EP1308630A1 - Statorsektor für einen Verdichter eines Turbotriebwerks - Google Patents

Statorsektor für einen Verdichter eines Turbotriebwerks Download PDF

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Publication number
EP1308630A1
EP1308630A1 EP02292634A EP02292634A EP1308630A1 EP 1308630 A1 EP1308630 A1 EP 1308630A1 EP 02292634 A EP02292634 A EP 02292634A EP 02292634 A EP02292634 A EP 02292634A EP 1308630 A1 EP1308630 A1 EP 1308630A1
Authority
EP
European Patent Office
Prior art keywords
housing
rotation
sectors
fixed
sectorized
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
EP02292634A
Other languages
English (en)
French (fr)
Other versions
EP1308630B1 (de
Inventor
Jean-Louis Bertrand
Jean-Marc Claude Perrollaz
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 Moteurs SA
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 Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1308630A1 publication Critical patent/EP1308630A1/de
Application granted granted Critical
Publication of EP1308630B1 publication Critical patent/EP1308630B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246Fastening of diaphragms or stator-rings
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/52Casings; Connections of working fluid for axial pumps
    • F04D29/54Fluid-guiding means, e.g. diffusers
    • F04D29/541Specially adapted for elastic fluid pumps
    • F04D29/542Bladed diffusers

