EP3084141B1 - Compresseur de turbomachine, en particulier de turbopropulseur ou de turboréacteur d'avion - Google Patents

Compresseur de turbomachine, en particulier de turbopropulseur ou de turboréacteur d'avion Download PDF

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Publication number
EP3084141B1
EP3084141B1 EP14827799.9A EP14827799A EP3084141B1 EP 3084141 B1 EP3084141 B1 EP 3084141B1 EP 14827799 A EP14827799 A EP 14827799A EP 3084141 B1 EP3084141 B1 EP 3084141B1
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EP
European Patent Office
Prior art keywords
control ring
compressor
hole
oblong hole
cylindrical
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
EP14827799.9A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3084141A1 (fr
Inventor
Pierre-Alain Francis Claude SEBRECHT
Sébastien COCHON
Arnaud Langlois
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
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Publication of EP3084141A1 publication Critical patent/EP3084141A1/fr
Application granted granted Critical
Publication of EP3084141B1 publication Critical patent/EP3084141B1/fr
Active legal-status Critical Current
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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
    • F01D17/10—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
    • 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
    • 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
    • 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
    • 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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • 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
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • 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
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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 invention relates to a turbomachine compressor, in particular a high-pressure turboprop compressor or aircraft turbojet engine.
  • a turbomachine compressor comprises a plurality of compression stages each comprising an annular row of blades mounted on a rotor shaft and an annular row of variable-pitch stator vanes mounted at their radially outer ends on a substantially cylindrical outer casing.
  • the adjustment of the angular setting of the stator vanes in a turbomachine is intended to optimize the efficiency of this turbomachine and to reduce its fuel consumption in the different phases of flight.
  • variable-pitch stator vanes each comprise at their radially outer end a radial pivot which is centered and guided in rotation in an orifice of the outer casing.
  • Each blade pivot is connected by a rod to a control ring which extends around the outer casing of the compressor and which is movable in rotation about the longitudinal axis of the compressor by actuating means for transmitting to the blades a rotational movement around the axes of their pivots.
  • Each link is attached to the blade pivot and has a cylindrical pin engaged in a cylindrical hole of the control ring.
  • control ring During the rotation of the control ring about its axis, it causes the pivoting rods and blades around the axis of the blade pivot.
  • the total angular range of rotation of the links is conventionally of the order of 50 to 90 °.
  • the ring is also axially movable so as to accompany the trajectory of the pieces. All the blades are then in the same angular position, for a given angular position of the control ring.
  • the flow of gas flowing into the vein passing through the high-pressure compressor is not homogeneous over its entire circumference, this flow may include pockets generating performance losses.
  • the turbomachine operates at high speed, significant forces and torques are exerted on the blades, which tends to slightly deform the control ring.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem, while avoiding a system hyperstatement, which requires having rods all having substantially the same length.
  • a turbomachine compressor in particular a turboprop or an airplane turbojet engine, comprising a stator comprising an annular housing and at least one annular row of variable-pitch vanes, each blade having a radially outer end comprising a pivot mounted in a housing orifice and connected by a connecting member to a control ring adapted to pivot axially relative to the housing, the connecting member having a first end attached to the pivot of the blade and a second end comprising a pin engaged in a hole of the control ring, characterized in that at least one of the holes of the control ring, for the engagement of the pins of the connecting members, is of oblong shape and extends in the circumferential direction so as to allow the displacement of the pin in said oblong hole, during the rotation of the control ring.
  • the oblong hole extending in the circumferential direction does not necessarily extend only in the circumferential direction, that is, in a radial plane perpendicular to the axis of the control ring. Indeed, the oblong hole can extend both in the axial direction and in the circumferential direction.
