EP2053203B1 - Verbesserung eines Stellrings für die Anstellung von Leitradschaufeln eines Turbotriebwerks - Google Patents

Verbesserung eines Stellrings für die Anstellung von Leitradschaufeln eines Turbotriebwerks Download PDF

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Publication number
EP2053203B1
EP2053203B1 EP08166367.6A EP08166367A EP2053203B1 EP 2053203 B1 EP2053203 B1 EP 2053203B1 EP 08166367 A EP08166367 A EP 08166367A EP 2053203 B1 EP2053203 B1 EP 2053203B1
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EP
European Patent Office
Prior art keywords
ring
turbomachine according
turbomachine
segments
straps
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
EP08166367.6A
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English (en)
French (fr)
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EP2053203A1 (de
Inventor
Michel André Bouru
Jean-Christophe Leininger
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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Publication date
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Publication of EP2053203A1 publication Critical patent/EP2053203A1/de
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Publication of EP2053203B1 publication Critical patent/EP2053203B1/de
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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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • 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
    • 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
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/79—Bearing, support or actuation arrangements therefor

Definitions

  • the invention relates to a turbomachine such as for example a compressor having at least one ring of rectifier blades with variable pitch. It relates more particularly to an improvement in the control ring of the orientation of the variable-pitch blades. The improvement makes it possible at the same time to improve the rigidity and the precision of operation of such a control ring of the positioning of these blades.
  • a turbomachine such as, for example, a high-pressure compressor of an aircraft turbojet, which comprises at least one stage of variable-pitch fixed vanes arranged circumferentially in a housing.
  • the compressor consists of a rotor comprising several stages of rotating blades, axially offset, between which are installed several stages of fixed blades variable pitch.
  • Each stage of fixed blades thus consists of a plurality of blades arranged radially and circumferentially in the casing forming a kind of crown, these blades are fixed but adjustable orientation.
  • the orientation of the blades must be identical for the entire crown of fixed vanes with variable pitch; it can be modified according to the operating conditions.
  • each blade comprises a control pivot projecting radially outside said housing and each pivot is connected by a lever to a common control ring, coaxial with said housing and rotatably mounted outside thereof.
  • the ring is slidably mounted on the outer surface of the casing and is actuated to be able to rotate about its own axis which coincides with that of the turbomachine.
  • the friction may represent up to 30% of the maneuvering force necessary to move the set of blades.
  • the behavior of the ring itself during these displacements can be the source of problems. There is sometimes an ovalization of the ring which is detrimental to the operation.
  • the ring consists of several sections, for example two half-rings, assembled around the housing.
  • FR-2-125,012 describes a control ring consisting of several sections assembled by bridge-shaped elements, to form a complete ring.
  • the bridge-shaped elements are bolted between distant ends of the sections of the ring.
  • the connection between two ring sections and a bridge-shaped element is made by radial bolting.
  • the bridge-shaped elements are relatively flexible and behave somewhat like soft hinges accentuating the deformation of the ring. This can result in a dispersion of blade angles of attack of up to two degrees or more. In the case where the compressor is part of a turboprop, this lack of precision increases the risk of pumping the engine.
  • the invention makes it possible at the same time to simplify and to stiffen the assembly of the sections constituting the control ring.
  • the invention relates to a turbomachine having a fixed blade stage variable pitch, arranged circumferentially in a housing, each blade having a control pivot projecting radially outside said housing and each pivot being connected by an arm a common control ring coaxial with said casing, rotatably mounted outside thereof, characterized in that said ring comprises two sections assembled by side connecting flanges fixed with recess on either side of said sections, to less in the vicinity of the ends thereof.
  • said sections have lateral recesses in which said connecting flanges are embedded.
  • such a connecting flange is a chamfered annular segment for defining frustoconical surfaces while the lateral recesses have a corresponding hollow profile, that is to say also having opposite frustoconical flanks.
  • such a connecting flange is an annular segment comprising a recess in which the end portions of said sections of the ring fit.
  • the sections of the ring may advantageously be chamfered to define four coaxially superposed two-by-two frustoconical surfaces and the aforementioned recess of each flange may comprise two corresponding frustoconical facets cooperating respectively with such two-by-two co-axial superimposed frustoconical surfaces. .