Definitions

  • the invention presented here concerns the high pressure turbine of a turbomachine such as a turbojet engine used on an airplane. It concerns more precisely a sectorized fixed rectifier for a turbomachine compressor.
  • US-A-4,126,405 discloses a segmented mounting of a turbine distributor.
  • Document FR-A-2 728 015 discloses a stator distributor of a turbine comprising sectors each consisting of an inner segment and an outer segment connected by blades.
  • a housing integrated in the stator of the compressor is intended to support the butted areas to each other. of the anti-rotation means are provided to prevent the rotation of the sectors supported by the housing.
  • the present invention has been designed to to further improve the manufacture and cost of a fixed rectifier for turbomachine compressor.
  • the housing is made in two parts or more, this which facilitates the manufacture.
  • the parts of the housing and the rectifier sectors are associated by a system forming slide and slide.
  • Anti-rotation means are designed to prevent the rotation of sectors relative to the crankcase.
  • the housing is made of two parts in the shape of a semicircle.
  • the casing comprising two radial flanks being face
  • the slide means comprises two Opposite grooves made in flanks, edges external segments of the sectors constituting the slider means.
  • the anti-rotation means fixed to the planes of joint can then include at least one bar immobilized between the two grooves by said means fastening and forming a stop for a sliding sector in a casing slide.
  • This bar can be a pair of tweezers inserted by bringing the two branches together in dwellings of intended reception in the throats, and immobilized in these dwellings by loosening of the two branches, thus realizing said fixing means.
  • Ways anti-rotation attached to the joint planes can also include at least one anti-rotation lock constituted by an element comprising slide means adapted to the slider means of the parts of the carter, the element also comprising means immobilization on the crankcase.
  • These means immobilization can be of the tenon-mortise type, a tenon engaging in a mortise when the element is pushed in a direction perpendicular to the sliding direction of the element in the housing, thus realizing said fixing means.
  • the segment outside the sector adjacent to that element may have one of its ends that has a clearance so that, when this adjacent sector is slipped on contact said element, the element can be pushed into said perpendicular direction.
  • the anti-rotation means blocked on the parts of the housing may then comprise at least one anti-rotation lock constituted by an element comprising slide means adapted to means forming a slide of the parts of the casing, the element also comprising means immobilization on the crankcase.
  • These means immobilization can be of the tenon-mortise type, a tenon engaging in a mortise when the element is pushed in a direction perpendicular to the sliding direction of the element in the housing, thereby realizing said locking means.
  • the segment outside a sector adjacent to that element may have one of its ends that presents a clearance so that when this adjacent area is slipped into contact with said element, the element can be pushed in said perpendicular direction.
  • Figure 1 is a partial sectional view of a compressor of a turbomachine using sectorized fixed rectifiers 1, 2 and 3 according to the invention. These rectifiers are functionally identical.
  • the rectifier 1 will be described more precisely. It includes a built-in circular case 4 in the stator of the compressor and supporting sectors such as sector 5.
  • a sector 5 consists of a segment inside 7 and an outer segment 6 connected between they by blades 8.
  • Figure 2 is a partial view and exploded sectorized fixed rectifier 1. It includes example a housing in two parts in the form of a semicircle. Figure 2 shows partially one of the parts 11 of this case with one of his joint plans 12 intended to be fixed on a joint plane corresponding to the other part of the housing. Three sectors 5 being assembled are represented. For sector 5, we recognize the outer segment 6, the inner segment 7 and the blades 8 which connect them.
  • the housing portion 11 comprises two flanks radial 12 and 13 facing each other and each provided of a throat.
  • the throats are located vis-à-vis constitute a slide.
  • the edges 21 and 22 of the segment outside 6 of sector 5 protrude outwards to ensure a slide function with respect to the slide formed by the casing portion 11.
  • an anti-rotation lock is installed at the joint plane 12 of the housing part 11. It can be a bar or a lock such as the one shown in Figure 4.
  • Figure 2 also shows an anti-rotation lock 30 disposed between two sectors 5.
  • This latch 30 is shown in cavalier view in Figure 3. It is formed an element 31 which is placed between the two flanks 12 and 13 of the housing portion 11 (see Figure 2).
  • the element 31 is in the shape of an arc of a circle and extended by an outer edge 32 and an inner edge 33.
  • the edges 32 and 33 are provided so that the lock 30 can slide in the grooves of the part of casing 11.
  • the outer edge 32 has a lug 34 protruding from the plane of the element 31. It is even for the lug 35 of the inner edge 33.
  • Figures 5 and 6 illustrate two steps of setting up an anti-rotation lock 30 between two sectors. 5.
  • a only flanks of the housing portion 11 has been represent. We can see the gorge 14 provided in this flank.
  • Figure 5 shows a first sector 5 already installed (to the left of the figure) and a second Sector 5 being installed (on the right of the figure). Between these two sectors was introduced by sliding a latch 30. Note that the height of the groove 14 allows the passage of the outer edge of the latch 30 with his ergot 34.
  • the element 30 is slipped to come into stop on the first sector 5. This corresponds to the element 30 at a position relative to the part of housing 11 such that the pin 34 is in vis-à-vis a notch 15 machined in the part of 11. Then just exercise on the lock 30 a push up (for the representation of Figures 5 and 6) for the pin 34 to enter the notch 15, the latch 30 being then in raised position.
  • the second sector 5 can then be pushed to lock 30.
  • This second sector 5 present, at the end in contact with the latch 30, a clearance 23 such as a portion of the outer segment 6 goes under lock 30.
  • Anti-rotation bolt 40 of joint plane shown in Figure 4 is mounted in the same way than the lock in Figure 3. It is formed of an element 25 between the two sides of the casing. Element 41 is extended by an outer edge 42 and an inner edge 43. The outer edge 42 has a lug 44 projecting from the plane of element 41. The same applies to the lug 45 of the edge interior 43.
EP02292634A 2001-10-31 2002-10-24 Statorsektor für einen Verdichter eines Turbotriebwerks Expired - Lifetime EP1308630B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0114102 2001-10-31
FR0114102A FR2831615B1 (fr) 2001-10-31 2001-10-31 Redresseur fixe sectorise pour compresseur d'une turbomachine

Publications (2)

Publication Number Publication Date
EP1308630A1 true EP1308630A1 (de) 2003-05-07
EP1308630B1 EP1308630B1 (de) 2006-08-23

Family

ID=8868935

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02292634A Expired - Lifetime EP1308630B1 (de) 2001-10-31 2002-10-24 Statorsektor für einen Verdichter eines Turbotriebwerks