  • the pins are cylindrical.
  • the holes of the control ring for engaging the pins of the connecting members, may be of such shape that it blocks the movement of the pin in said hole.
  • the control ring comprises at least one cylindrical hole, in which is engaged a cylindrical pin of a connecting member, the diameters of the pin and the cylindrical hole being substantially identical, and at least one oblong hole. extending circumferentially, in which is engaged another cylindrical pin of another connecting member.
  • said oblong hole of the control ring has a first end located on the side of a first lateral edge of the control ring, a second end located on the side of a second lateral edge of the control ring, the two ends being connected by a curved connection zone having a point of inflection.
  • said oblong hole of the control ring extends only in the circumferential direction.
  • said oblong hole of the control ring extends obliquely with respect to the axial direction and with respect to the circumferential direction.
  • said oblong hole of the control ring has an arcuate shape.
  • said oblong hole of the control ring has a first end extending only circumferentially and located on the side of a lateral edge of the control ring, a second end s' extending only circumferentially and being located on the side of the other lateral edge of the control ring, said ends being connected by a connecting zone extending obliquely with respect to the circumferential direction and with respect to the axial direction.
  • the invention further relates to a turbomachine, such as for example a turboprop or an airplane turbojet, comprising at least one compressor of the aforementioned type.
  • a turbomachine such as for example a turboprop or an airplane turbojet, comprising at least one compressor of the aforementioned type.
  • FIG 1 represents a schematic half-view of the upstream portion of a high-pressure compressor 10 according to the prior art, in section along a plane passing through the axis of rotation 12 of the turbomachine.
  • the high-pressure compressor 10 comprises a rotor formed of disks 14, 16, 18, 20 assembled axially with each other, the rotor being supported on a bearing 22 by means of a pin 24.
  • Each disk is arranged downstream of an annular row of stator vanes 26 with variable pitch.
  • Each stator vane comprises at its radially inner and outer ends coaxial cylindrical pivots 28, 30.
  • the internal cylindrical pivot 28 extends inwardly from the stator vane 26 and is centered and guided in rotation in a cylindrical housing of an annular element of the stator, and the external cylindrical pivot 30 extends radially towards the outside. outside and is centered and guided in rotation in a cylindrical chimney 32 of a substantially cylindrical outer casing 34 of the high-pressure compressor 10.
  • the adjustment of the angular setting of the stator vanes 26 of a stage is ensured by means of rods 36 which are rotated by a control ring 38 pivotally mounted relative to the casing 34 about the axis 12.
  • the deflection total of the control ring is for example between 5 and 20 °.
  • a hydraulic cylinder 40 allows the simultaneous displacement in rotation of several control rings 38.
  • the ring 38 is for example formed of two parts 39 assembled to each other by means of bridges (not shown) attached to the ends said parts 39.
  • the links 36 are fixed at one end to the radial pivots 30 of the variable-pitch vanes 26, these pivots 30 being guided in rotation in bushes 42 mounted in the chimneys 32 of the casing 34 (FIG. figure 2 ).
  • the end of the rod attached to the blade pivot 30 is held radially on a rim 44 of the sleeve 42 by a nut 46 screwed onto the end of the pivot 30.
  • the other end of the rod 36 comprises an orifice in which is guided in rotation a radial cylindrical pin 48 mounted in a cylindrical hole 52 of the control ring 38.
  • the pins 48 are held in position by bent tabs 50 fixed to the control ring 38.
  • the control ring 38 is also axially displaceable in translation, so as to accompany the circular trajectory of the pins 48.
  • the portions 39 of the control ring 38 comprise other holes 54, 56 serving respectively for fixing the connecting members for connecting the ends of the two parts 39 of the control member 38 between them or used for the fixing centering pads coming to apply on a track formed on the outer surface of the casing.
  • control ring 38 During the rotation of the control ring 38 about its axis 12, it causes the pivoting rods 36 and vanes 26 to pivot about the axis of the pivots 28, 30 of the blades 26. All the blades 26 are located then in the same angular position, for a given angular position of the control ring 38, the rods 36 all having the same length.
  • the invention responds to this need by providing a control ring 38 for adapting the angular setting of the blades 26 individually or by group of blades 26, depending on the azimuthal positions of the blades 26 concerned or groups of blades 24 concerned.
