EP1335112B1 - Agencement de pivotement d'aube de stator dans une turbomachine - Google Patents

Agencement de pivotement d'aube de stator dans une turbomachine Download PDF

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Publication number
EP1335112B1
EP1335112B1 EP03290287A EP03290287A EP1335112B1 EP 1335112 B1 EP1335112 B1 EP 1335112B1 EP 03290287 A EP03290287 A EP 03290287A EP 03290287 A EP03290287 A EP 03290287A EP 1335112 B1 EP1335112 B1 EP 1335112B1
Authority
EP
European Patent Office
Prior art keywords
pivot
connecting rod
spring
washer
engaged
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.)
Expired - Lifetime
Application number
EP03290287A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1335112A1 (fr
Inventor
Alain Chatel
Fabrice Marois
Dominique Raulin
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1335112A1 publication Critical patent/EP1335112A1/fr
Application granted granted Critical
Publication of EP1335112B1 publication Critical patent/EP1335112B1/fr
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

  • This invention is a result of a stator vane pivoting arrangement in a turbomachine.
  • the stator vanes fixed in a turbomachine and used to straighten the flow of gases before the next rotor stage of the rotor, may be of variable pitch, that is to say that their orientation is controlled according to of the machine's diet. They are then mounted on external pivots that protrude out of the stator housing and are connected to rods that a common control ring, surrounding the stator housing, rotates at will.
  • the rotation of the links produces a similar rotation of the vanes.
  • the transmission of the rotation is acquired by a suitable adjustment which may include a mutual support of plane faces established on an end section of the blade pivot and on a bore at the end of the rod, see for example the document EP -A-11 56 227: This end section and drilling are often squares.
  • a solution is offered with the invention, which is by its most general definition a stator vane pivoting arrangement in a turbomachine, comprising a vane pivot having an end protruding out of the stator and including a cross section. flat faces, and a control rod engaged on the end of the blade pivot by a bore limited by planar faces associated with the flat faces of the pivot, characterized in that it comprises a spring biased between the pivot and the link and arranged to press one of the flat faces of the pivot against one of the flat faces of the link.
  • the assemblies of these documents are also of a special kind.
  • the spring of the invention is an independent piece, distinct from the rest of the conventional square section assembly that does not need to be modified, the spring being only added to it.
  • the springs comprise a pierced washer placed on the rod and engaged around the end of the blade pivot, and a flexible flange of the washer, engaged on one side of the edge of the rod which is opposed to a the faces of the pivot on which the washer abuts, making with the washer a more open angle than a free state of the spring.
  • a turbomachine portion comprises a stator casing 1 carrying blades 2 fixed but orientable by pivots 3, located at the outer ends of the blades 2 and in bearings 4 passing through the housing 1; the inner ends of the blades 2 are united by a ring 5 engaged around an inner pivot 6 and which helps to maintain the circular stages of the blades 2 in place.
  • the pivots 3 pass through the stator casing 1 and end at an outer end 7, one of which Section 8 has a square shape. Further outside, the end 7 is threaded and receives a nut 9.
  • a link 10 is articulated between the end 7 and a control ring 11 around the stator housing 1 and at a short distance from the blade 2
  • the control ring 11 circles the stator housing 1 and is rotated by known means such as cylinders according to the control of the machine. It rotates the rod 10 around the pivot 3, as well as the latter and the entire blade 2.
  • the rod 10 comprises a hole 13 of square shape to its eyelet 17 end, and which comprises flat faces bearing on the flat faces of the pivot 3 to turn it.
  • a spring 15 is added to the device. It is distinct from the other parts of the assembly and in particular from the connecting rod 10 and the pivot 3, and it consists of a washer 16 placed on the eyelet 17 of the rod 10 and a flange 18 substantially at right angles with the washer 16 extending along a side edge face 19 of the washer 16.
  • the flange 18 has a corrugation 20 facing the side edge face 19 and the top touches.
  • a square bore 21 is formed through the washer 16.
  • the proportions of the spring 15 are chosen so that the flange 18 is pushed back when the bore 21 is engaged on the square section 8 of the end of the pivot 3, even though that one of the edge faces of the piercing 21 touches one of flat faces 12 (opposite to the side edge face 19) of the square section 8, and that the flat face 12 of the square section 8 which is opposite to the preceding touches the flat face 13 complementary to the eyelet 17 rod.
  • a tension is exerted on the spring 15, by which the angle of the washer 16 and the flange 18 is open relative to a free state, and it is reflected by a contact pressure between a pair planar faces 12 and 13 of the pivot 3 and the rod 10, which continues during all operating states of the machine.
  • the link 10 and the blade 2 remain at a fixed mutual angular position.
  • All the blades 2 of the stage controlled by the ring 11 are equipped with a similar spring 15. It may be useful to check that all the springs 15 will be mounted in the same way, in order to avoid differences in the positioning of the clearance between the piercing 21 and the square section 8 of the pivot 3.
  • a tongue 22 may be added to spring 15, which is fixed to the washer 16 and directed perpendicularly to it as the flange 18 already encountered, but which is not intended to be elastically deformed when the spring is placed, but to provide a foolproof function not to place the spring 15 only on one side.
  • the tongue 22 extends along the end faces of the wafer 23 of the rod 10 when the spring 15 has been correctly placed, but it prevents the washer 16 from resting on the eyelet 17 of the link 10 in the opposite case.
  • the invention would be practicable with other polygonal sections of the blade pivot and rod drilling.