  • the frustoconical surfaces cooperating with the assembly during the tightening of the bolts, facilitate the positioning of the parts relative to each other.
  • the connecting flanges are bolted on either side of the adjacent end portions of said sections at the rate of at least one bolt for each end portion. Generally, two bolts are provided for each end portion.
  • a bolt screw is fitted to the hole of each end portion of the ring section in which it is engaged. If the assembly comprises more than one bolt per end portion of the ring section, the adjustment of a single bolt screw per ring section is generally sufficient to obtain the desired accuracy.
  • the ring comprises at least one actuating yoke or the like by which the actuating force causing its rotation is transmitted thereto.
  • the yoke has a base attached laterally with embedding to the ring, similarly to a lateral flange mentioned above.
  • the base itself forms one of said side flanges.
  • lateral recesses are defined on either side of the ring, considering its axial length, it is possible to proceed by practicing two truncated flank grooves on either side of a complete ring with radial section. rectangular or square, and then cutting the ring into several sections, for example and preferably into two half-rings and reconstituting the ring around the housing by assembling the sections by means of lateral connecting flanges bolted vis-à-vis at the ends of the sections.
  • the aforementioned lateral recesses extend over the entire circumference of the ring thus reconstituted.
  • a compressor 11 comprising, in a casing 13, a fixed blade ring 15 variable setting, adjustable by the rotation of a control ring 17 rotatably mounted outside the housing.
  • the control ring has two cylindrical faces 19, 20 coaxial.
  • the lower face 19 rests on the outer surface of the housing, by means of sliding pads (not visible in the drawings).
  • the center of the ring is located on the axis of rotation of the turbomachine. Only one dawn 15 is visible on the figure 1 .
  • Bores 23 oriented radially are made at regular intervals in the ring and open on its upper face 20 to receive axes 25 of control arm 27 of the blades 15.
  • the blades are arranged circumferentially and radially in the housing 13.
  • Each comprises a control pivot 29 projecting radially outside the housing, through a bore 31 thereof.
  • Each pivot is connected to the control ring by a specific arm 27. All this arrangement is classic.
  • the ring is manufactured in several sections 30a, 30b (at least two half-rings, for example) connected end to end.
  • the sections 30a, 30b of the ring are assembled by connecting flanges 33, 34 lateral fixed with embedding on either side of said sections, at least in the vicinity of the ends thereof.
  • said sections 30a, 30b comprise lateral recesses 35, 36 in which are embedded in said connecting flanges 33, 34.
  • Such a connecting flange is here an annular segment trapezoidal section that is to say having two frustoconical surfaces.
  • the lateral recesses 35, 36 have a corresponding recessed profile, that is to say they comprise two flanks with frustoconical surfaces complementary to those of the connecting flanges.
  • the lateral recesses 35, 36 are made at the ends of the sections 30a, 30b (half-rings) assembled by the connecting flanges described above. It suffices that these recesses have a sufficient length to accommodate the flanges of connection. However, in the embodiment shown, the lateral recesses 35, 36 extend over the entire circumference of the control ring. This results from an advantageous machining process of the ring. According to this method, a complete ring with a rectangular section is available and, by machining the flat annular surfaces (perpendicular to the axis of rotation) of this ring, two grooves with frustoconical sides.
  • the ring is then cut, for example in two equal parts, and holes 40 are made in the end portions of the sections thus formed. Corresponding holes 41 are made in the flanges 33, 34.
  • These sections are reassembled around the casing by means of bolts 44, at the rate of at least one bolt 44 per section, here two bolts 44 per section 30a or 30b, side to side. side.
  • an additional bolt 44a may be provided in the middle of the two flanges 33, 34, opposite the junction between the sections 30a, 30b.
  • connection is particularly rigid and the geometric and dimensional characteristics of the ring are particularly well controlled and stabilized over time.
  • the continuous lateral recesses 35 allow other elements to be connected to the control ring, with the same type of recessed assembly, for example for mounting at least one yoke 47 connected to an actuating jack of the ring.
  • the yoke has a base attached laterally with recess to the ring, in a manner similar to that shown for fixing the side flanges.
  • the base 48 forms one piece with one of the side flanges (the flange 34), as shown.
  • each connecting flange 133, 134 is an annular segment comprising a recess 135, 136 in which the end portions of the segments of the ring 17 are embedded.
  • the sections of the ring are chamfered to define four frustoconical surfaces 139a, 139b-140a, 140b two by two superimposed coaxially while the aforementioned hollow 135, 136 of each flange 133, 134 comprises two frustoconical facets 143a Corresponding 143b cooperating respectively with such two-by-two co-axial superimposed frustoconical surfaces.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (12)