  • FIGS. 5 and 6 illustrate a first embodiment of the invention in which part of the holes in which the cylindrical pins 48 are engaged have an oblong shape (holes 58), another part of said holes being cylindrical (holes 52) and of diameter substantially identical to that of the corresponding pawns 48.
  • the oblong holes 58 each comprise a first end 60 located on the side of a first lateral edge or upstream edge 62 of the control ring 38, a second end 64 located on the side of a second side edge or downstream edge 66 of the control ring 38, the two ends 60, 64 being connected by a curved connection zone 68 having a point of inflection.
  • the wedging angle of the blades 26 does not vary in the same way, as a function of the angular position of the control ring 38, for the blades 26 associated with the cylindrical holes 52 or for the blades 26 associated with them. to the oblong holes 58.
  • control ring 38 thus has two groups of blades 26, located in azimuthal zones different from the turbomachine, and according to different timing laws from one group to another.
  • center of the holes 52 is aligned circumferentially with one of the ends of the oblong holes 58.
  • the figure 7 illustrates a second embodiment of the invention wherein each elongate hole 58 of the control ring 38 extends only in the circumferential direction.
  • each oblong hole 58 of the control ring 38 extends obliquely with respect to the axial direction A and with respect to the circumferential direction C. More particularly, each hole oblong 58 extends rectilinearly, from upstream to downstream (i.e. from left to right at figure 8 ), in a first direction of rotation of the control ring indicated by the arrow S1, which is an opening direction of the blades 26.
  • each oblong hole 58 of the control ring 38 has a shape in an arc of circle or approaching an arc of a circle, plus especially in a quarter circle.
  • One end 70 of each oblong hole 58 is directed axially upstream, the other end 72 being directed circumferentially in a direction S2 opposite to the aforesaid direction S1, the direction S2 being a closing direction of the blades 26.
  • the figure 10 illustrates the blade registration law for blades 26 associated respectively with a cylindrical hole 52 (curve C1), with an oblong hole 58 of the figure 7 (curve C2), to an oblong hole 58 of the figure 8 (curve C3) and an oblong hole 58 of the figure 9 (curve C4).
  • the calibration laws are the curves representative of the evolution of the angular position of the blade 26 ( ⁇ aube) as a function of the angular position of the control ring 38 ( ⁇ anneau).
  • the angle ⁇ aube corresponds to the angle of the rods 36 with respect to the axis 12 of the turbomachine, by defining a straight line which passes through the center of the pivot 30 of the blade 26 and the center of the pin 48 which is inserted in the ring 38.
  • the open position corresponds to a negative angle ⁇ aube relative to the axis 12 of the turbomachine, considering that the positive direction is the trigonometric direction, and the closed position corresponds to an angle ⁇ aube positive with respect to the axis 12 of the turbomachine.
  • the angle ⁇ aube 0 corresponds to the position where the rods 36 are aligned with the axis 12 of the turbomachine.
  • the figure 11 illustrates a fifth embodiment of the invention in which each oblong hole 58 of the control ring 38 has a shape symmetrical to the shape of the oblong holes 58 of the figure 6 , with respect to a radial plane passing through the axially central zone of the control ring 38.
  • each oblong hole 58 of the control ring 38 has a first end 74 extending only circumferentially and located on the side of the upstream edge 62 of the control ring, a second end 76 extending only circumferentially and located on the side of the downstream edge 66 of the control ring 38, said ends 74, 76 being connected by a connecting zone 78 extending obliquely with respect to the circumferential direction C and with respect to the axial direction A.
  • the figure 13 illustrates a seventh embodiment of the invention in which each oblong hole 58 of the control ring 38 has a shape symmetrical to the shape of the oblong holes 58 of the figure 8 , with respect to a radial plane passing through the axially central zone of the control ring 38.
  • control ring 38 may comprise at least two types of oblong hole 58 among those described above.
  • Other forms of oblong holes 58 may also be used, provided that these oblong holes 58 extend in particular in the circumferential direction C.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP14827799.9A 2013-12-19 2014-12-04 Compresseur de turbomachine, en particulier de turbopropulseur ou de turboréacteur d'avion Active EP3084141B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1362972A FR3015594B1 (fr) 2013-12-19 2013-12-19 Compresseur de turbomachine, en particulier de turbopropulseur ou de turboreacteur d'avion
PCT/FR2014/053163 WO2015092197A1 (fr) 2013-12-19 2014-12-04 Compresseur de turbomachine, en particulier de turbopropulseur ou de turboréacteur d'avion