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)
  • Control Of Turbines (AREA)
EP03290287A 2002-02-07 2003-02-05 Agencement de pivotement d'aube de stator dans une turbomachine Expired - Lifetime EP1335112B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0201459A FR2835562B1 (fr) 2002-02-07 2002-02-07 Agencement de pivotement d'aube de stator dans une turbomachine
FR0201459 2002-02-07

Publications (2)

Publication Number Publication Date
EP1335112A1 EP1335112A1 (fr) 2003-08-13
EP1335112B1 true EP1335112B1 (fr) 2006-05-03

Family

ID=27589602

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03290287A Expired - Lifetime EP1335112B1 (fr) 2002-02-07 2003-02-05 Agencement de pivotement d'aube de stator dans une turbomachine

Country Status (9)

Country Link
US (1) US6799945B2 (ru)
EP (1) EP1335112B1 (ru)
JP (1) JP4050158B2 (ru)
CA (1) CA2418356C (ru)
DE (1) DE60304908T2 (ru)
ES (1) ES2261886T3 (ru)
FR (1) FR2835562B1 (ru)
RU (1) RU2315869C2 (ru)
UA (1) UA76114C2 (ru)

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2854648B1 (fr) * 2003-05-07 2005-07-15 Snecma Moteurs Fixation avec rattrapage de jeu d'un levier de commande sur des aubes a angle de calage variable
GB2402180B (en) * 2003-05-30 2006-09-20 Rolls Royce Plc Variable stator vane actuating levers
FR2866058B1 (fr) * 2004-02-05 2006-06-02 Snecma Moteurs Levier de commande du calage angulaire d'une aube dans une turbomachine
GB2412947B (en) 2004-04-07 2006-06-14 Rolls Royce Plc Variable stator vane assemblies
FR2877059B1 (fr) * 2004-10-27 2007-02-02 Snecma Moteurs Sa Biellette de commande destinee a l'entrainement d'une aube a calage variable
GB0505147D0 (en) * 2005-03-12 2005-04-20 Rolls Royce Plc Securing arrangement
US7753647B2 (en) * 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7690889B2 (en) * 2005-07-20 2010-04-06 United Technologies Corporation Inner diameter variable vane actuation mechanism
US7588415B2 (en) * 2005-07-20 2009-09-15 United Technologies Corporation Synch ring variable vane synchronizing mechanism for inner diameter vane shroud
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US8172517B2 (en) * 2006-12-19 2012-05-08 Rolls-Royce North American Technologies, Inc. Passive guide vane control
US9353643B2 (en) * 2007-04-10 2016-05-31 United Technologies Corporation Variable stator vane assembly for a turbine engine
JP5256977B2 (ja) * 2008-10-03 2013-08-07 株式会社Ｉｈｉ ターボチャージャ
US8414248B2 (en) 2008-12-30 2013-04-09 Rolls-Royce Corporation Variable geometry vane
DE102009047006A1 (de) * 2009-11-23 2011-05-26 Robert Bosch Gmbh Aufladeeinrichtung
US8794910B2 (en) 2011-02-01 2014-08-05 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US10208618B2 (en) * 2013-02-04 2019-02-19 United Technologies Corporation Vane arm having a claw