  1. Turbomaschine, umfassend eine Stufe von Leitschaufeln mit veränderlichem Anstellwinkel, die in einem Gehäuse (13) umfangseitig angeordnet ist, wobei jede Schaufel ein außerhalb des Gehäuses radial vorspringendes Betätigungsdrehgelenk (29) umfaßt und jedes Drehgelenk durch einen Arm (27) mit einem gemeinsamen, zu dem Gehäuse koaxialen Verstellring (17) verbunden ist, der außerhalb dessen drehbar angebracht ist, dadurch gekennzeichnet, daß der Ring (17) zwei Abschnitte (30a, 30b) umfaßt, die durch seitliche Verbindungsflansche (33, 34), welche auf beiden Seiten der Abschnitte, wenigstens in der Nähe ihrer Enden, unter Einfügen befestigt sind, verbunden sind.
  2. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, daß die Abschnitte seitliche Einsenkungen (35, 36) umfassen, in die sich die Verbindungsflansche (33, 34) einfügen.
  3. Turbomaschine nach Anspruch 2, dadurch gekennzeichnet, daß ein solcher Verbindungsflansch (33, 34) ein gefastes Ringsegment ist, um kegelstumpfförmige Flächen zu definieren, und daß die seitlichen Einsenkungen (35, 36) ein entsprechendes vertieftes Profil aufweisen.
  4. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, daß ein solcher Verbindungsflansch (133, 134) ein Ringsegment ist, das eine Einsenkung (135, 136) aufweist, in die sich die Endteile der Abschnitte einfügen.
  5. Turbomaschine nach Anspruch 4, dadurch gekennzeichnet, daß die Abschnitte gefast sind, um vier kegelstumpfförmige Flächen (139a, 139b - 140a, 140b) zu definieren, die paarweise koaxial übereinanderliegen, und daß die vorgenannte Einsenkung eines jeden seitlichen Flansches (133, 134) zwei entsprechende kegelstumpfförmige Facetten umfaßt, die jeweils mit derartigen paarweise koaxial übereinanderliegenden kegelstumpfförmigen Flächen zusammenwirken.
  6. Turbomaschine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Verbindungsflansche auf beiden Seiten der benachbarten Endteile der Abschnitte mittels wenigstens eines Bolzens (44) für jeden Endteil verbolzt sind.
  7. Turbomaschine nach Anspruch 6, dadurch gekennzeichnet, daß die Verbindungsflansche mittels zweier Bolzen (44) für jeden Endteil verbolzt sind.
  8. Turbomaschine nach Anspruch 6 oder 7, dadurch gekennzeichnet, daß eine Durchsteckschraube (44) dem Loch (40) eines jeden Endteils des Ringabschnitts angepaßt ist, in das sie gesteckt wird.
  9. Turbomaschine nach einem der Ansprüche 6 bis 8, dadurch gekennzeichnet, daß ein zusätzlicher Bolzen (44a) in der Mitte der beiden Flansche vorgesehen ist.
  10. Turbomaschine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß, da der Ring wenigstens einen Betätigungsbügel (47) oder ähnliches umfaßt, der Bügel einen Sockel (48) aufweist, der - in ähnlicher Weise wie ein vorgenannter seitlicher Flansch - seitlich an dem Ring unter Einfügen befestigt ist.
  11. Turbomaschine nach Anspruch 10, dadurch gekennzeichnet, daß der Sockel (48) mit einem der seitlichen Flansche ein einziges Teil bildet.
  12. Turbomaschine nach einem der Ansprüche 2 bis 11, dadurch gekennzeichnet, daß die seitlichen Einsenkungen (35) sich über den gesamten Umfang des Rings erstrecken.
EP08166367.6A 2007-10-12 2008-10-10 Verbesserung eines Stellrings für die Anstellung von Leitradschaufeln eines Turbotriebwerks Active EP2053203B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0758244A FR2922257B1 (fr) 2007-10-12 2007-10-12 Perfectionnement a un anneau de commande de calage des aubes fixes d'une turbomachine

Publications (2)

Publication Number Publication Date
EP2053203A1 EP2053203A1 (de) 2009-04-29
EP2053203B1 true EP2053203B1 (de) 2013-04-10

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ID=39495764

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08166367.6A Active EP2053203B1 (de) 2007-10-12 2008-10-10 Verbesserung eines Stellrings für die Anstellung von Leitradschaufeln eines Turbotriebwerks

Country Status (6)