Publications (2)

Publication Number Publication Date
EP3084141A1 EP3084141A1 (fr) 2016-10-26
EP3084141B1 true EP3084141B1 (fr) 2018-02-07

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP14827799.9A Active EP3084141B1 (fr) 2013-12-19 2014-12-04 Compresseur de turbomachine, en particulier de turbopropulseur ou de turboréacteur d'avion

Country Status (9)

Country Link
US (1) US10590794B2 (enExample)
EP (1) EP3084141B1 (enExample)
JP (1) JP6419831B2 (enExample)
CN (1) CN105874171B (enExample)
BR (1) BR112016013833B1 (enExample)
CA (1) CA2932998C (enExample)
FR (1) FR3015594B1 (enExample)
RU (1) RU2670473C1 (enExample)
WO (1) WO2015092197A1 (enExample)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9835037B2 (en) * 2015-06-22 2017-12-05 General Electric Company Ducted thrust producing system with asynchronous fan blade pitching
FR3041714B1 (fr) 2015-09-30 2020-02-14 Safran Aircraft Engines Compresseur de turbomachine, en particulier de turbopropulseur ou de turboreacteur d'avion
GB201717091D0 (en) * 2017-10-18 2017-11-29 Rolls Royce Plc A variable vane actuation arrangement
FR3100272B1 (fr) * 2019-08-27 2025-04-25 Safran Aircraft Engines Guignol pour un dispositif de calage variable d’une turbomachine
CN112360816A (zh) * 2020-12-08 2021-02-12 成都成发科能动力工程有限公司 一种轴流压缩机承缸和应用其的轴流压缩机
US12510004B2 (en) * 2024-06-14 2025-12-30 General Electric Company Outward facing load reacting bodies for use with unison rings

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US3066488A (en) * 1959-11-04 1962-12-04 Bendix Corp Power output control for a gas turbine engine
US3314595A (en) * 1965-06-09 1967-04-18 Gen Electric Adjustment mechanism for axial flow compressors
FR1592922A (enExample) * 1968-11-21 1970-05-19
US3861822A (en) * 1974-02-27 1975-01-21 Gen Electric Duct with vanes having selectively variable pitch
US4737071A (en) * 1985-04-22 1988-04-12 Williams International Corporation Variable geometry centrifugal compressor diffuser
US5993152A (en) * 1997-10-14 1999-11-30 General Electric Company Nonlinear vane actuation
GB2402180B (en) * 2003-05-30 2006-09-20 Rolls Royce Plc Variable stator vane actuating levers
FR2857404B1 (fr) * 2003-07-10 2007-03-09 Snecma Moteurs Dispositif de guidage en rotation d'aubes a calage variable dans une turbomachine
FR2879687B1 (fr) * 2004-12-16 2007-04-20 Snecma Moteurs Sa Turbomachine a stator comportant un etage d'aubes de redresseur actionnees par une couronne rotative deplacee par des moyens moteurs electriques
FR2882570B1 (fr) * 2005-02-25 2007-04-13 Snecma Moteurs Sa Dipositif de commande d'aubes a calage variable dans une turbomachine
FR2890136B1 (fr) * 2005-08-30 2007-11-09 Snecma Bielle a longueur evolutive en fonctionnement
US7413401B2 (en) * 2006-01-17 2008-08-19 General Electric Company Methods and apparatus for controlling variable stator vanes
US8297918B2 (en) * 2009-01-06 2012-10-30 General Electric Company Variable position guide vane actuation system and method
US20110176913A1 (en) * 2010-01-19 2011-07-21 Stephen Paul Wassynger Non-linear asymmetric variable guide vane schedule

Also Published As

Publication number Publication date
CA2932998C (fr) 2022-04-19
WO2015092197A1 (fr) 2015-06-25
FR3015594B1 (fr) 2018-04-06
BR112016013833B1 (pt) 2022-02-08
US10590794B2 (en) 2020-03-17
BR112016013833A2 (enExample) 2017-08-08
CN105874171B (zh) 2018-06-12
JP6419831B2 (ja) 2018-11-07
RU2016123656A (ru) 2018-01-24
RU2670473C1 (ru) 2018-10-23
CN105874171A (zh) 2016-08-17
US20160348530A1 (en) 2016-12-01
FR3015594A1 (fr) 2015-06-26
EP3084141A1 (fr) 2016-10-26
CA2932998A1 (fr) 2015-06-25
JP2017501334A (ja) 2017-01-12

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