EP0636766A1 - Turbomaschinenstator mit verstellbaren Leitschaufeln und deren Bedienungsring - Google Patents

Turbomaschinenstator mit verstellbaren Leitschaufeln und deren Bedienungsring Download PDF

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Publication number
EP0636766A1
EP0636766A1 EP94401719A EP94401719A EP0636766A1 EP 0636766 A1 EP0636766 A1 EP 0636766A1 EP 94401719 A EP94401719 A EP 94401719A EP 94401719 A EP94401719 A EP 94401719A EP 0636766 A1 EP0636766 A1 EP 0636766A1
Authority
EP
European Patent Office
Prior art keywords
casing
rings
control
vanes
control ring
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.)
Granted
Application number
EP94401719A
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English (en)
French (fr)
Other versions
EP0636766B1 (de
Inventor
Jean-Louis Charbonnel
Philippe Guerout
Jacques Lucien Happey
Frédéric Mainfroy
Jacky Naudet
Jean-Claude Porcher
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA 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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0636766A1 publication Critical patent/EP0636766A1/de
Application granted granted Critical
Publication of EP0636766B1 publication Critical patent/EP0636766B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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

Definitions

  • the invention relates to a turbomachine stator with pivoting vanes and a control ring.
  • turbomachines include, in particular for the high pressure stages of the compressors, stator vanes which are not fixed but pivoting in order to modify the characteristics of the rectification of the gases which pass through the vein in which these vanes extend.
  • Such vanes called variable pitch, therefore include pivots which extend through an envelope which delimits the flow stream and out of it, and these pivots are connected to rods which are normally joined together by a control ring disposed around the stream and that a control mechanism moves in translation along the axis of the turbomachine or in rotation about this axis. In both cases, the links rotate and drive the pivots of the blades.
  • a disadvantage of this system is due to the thrust of the gases which produces significant forces on the blades. These forces are transmitted to the pivots and to the bearings of the envelope which support them. They are in the preferred direction. The friction exerted by the pivots when they rotate is responsible for concentrated wear of the bearings which results in an ovalization of their shape. The vein then enters into communication with other volumes of the turbomachine, the efficiency of which drops due to gas leaks which appear. These drawbacks are even more marked if the compression ratio sought for the gases is high, because the thrust is greater and faster wear. These circumstances explain that, in the currently known embodiments, the envelope which carries the bearings of the pivots and which delimits the vein has great rigidity and is constructed of steel, which makes it very heavy. The classically sought-after substitution of titanium for steel to lighten the structure is not possible here because of the temperature of the gases in the vein and of the resulting fire risks of titanium.
  • the essential object of the invention is to dissociate the envelope, bearing pivot bearings of pivoting vanes and undergoing the forces due to the pressure of the gases, from the casing, which undergoes the structural forces, without compromising the seal between pivots and bearings.
  • the fundamental advantage obtained is that the envelope can now be constructed of composite material and therefore significantly lightened.
  • the solution adopted for this consists, briefly explained, of supporting the forces of the gases by a bearing constructed on a casing separate from the envelope and which is occupied by a rotary axis belonging to the control mechanism. The forces undergone by the blades are therefore transmitted by the pivots, the rods, the control ring and a part of the control mechanism up to the axis in question, then are diffused in the casing of the machine which is perfectly capable to undergo them.
  • the envelope is advantageously formed of rings juxtaposed axially by assembly means allowing relative axial displacements of the rings, each of these rings being preferably associated with a single stage of pivoting vanes; it is even better that the crowns are made up of angular sectors separated by clearances that seal off the joints. All these arrangements for dividing the envelope, the elements of which are above all retained by a few places of attachment to the casing, make it possible to greatly reduce the stresses therein and in particular those which result from thermal expansions. It is then that it becomes really easy to construct the envelope of composite material of relatively low resistance to forces.