Country Link
US (1) US8226357B2 (de)
EP (1) EP2053203B1 (de)
JP (1) JP5420221B2 (de)
CA (1) CA2641017C (de)
FR (1) FR2922257B1 (de)
RU (1) RU2503823C2 (de)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2983924B1 (fr) * 2011-12-09 2013-11-22 Snecma Carter annulaire pour un compresseur de turbomachine
US9404384B2 (en) * 2012-09-12 2016-08-02 United Technologies Corporation Gas turbine engine synchronizing ring with multi-axis joint
US9644491B2 (en) 2014-06-13 2017-05-09 Pratt & Whitney Canada Corp. Single bolting flange arrangement for variable guide vane connection
KR101850237B1 (ko) 2014-07-10 2018-04-18 미츠비시 히타치 파워 시스템즈 가부시키가이샤 가변 정익 장치의 메인터넌스 방법 및 가변 정익 장치
FR3029562B1 (fr) * 2014-12-09 2016-12-09 Snecma Anneau de commande d’un etage d’aubes a calage variable pour une turbomachine
FR3063779B1 (fr) 2017-03-07 2022-11-04 Safran Aircraft Engines Anneau de commande de calage d'un etage d'aube d'un stator
US10526911B2 (en) 2017-06-22 2020-01-07 United Technologies Corporation Split synchronization ring for variable vane assembly
FR3072719B1 (fr) * 2017-10-20 2020-10-09 Safran Aircraft Engines Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine
FR3079870B1 (fr) 2018-04-06 2020-03-20 Safran Aircraft Engines Dispositif de commande d'une rangee annulaire d'aubes a calage variable pour un moteur d'aeronef
BE1026411B1 (fr) * 2018-06-21 2020-01-30 Safran Aero Boosters Sa Virole extérieure de turbomachine
US11346240B2 (en) * 2019-06-07 2022-05-31 Raytheon Technologies Corporation Gas turbine engine bleed valve damping guide link

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US3685920A (en) 1971-02-01 1972-08-22 Gen Electric Actuation ring for variable geometry compressors or gas turbine engines
US3736070A (en) * 1971-06-22 1973-05-29 Curtiss Wright Corp Variable stator blade assembly for axial flow, fluid expansion engine
FR2599785B1 (fr) * 1986-06-04 1990-10-12 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
FR2608678B1 (fr) * 1986-12-17 1991-02-08 Snecma Dispositif de commande d'aubes a calage variable de redresseur de turbomachine
US5503331A (en) * 1994-05-20 1996-04-02 Portec-Rmp Division Insulated rail joint incorporating spacer-impregnated adhesive and method for bonding insulated rail joints
RU2117826C1 (ru) * 1995-03-27 1998-08-20 Акционерное общество открытого типа "А.Люлька-Сатурн" Статор компрессора газотурбинного двигателя
FR2794801B1 (fr) * 1999-06-10 2001-07-06 Snecma Dispositif de protection de mecanisme de commande des volets d'une roue directrice d'entree de turboeacteur
RU17586U1 (ru) * 2000-09-04 2001-04-10 ОАО "Судогодское ремонтно-техническое предприятие" Разъемное стержневое соединение
FR2857404B1 (fr) * 2003-07-10 2007-03-09 Snecma Moteurs Dispositif de guidage en rotation d'aubes a calage variable dans une turbomachine
FR2859762B1 (fr) * 2003-09-11 2006-01-06 Snecma Moteurs Realisation de l'etancheite pour le prelevement cabine par un joint segment
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FR2879686B1 (fr) * 2004-12-16 2007-04-06 Snecma Moteurs Sa Turbomachine a stator comportant un etage d'aubes de redresseur actionnees par une couronne rotative a centrage automatique
US7958735B2 (en) * 2006-12-21 2011-06-14 Power Systems Manufacturing, Llc Turbine static structure for reduced leakage air

Also Published As

Publication number Publication date
FR2922257A1 (fr) 2009-04-17
US20090116954A1 (en) 2009-05-07
US8226357B2 (en) 2012-07-24
RU2503823C2 (ru) 2014-01-10
FR2922257B1 (fr) 2014-03-28
CA2641017A1 (fr) 2009-04-12
CA2641017C (fr) 2015-06-16
JP2009097510A (ja) 2009-05-07
EP2053203A1 (de) 2009-04-29
JP5420221B2 (ja) 2014-02-19
RU2008140325A (ru) 2010-04-20

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