WO2015026420A1 (en) * 2013-08-22 2015-02-26 United Technologies Corporation Vane arm assembly
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
CA2990290C (en) 2015-07-01 2023-10-03 Big Hat Investments, LLC Vehicle mounted fork lift and method
US10815818B2 (en) * 2017-07-18 2020-10-27 Raytheon Technologies Corporation Variable-pitch vane assembly
GB201711582D0 (en) * 2017-07-19 2017-08-30 Rolls Royce Plc Unison ring assembly
DE102017222209A1 (de) 2017-12-07 2019-06-13 MTU Aero Engines AG Leitschaufelanbindung sowie Strömungsmaschine
US11008879B2 (en) * 2019-01-18 2021-05-18 Raytheon Technologies Corporation Continuous wedge vane arm with failsafe retention clip
US10837309B2 (en) 2019-04-09 2020-11-17 Raytheon Technologies Corporation Retention clip for variable vane arm
US11391174B2 (en) 2019-09-17 2022-07-19 Raytheon Technologies Corporation Vane arm clip for variable stator vanes
US20210254557A1 (en) * 2020-02-13 2021-08-19 Honeywell International Inc. Variable vane system for turbomachine with linkage having tapered receiving aperture for unison ring pin
US11680494B2 (en) * 2020-02-14 2023-06-20 Raytheon Technologies Corporation Vane arm torque transfer plate

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2029859A1 (de) * 1970-06-18 1972-02-03 Motoren Turbinen Union Verstell Leitapparat fur Turbomaschi nen
US4668165A (en) * 1986-03-27 1987-05-26 The United States Of America As Represented By The Secretary Of The Air Force Super gripper variable vane arm
US4767264A (en) * 1986-10-31 1988-08-30 United Technologies Corporation Vane lever arm construction
GB8913988D0 (en) * 1989-06-17 1989-08-09 Rolls Royce Plc Improvements in or relating to control of variable stator vanes
CA2082709A1 (en) * 1991-12-02 1993-06-03 Srinivasan Venkatasubbu Variable stator vane assembly for an axial flow compressor of a gas turbine engine
US5211537A (en) * 1992-03-02 1993-05-18 United Technologies Corporation Compressor vane lock
US6019574A (en) * 1998-08-13 2000-02-01 General Electric Company Mismatch proof variable stator vane
JP2001329851A (ja) * 2000-05-19 2001-11-30 Mitsubishi Heavy Ind Ltd 可変容量タービンの可変ノズル機構

Also Published As

Publication number Publication date
DE60304908D1 (de) 2006-06-08
JP2003239899A (ja) 2003-08-27
FR2835562B1 (fr) 2004-07-16
US6799945B2 (en) 2004-10-05
FR2835562A1 (fr) 2003-08-08
DE60304908T2 (de) 2006-12-21
CA2418356C (en) 2009-12-15
UA76114C2 (ru) 2006-07-17
CA2418356A1 (en) 2003-08-07
ES2261886T3 (es) 2006-11-16
JP4050158B2 (ja) 2008-02-20
EP1335112A1 (fr) 2003-08-13
RU2315869C2 (ru) 2008-01-27
US20030147743A1 (en) 2003-08-07

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