  • FIG. 1 represents a portion of a turbomachine and more specifically a compressor essentially constituted by a portion of rotor 1 flaring downstream, a casing 2 made of titanium and cylindrical and an envelope 3 made of composite material and supported by the casing 2, which surrounds it and constitutes with it the framework of a stator whose other elements will soon be described.
  • the rotor 1 and the casing 3 delimit a flow vein 4 occupied by several stages of movable blades 5 fixed to the rotor 1 and by several stages of stator blades which alternate with the preceding ones and the first of which (towards the upstream) are composed of fixed vanes 6 and the last two (downstream) of pivoting vanes 7.
  • the casing 2 is cylindrical to facilitate its manufacture
  • the casing 3 is conical and of reduced diameter towards the downstream where it is therefore increasingly spaced from the casing 2. It follows from this arrangement that the fixed blades 6 are held by fixed pins 8 engaged in support rings 9 rigidly connected to the casing 2 or in one piece with it , but that the pivoting vanes 7 have rotary axes or pivots 10 movable in rotation in bearing bearings 11 situated through thickened regions 12 of the casing 3.
  • the pivots 10 protrude outside these thickened zones 12 and are joined to this place has links 13 respective by a screwing, a snap-fastening or another known system ensuring a rigid connection in rotation, and the connecting rods 13 of each stage of pivoting vanes 7 are articulated by their opposite end to a common control ring 14 and more precisely to axes 27 of this ring, axes clearly visible in Figure 2 and which therefore allow full transmission of linear forces.
  • the control rings 14 extend over an entire circumference in FIG.
  • a control mechanism 15 composed of a lever 16 of substantially axial extension (see also Figure 3) and one end 17 of which is pivotally mounted on an arm 19 outside the casing 2 and the opposite end 18 of which is fixed to a radial axis 20 of which it controls the pivoting.
  • the axis 20 is terminated by a lever 21 whose displacement causes that of the control ring 14, to which it is united according to the arrangements which will be detailed later.
  • the arm 19 rotates with an output shaft of a motor 29 around an axis of axial rotation.
  • the motor 29 is linked to a support structure 22.
  • the support structure 22 is composed of at least one clamping segment 23 bolted to a ring 24 of the casing 2, or of several of these segments joined by an axial spacer.
  • the situation is slightly different in FIG. 2 where we find in particular the radial axis 20, but where this axis is single as well as the jack 16 and the support 22 and where the lever 21 is replaced by a double lever 121 connected to the two control rings, referenced here by 114, by its two opposite ends: unlike the previous embodiment, the axis 20 is connected to the center of the double lever 121.
  • control rings 114 There is no or practically no difference in structure between the control rings 114 and those above, but their arrangement is a little different because they are brought together so that they can be controlled by the double lever 121 and located between the two stages of pivoting vanes 7.
  • the rods 113 of the two stages instead of being oriented substantially parallel as in the previous embodiment, are therefore oriented in opposite directions.
  • the control mechanism is then generally designated by 115, and the rest of the preceding description remains valid.
  • Another solution consists in providing two diametrically opposite control mechanisms 115, as in FIG. 1, each of which controls half of the control rings 114, which would have the advantage of dividing the force produced on the axis 20 and of make it symmetrical on the casing 2.
  • the control mechanism 15 or 115 between the axis 20 and the control rings 14 or 114 is generally too bulky to fit in the space between the cylindrical casing 2 and the casing 3, and it this is why the casing 2 is hollowed out at this location and provided with a removable boss projecting outwards in the shape of a bell 28, bell clamped by a flat outer rim 29 to a crown 30 of the casing 2 by bolts 31 and the center is provided with an opening carrying a bearing constituting a bearing 32 for the axis 20.
  • the control lever 21 or 121 extends under the bell 28.
  • sealing rings 60 in the form of rings are arranged around the bases. 61 of the pivoting vanes 7 and housed in counterbores 62 of the casing 3 which contain these counterbores 62.
  • the sealing segments 60 are made of composite material such as Avimide and are approximately one millimeter thick. Their function is to prevent impurities contained in the gases of the flow stream 4 from sliding up to the bearings 11, which are made of relatively soft material with a low coefficient of friction, and do not deteriorate them. The performance of the machine is therefore saved.
  • a similar arrangement is possible with other types of mounting of the pivoting vanes 7 on the casing 3.