Country Status (9)

Country Link
US (1) US6890151B2 (de)
EP (1) EP1308630B1 (de)
JP (1) JP4181375B2 (de)
CA (1) CA2409972C (de)
DE (1) DE60214106T2 (de)
ES (1) ES2266430T3 (de)
FR (1) FR2831615B1 (de)
RU (1) RU2287090C2 (de)
UA (1) UA75069C2 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2859509A1 (fr) * 2003-09-10 2005-03-11 Snecma Moteurs Arret en rotation des secteurs d'aubes de redresseurs par des barrettes dans les plans de joint du carter
FR2948736A1 (fr) * 2009-07-31 2011-02-04 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
WO2012153037A1 (fr) * 2011-05-09 2012-11-15 Snecma Virole annulaire de moteur d'aeronef comportant une fenetre d'introduction d'aubes
EP2933437A1 (de) * 2014-04-16 2015-10-21 United Technologies Corporation Systeme und verfahren für verdrehsicherungsfunktionen
EP2943658B1 (de) 2013-01-08 2017-03-29 United Technologies Corporation Statordrehschutzvorrichtung

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7033135B2 (en) * 2003-11-10 2006-04-25 General Electric Company Method and apparatus for distributing fluid into a turbomachine
US7144218B2 (en) * 2004-04-19 2006-12-05 United Technologies Corporation Anti-rotation lock
FR2878293B1 (fr) * 2004-11-24 2009-08-21 Snecma Moteurs Sa Montage de secteurs de distributeur dans un compresseur axial
JP4918263B2 (ja) 2006-01-27 2012-04-18 三菱重工業株式会社 軸流圧縮機の静翼環
US20080025838A1 (en) * 2006-07-25 2008-01-31 Siemens Power Generation, Inc. Ring seal for a turbine engine
US8128354B2 (en) * 2007-01-17 2012-03-06 Siemens Energy, Inc. Gas turbine engine
FR2913052B1 (fr) * 2007-02-22 2011-04-01 Snecma Commande des aubes a angle de calage variable
EP2211023A1 (de) * 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Leitschaufelsystem für eine Strömungsmaschine mit segmentiertem Leitschaufelträger
GB2468848B (en) * 2009-03-23 2011-10-26 Rolls Royce Plc An assembly for a turbomachine
EP2339120B1 (de) * 2009-12-22 2015-07-08 Techspace Aero S.A. Leitschaufelstufe einer Strömungsmaschine und zugehöriger Verdichter
US8454303B2 (en) * 2010-01-14 2013-06-04 General Electric Company Turbine nozzle assembly
US20110243725A1 (en) * 2010-03-31 2011-10-06 General Electric Company Turbine shroud mounting apparatus with anti-rotation feature
US9074489B2 (en) 2012-03-26 2015-07-07 Pratt & Whitney Canada Corp. Connector assembly for variable inlet guide vanes and method
US10428832B2 (en) 2012-08-06 2019-10-01 United Technologies Corporation Stator anti-rotation lug
US10309235B2 (en) 2012-08-27 2019-06-04 United Technologies Corporation Shiplap cantilevered stator
US10190434B2 (en) * 2014-10-29 2019-01-29 Rolls-Royce North American Technologies Inc. Turbine shroud with locating inserts
WO2016071224A1 (en) * 2014-11-03 2016-05-12 Nuovo Pignone Srl Sector for the assembly of a stage of a turbine and corresponding manufacturing method
BE1023619B1 (fr) * 2015-06-26 2017-05-18 Safran Aero Boosters S.A. Carter de compresseur de turbomachine axiale
US20190309641A1 (en) * 2018-04-04 2019-10-10 United Technologies Corporation Gas turbine engine having cantilevered stators with sealing members

