas the opening/closing of the stages 46a is asynchronous relative to the other stages in that the first stage 46a may be opening when the other stages are closing, and may close at a different rate to the other stages.
  • Figure 6 shows a plot of variable guide vane angle plotted against engine speed.
  • the vanes are disposed at a first angle relative to the operational axis 20 (and/or direction of flow through the compressor), and as engine speed increases the vanes are rotated relative to the operational axis 20 such that they are at their most "open" configuration at highest engine speed to allow maximum airflow.
  • the angle of the variable guide vane relative to the operational axis 20 may be considered in terms of the angle a chord line 123 which extends between the vane leading edge and trailing edge makes with the operational axis 20, for example as shown in Figure 4 .
  • vanes 8a of the first stage 46a would follow the same pattern as the later stages, as indicated by the profile marked 8a' in Figure 6 .
  • the pin/guide member 232 is at the starting point 241 of the guide path 230 with the vanes 8a in their most "closed” orientation relative to the operational axis 20 (i.e. moved in the R2 direction to a predetermined extent).
  • the shaft 152 and cam plate 226 rotate the pin 232 is urged along the path 230, and because the push rod 150 is constrained to move only along its longitudinal axis 212, the movement of the pin 232 draws the push rod 150 drawn in the first direction D1 to open the vanes 8a in direction R1, as indicated in the region between points "A" and "B” in Figure 6 .
  • the second flow stage adjustment linkage 200b, and the first flow stage adjustment linkage 200a are configured such that for a given output (e.g. rotation of the shaft 152 between points "B" and "C") of the adjustment drive 154, the vanes 8b of the second flow stage 46b will move by a different amount and/or in a different direction (R1, R2) to the variable vanes 8a of the first flow stage 46a.
  • the second flow stage adjustment linkage 200b and the first flow stage adjustment linkage 200a are configured such that the vanes 8b of the second flow stage 46b will move by a different amount and/or in a different direction to the variable vanes of the first flow stage 46a at a predetermined flow condition in the compressor 14.
  • the predetermined flow condition may be expressed in terms of engine speed. That is to say the displacement mechanism 210 is configured such that point "B" is at a first % of maximum engine speed, and point C is a second % of maximum engine speed.
  • the displacement mechanism 210 may be configured such that point "B" is in the range of 70% to 80% of maximum engine speed, and point C is in the range of 85% to 95% of maximum engine speed.
  • the displacement mechanism 210 may be configured such that point "B" is at 80% of maximum engine speed, and point C is at 90% of maximum engine speed.
  • the displacement mechanism 210 may be configured such that point "B" is at 80% of maximum engine speed, and point C is at 95% of maximum engine speed.
  • variable guide vane stage a "programmed" schedule (i.e. a predetermined movement profile) of operation for a variable guide vane stage to avoid stall and other potentially damaging air flow conditions. It also enables several variable guide vane stages to be operated to different predetermined opening/closing schedules to avoid stall and other potentially damaging airflow conditions.
  • the arrangement of the present disclosure also enables several variable guide vane stages to be controlled using a single actuator/motor/distributor drive 154 and/or common shaft 152, thus avoiding cost and reducing risk associated with using a separator actuator to control one or more stages.
  • Control using a single actuator for all of the guide vanes, and thus driving all of the vanes from a common shaft, also simplifies the overall compressor structure, and obviates the need for reconfiguring/relocating engine components if the arrangement of the present disclosure is fitted retrospectively.
  • push rod lever 220 and displacement mechanism e.g. cam plate 226 with path 30 which guides a pin 232
  • displacement mechanism e.g. cam plate 226 with path 30 which guides a pin 232

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17208561.5A 2017-12-19 2017-12-19 Liaison de réglage Withdrawn EP3502484A1 (fr)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115163565A (zh) * 2022-07-29 2022-10-11 中国航发沈阳发动机研究所 一种航空涡扇发动机中介机匣联动可调放气机构

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Publication number Priority date Publication date Assignee Title
US20060260307A1 (en) * 2005-05-17 2006-11-23 Snecma System for controlling stages of variable-pitch stator vanes in a turbomachine
EP1808579A2 (fr) * 2006-01-17 2007-07-18 General Electric Company Système d'actionnement pour aubes de stator variables
EP2157299A1 (fr) * 2008-07-17 2010-02-24 United Technologies Corporation Ensemble de nacelle à section d'entrée de forme variable pour moteur à turbine à gaz, moteur à turbine à gaz et procédé d'exploitation associés
WO2010031768A2 (fr) * 2008-09-18 2010-03-25 Siemens Aktiengesellschaft Procédé, système et dispositif pour aubes directrices variables
US20100158663A1 (en) * 2008-09-30 2010-06-24 Snecma System for controlling at least two variable-geometry equipments of a gas turbine engine, particularly by cam mechanism
US20110190950A1 (en) * 2008-09-30 2011-08-04 Snecma System for controlling variable geometry equipment of a gas turbine engine especially comprising a guiding track connection

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060260307A1 (en) * 2005-05-17 2006-11-23 Snecma System for controlling stages of variable-pitch stator vanes in a turbomachine
EP1808579A2 (fr) * 2006-01-17 2007-07-18 General Electric Company Système d'actionnement pour aubes de stator variables
EP2157299A1 (fr) * 2008-07-17 2010-02-24 United Technologies Corporation Ensemble de nacelle à section d'entrée de forme variable pour moteur à turbine à gaz, moteur à turbine à gaz et procédé d'exploitation associés
WO2010031768A2 (fr) * 2008-09-18 2010-03-25 Siemens Aktiengesellschaft Procédé, système et dispositif pour aubes directrices variables
US20100158663A1 (en) * 2008-09-30 2010-06-24 Snecma System for controlling at least two variable-geometry equipments of a gas turbine engine, particularly by cam mechanism
US20110190950A1 (en) * 2008-09-30 2011-08-04 Snecma System for controlling variable geometry equipment of a gas turbine engine especially comprising a guiding track connection

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115163565A (zh) * 2022-07-29 2022-10-11 中国航发沈阳发动机研究所 一种航空涡扇发动机中介机匣联动可调放气机构
CN115163565B (zh) * 2022-07-29 2023-08-04 中国航发沈阳发动机研究所 一种航空涡扇发动机中介机匣联动可调放气机构

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