  • FIG. 4 Reference is now also made to FIG. 4 and to FIGS. 5A and 5B to continue the description of the embodiment of FIG. 2, but this description could be transposed to the embodiment of FIG. 1.
  • the control rings 114 are provided with a spar 33 from which a console 34 protrudes and which carries a rod 35 oriented in the radial direction, that is to say parallel to the axis 20.
  • An externally spherical bush 36 shown in the figures 2 and 5 is engaged around the rod 35. It constitutes a ball joint with a crown 38 which can tilt on it and therefore has a spherical internal edge and a cylindrical external edge.
  • the rod 35 is composed of an exposed portion 35a which comes out of the console 34 and which receives the bush 36 and of a root portion 35b engaged in a drilling of the console 34.
  • the two portions of the rod 35 are cylindrical but their axes are not confused: the rod 35 forms an eccentric thanks to which the console 34, the side member 33, and the control ring 14 can be moved somewhat to finely adjust the setting of the pivoting vanes 7 without moving the double lever 121 This operation is made during periodic machine maintenance adjustments.
  • the visible portion 35a is therefore provided with opposite flats 39 (FIG. 4) which can be grasped by a key to turn the rod 35.
  • a bolt 50 which passes entirely through the rod 35 is mounted to block it rotating against the console 34 while retaining the socket 36 by a washer or a screw head.
  • the double lever 121 is provided with two elongated slots 37 in each of which one of the rings 38 slides.
  • FIGS. 5A and 5B represent two states corresponding to the two extreme strokes of the double lever 121 for which the crowns 38 arrive at the respective ends of the elongated slots 37. These positions correspond to the extreme stallings allowed for the pivoting vanes 7, whose angular movement is similar to that of the rods 13.
  • the casing 3 is made up of ferrules and terminated by tenon 40 and mortise 41 systems which make it possible to join the crowns to one another by juxtaposing them in the axial direction.
  • Each ring is associated with a stage of stator vanes and therefore comprises a thickened region 12 in which the axes 8 or the pivots 10 pass.
  • these thickened regions 12 sometimes widen to form tapped bosses 42 in which bolts 43 are clearly visible in FIG. 1 which join the crowns to the casing 2.
  • the bosses 42 can moreover be replaced by structures equivalents such as ribs with clamping flange 44 for some of the blade stages.
  • the crowns of the envelope 3 are advantageously divided into sectors each extending over a portion of the circumference and which are therefore terminated by transverse edges 45 separated by games 46.
  • This arrangement which is beneficial for relieving the envelope 3 of differential stresses thermal expansion, involves re-establishing the tightness at these places thanks to lamellar seals 47, conventionally used in this technical field, which cover the clearances 46 by spanning over consecutive sectors of crowns and penetrating into slots 48 leading to the transverse edges 45.
  • Other seals which may consist of wavy leaf springs that the pins 40 compress at the bottom of the mortises 41, make it possible to complete the seal. These other seals are however optional and have therefore not been illustrated, especially since they are well known.
  • the invention makes it possible to eliminate all of a sudden all the leaks due to the widening of tens or hundreds of bearings 11.
  • the wear is concentrated on the bearings 32, which are few in number on the turbomachine and which do not open out in the flow stream 4, so that their wear is not responsible for leaks. If however the replacement of a bearing 32 is decided, it is quickly carried out thanks to their small number and their presence on the casing 2, in an external location of the turbomachine more accessible than the casing 3.
  • the residual forces on the bearings 11 of the pivots 10 are compensated by small displacements of the crown sectors which have the freedom to play axially and angularly thanks to the tenon systems and mortise 40 and 41 and games 46, without leaks or stresses being produced.
  • the bearings 11 are therefore not loaded.
  • the direction of the levers 21 and 121 is chosen so that the thrust received by the pivoting vanes 7 is effectively transmitted by the crowns 36 to said levers, that is to say is substantially perpendicular to the axis of the elongated lights 37 .
  • control mechanisms 15 or 115 which are located outside the bells 28 can take very different forms from that which has been illustrated and are in reality independent of the invention itself.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP94401719A 1993-07-28 1994-07-27 Turbomaschinenstator mit verstellbaren Leitschaufeln und deren Bedienungsring Expired - Lifetime EP0636766B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9309266 1993-07-28
FR9309266A FR2708311B1 (fr) 1993-07-28 1993-07-28 Stator de turbomachine à aubes pivotantes et anneau de commande.