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2945290A (en) * 1957-09-16 1960-07-19 Gen Electric Stator vane half ring assemblies
US4126405A (en) * 1976-12-16 1978-11-21 General Electric Company Turbine nozzle
FR2728015A1 (fr) * 1994-12-07 1996-06-14 Snecma Distributeur monobloc sectorise d'un stator de turbine de turbomachine
EP1104836A2 (de) * 1999-12-03 2001-06-06 General Electric Company Haltefeder für Leitschaufelsektoren und deren Halterung

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US3365173A (en) * 1966-02-28 1968-01-23 Gen Electric Stator structure
US4126914A (en) 1976-06-22 1978-11-28 Cotton, Incorporated Process and apparatus for treating fibrous materials for subsequent processing
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
US5197856A (en) * 1991-06-24 1993-03-30 General Electric Company Compressor stator
US5141395A (en) * 1991-09-05 1992-08-25 General Electric Company Flow activated flowpath liner seal
US5846050A (en) * 1997-07-14 1998-12-08 General Electric Company Vane sector spring

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2945290A (en) * 1957-09-16 1960-07-19 Gen Electric Stator vane half ring assemblies
US4126405A (en) * 1976-12-16 1978-11-21 General Electric Company Turbine nozzle
FR2728015A1 (fr) * 1994-12-07 1996-06-14 Snecma Distributeur monobloc sectorise d'un stator de turbine de turbomachine
EP1104836A2 (de) * 1999-12-03 2001-06-06 General Electric Company Haltefeder für Leitschaufelsektoren und deren Halterung

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2859509A1 (fr) * 2003-09-10 2005-03-11 Snecma Moteurs Arret en rotation des secteurs d'aubes de redresseurs par des barrettes dans les plans de joint du carter
EP1515002A1 (de) * 2003-09-10 2005-03-16 Snecma Moteurs Verdrehsicherung für Turbinenstatorschaufeln in der Gehäusetrennebene
US7059832B2 (en) 2003-09-10 2006-06-13 Snecma Moteurs Rotation-locking of sectors of rectifier blades by bars in the parting planes of the housing
FR2948736A1 (fr) * 2009-07-31 2011-02-04 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
WO2011012679A3 (fr) * 2009-07-31 2011-04-21 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
FR2975124A1 (fr) * 2011-05-09 2012-11-16 Snecma Virole annulaire de moteur d’aeronef comportant une fenetre d’introduction d’aubes
WO2012153037A1 (fr) * 2011-05-09 2012-11-15 Snecma Virole annulaire de moteur d'aeronef comportant une fenetre d'introduction d'aubes
GB2504883A (en) * 2011-05-09 2014-02-12 Snecma Aircraft engine annular shroud comprising an opening for the insertion of blades
GB2504883B (en) * 2011-05-09 2017-12-13 Snecma Aircraft engine annular shroud comprising an opening for the insertion of blades
US9879549B2 (en) 2011-05-09 2018-01-30 Snecma Aircraft engine annular shroud comprising an opening for the insertion of blades
EP2943658B1 (de) 2013-01-08 2017-03-29 United Technologies Corporation Statordrehschutzvorrichtung
EP2933437A1 (de) * 2014-04-16 2015-10-21 United Technologies Corporation Systeme und verfahren für verdrehsicherungsfunktionen
US9745864B2 (en) 2014-04-16 2017-08-29 United Technologies Corporation Systems and methods for anti-rotational features

Also Published As

Publication number Publication date
FR2831615B1 (fr) 2004-01-02
RU2287090C2 (ru) 2006-11-10
JP4181375B2 (ja) 2008-11-12
EP1308630B1 (de) 2006-08-23
CA2409972C (en) 2011-04-12
JP2003161297A (ja) 2003-06-06
DE60214106D1 (de) 2006-10-05
ES2266430T3 (es) 2007-03-01
CA2409972A1 (en) 2003-04-30
DE60214106T2 (de) 2007-04-12
US20030082051A1 (en) 2003-05-01
UA75069C2 (en) 2006-03-15
US6890151B2 (en) 2005-05-10
FR2831615A1 (fr) 2003-05-02

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