Publications (2)

Publication Number Publication Date
EP0636766A1 true EP0636766A1 (de) 1995-02-01
EP0636766B1 EP0636766B1 (de) 1997-09-03

Family

ID=9449698

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94401719A Expired - Lifetime EP0636766B1 (de) 1993-07-28 1994-07-27 Turbomaschinenstator mit verstellbaren Leitschaufeln und deren Bedienungsring

Country Status (4)

Country Link
US (1) US5466122A (de)
EP (1) EP0636766B1 (de)
DE (1) DE69405334T2 (de)
FR (1) FR2708311B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2362071A1 (de) * 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Antriebsvorrichtung zum Schwenken von verstellbaren Schaufeln einer Turbomaschine
WO2019243484A1 (fr) * 2018-06-21 2019-12-26 Safran Aero Boosters Sa Virole extérieure de turbomachine

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2723614B1 (fr) * 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
US5593275A (en) * 1995-08-01 1997-01-14 General Electric Company Variable stator vane mounting and vane actuation system for an axial flow compressor of a gas turbine engine
FR2739137B1 (fr) * 1995-09-27 1997-10-31 Snecma Dispositif de commande d'un etage d'aubes a calage variable
US6174129B1 (en) 1999-01-07 2001-01-16 Siemens Westinghouse Power Corporation Turbine vane clocking mechanism and method of assembling a turbine having such a mechanism
US6283705B1 (en) * 1999-02-26 2001-09-04 Allison Advanced Development Company Variable vane with winglet
ITTO20010444A1 (it) * 2001-05-11 2002-11-11 Fiatavio Spa Turbina assiale per applicazioni aeronautiche.
FR2882394B1 (fr) 2005-02-22 2007-05-18 Snecma Moteurs Sa Dispositif de variation de la section de col d'un distributeur de turbine
GB0504588D0 (en) * 2005-03-05 2005-04-13 Rolls Royce Plc Pivot ring
EP2165047A1 (de) * 2007-04-10 2010-03-24 Elliott Company Radialverdichter mit einstellbaren eintrittsleitschaufeln
US8851832B2 (en) * 2009-12-31 2014-10-07 Rolls-Royce North American Technologies, Inc. Engine and vane actuation system for turbine engine
US8790067B2 (en) 2011-04-27 2014-07-29 United Technologies Corporation Blade clearance control using high-CTE and low-CTE ring members
US8739547B2 (en) 2011-06-23 2014-06-03 United Technologies Corporation Gas turbine engine joint having a metallic member, a CMC member, and a ceramic key
US8864492B2 (en) 2011-06-23 2014-10-21 United Technologies Corporation Reverse flow combustor duct attachment
US8511975B2 (en) 2011-07-05 2013-08-20 United Technologies Corporation Gas turbine shroud arrangement
US9335051B2 (en) 2011-07-13 2016-05-10 United Technologies Corporation Ceramic matrix composite combustor vane ring assembly
US8920127B2 (en) 2011-07-18 2014-12-30 United Technologies Corporation Turbine rotor non-metallic blade attachment
US10563670B2 (en) * 2016-07-29 2020-02-18 Rolls-Royce Corporation Vane actuation system for a gas turbine engine
GB201614803D0 (en) 2016-09-01 2016-10-19 Rolls Royce Plc Variable stator vane rigging
US10502091B2 (en) 2016-12-12 2019-12-10 United Technologies Corporation Sync ring assembly and associated clevis including a rib
JP7199248B2 (ja) * 2019-02-22 2023-01-05 三菱重工業株式会社 車室、及び蒸気タービン

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BE623280A (de) *
US2862687A (en) * 1953-10-09 1958-12-02 Sulzer Ag Axial flow turbomachine
DE1136350B (de) * 1959-08-11 1962-09-13 Entwicklungsbau Pirna Veb Verstellvorrichtung fuer Leitschaufelkraenze einer Axial-Stroemungsmaschine
GB1466613A (en) * 1973-09-07 1977-03-09 Nissan Motor Guide vane control for an automobile gas turbine engine
GB1505858A (en) * 1976-12-08 1978-03-30 Secr Defence Axial flow rotary machines
FR2583820A1 (fr) * 1985-06-20 1986-12-26 Snecma Dispositif de variation de section de passage d'un distributeur de turbine
US4755104A (en) * 1986-04-29 1988-07-05 United Technologies Corporation Stator vane linkage
GB2254381A (en) * 1991-01-25 1992-10-07 Mtu Muenchen Gmbh Device for adjusting turbine guide vanes.
US5158430A (en) * 1990-09-12 1992-10-27 United Technologies Corporation Segmented stator vane seal

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US3632224A (en) * 1970-03-02 1972-01-04 Gen Electric Adjustable-blade turbine
US4214852A (en) * 1978-04-20 1980-07-29 General Electric Company Variable turbine vane assembly
JPS597708A (ja) * 1982-07-07 1984-01-14 Hitachi Ltd 軸流機械における静翼取付角可変装置
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DE3407946A1 (de) * 1984-03-03 1985-09-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur verhinderung der ausbreitung von titanfeuer bei turbomaschinen, insbesondere gasturbinen- bzw. gasturbinenstrahltriebwerken
FR2681640B1 (fr) * 1991-09-25 1993-11-19 Snecma Turbomachine a aubes de stator a calage variable.
FR2691749B1 (fr) * 1992-05-27 1994-07-22 Snecma Dispositif d'etancheite entre des etages d'aubes et un tambour tournant notamment pour eviter les fuites autour des etages d'aubes de redresseur .
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE623280A (de) *
US2862687A (en) * 1953-10-09 1958-12-02 Sulzer Ag Axial flow turbomachine
DE1136350B (de) * 1959-08-11 1962-09-13 Entwicklungsbau Pirna Veb Verstellvorrichtung fuer Leitschaufelkraenze einer Axial-Stroemungsmaschine
GB1466613A (en) * 1973-09-07 1977-03-09 Nissan Motor Guide vane control for an automobile gas turbine engine
GB1505858A (en) * 1976-12-08 1978-03-30 Secr Defence Axial flow rotary machines
FR2583820A1 (fr) * 1985-06-20 1986-12-26 Snecma Dispositif de variation de section de passage d'un distributeur de turbine
US4755104A (en) * 1986-04-29 1988-07-05 United Technologies Corporation Stator vane linkage
US5158430A (en) * 1990-09-12 1992-10-27 United Technologies Corporation Segmented stator vane seal
GB2254381A (en) * 1991-01-25 1992-10-07 Mtu Muenchen Gmbh Device for adjusting turbine guide vanes.

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2362071A1 (de) * 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Antriebsvorrichtung zum Schwenken von verstellbaren Schaufeln einer Turbomaschine
WO2019243484A1 (fr) * 2018-06-21 2019-12-26 Safran Aero Boosters Sa Virole extérieure de turbomachine
BE1026411B1 (fr) * 2018-06-21 2020-01-30 Safran Aero Boosters Sa Virole extérieure de turbomachine
US11236634B2 (en) 2018-06-21 2022-02-01 Safran Aero Boosters Sa Turbine engine outer shroud

Also Published As

Publication number Publication date
FR2708311B1 (fr) 1995-09-01
US5466122A (en) 1995-11-14
DE69405334D1 (de) 1997-10-09
DE69405334T2 (de) 1998-02-12
FR2708311A1 (fr) 1995-02-03
EP0636766B1 (de) 1997-09-03

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