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EP1308630B1 - Statorsektor für einen Verdichter eines Turbotriebwerks - Google Patents

Statorsektor für einen Verdichter eines Turbotriebwerks Download PDF

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Publication number
EP1308630B1
EP1308630B1 EP02292634A EP02292634A EP1308630B1 EP 1308630 B1 EP1308630 B1 EP 1308630B1 EP 02292634 A EP02292634 A EP 02292634A EP 02292634 A EP02292634 A EP 02292634A EP 1308630 B1 EP1308630 B1 EP 1308630B1
Authority
EP
European Patent Office
Prior art keywords
casing
rotation
fixed stator
stator according
parts
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
EP02292634A
Other languages
English (en)
French (fr)
Other versions
EP1308630A1 (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 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 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

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers

Definitions

  • the invention presented here concerns the high-pressure turbine of a turbomachine such as a turbojet engine used on an airplane. It relates more specifically to a sectorized fixed rectifier for a turbomachine compressor.
  • 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.
  • An integrated casing in the stator of the compressor is intended to support the abutting sectors to each other.
  • Anti-rotation means are provided to prevent rotation of the sectors supported by the housing.
  • the present invention has been designed to further improve the manufacture and cost of a fixed rectifier for a turbomachine compressor.
  • the housing is made of two or more parts, which facilitates the manufacture.
  • the parts of the housing and the rectifier sectors are associated by a system forming a slide and slider.
  • Anti-rotation means are provided to prevent rotation of the sectors relative to the housing.
  • the housing consists of two parts in the form of a semicircle.
  • the casing comprising two radial flanks facing each other, the slideway means comprise two opposite grooves formed in the flanks, the edges of the outer segments of the sectors constituting the slider means.
  • the anti-rotation means attached to the joint planes may then comprise at least one bar immobilized between the two grooves by said fixing means and forming a stop for a sliding sector in a slide of the housing.
  • This bar may be a pair of tweezers inserted by bringing the two branches together in receiving housings provided in the grooves, and immobilized in these housing by loosening the two branches, thereby achieving said fixing means.
  • the anti-rotation means attached to the joint planes may also include at least one anti-rotation lock constituted by an element comprising slider means adapted to the slide means of the housing parts, the element also comprising immobilization means on the housing.
  • These immobilization means may 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 achieving said fastening means.
  • the outer segment of the sector adjacent to said element may have one of its ends which has a clearance so that when this adjacent sector is slid in contact with said element, the element can be pushed in said perpendicular direction.
  • the anti-rotation means blocked on the housing parts may then comprise at least one anti-rotation lock consisting of an element comprising slide means adapted to the slide means of the housing parts, the element also comprising immobilization means on the crankcase.
  • These immobilization means may be of the tenon-mortise type, a tenon engaging in a mortise when the element is pushed in a direction perpendicular to the direction of sliding of the element in the housing, thus realizing said locking means .
  • the outer segment of a sector adjacent to said element may have one of its ends which has a clearance so that when this adjacent sector is slid in 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 sectored fixed rectifiers 1, 2 and 3 according to the invention. These rectifiers are functionally identical.
  • the rectifier 1 will be described more precisely. It comprises a circular casing 4 integrated in the stator of the compressor and supporting sectors such as sector 5.
  • a sector 5 consists of an inner segment 7 and an outer segment 6 interconnected by vanes 8.
  • FIG. 2 is a partial and exploded view of the sectorized fixed rectifier 1. It comprises, for example, a two-part casing in the shape of a semicircle. Figure 2 partially shows one of the parts 11 of this housing with one of its joint planes 16 to be fixed on a corresponding joint plane of the other part of the housing. Three sectors 5 being edited are represented. For a sector 5, the outer segment 6, the inner segment 7 and the blades 8 which connect them are recognized.
  • the housing portion 11 comprises two radial flanks 12 and 13 facing each other and each provided with a groove.
  • the grooves are located vis-à-vis to form a slide.
  • the edges 21 and 22 of the outer segment 6 of the sector 5 project outwards to provide a sliding function with respect to the slide formed by the housing part 11.
  • an anti-rotation lock is installed at the joint plane 16 of the housing portion 11. It may be a bar or a lock such as the one shown in Figure 4.
  • FIG. 2 also shows an anti-rotation lock 30 disposed between two sectors 5.
  • This lock 30 is shown in a cavalier view in FIG. 3. It is formed of an element 31 which is placed between the two sides 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 latch 30 can slide in the grooves of the housing portion 11.
  • the outer edge 32 has a lug 34 projecting from the plane of the housing. element 31. The same applies to the lug 35 of the inner edge 33.
  • FIGs 5 and 6 illustrate two steps of the establishment of an anti-rotation lock 30 between two sectors 5.
  • FIG. 5 illustrates two steps of the establishment of an anti-rotation lock 30 between two sectors 5.
  • Only one of the sides of the housing portion 11 has been shown. We can see the groove 14 provided in this flank.
  • Figure 5 shows a first sector 5 already installed (left of the figure) and a second sector 5 being mounted (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 its lug 34.
  • the element 30 is slid up to abut on the first sector 5. This corresponds for the element 30 to a relative position relative to the housing portion 11 such that the lug 34 is vis-à-vis screw of a notch 15 machined in the housing portion 11. It is then sufficient to exert on the latch 30 upward thrust (for the representation of Figures 5 and 6) so that the lug 34 enters the notch 15, the latch 30 is then in raised position.
  • the second sector 5 can then be pushed towards the latch 30.
  • This second sector 5 present, at the end in contact with the latch 30, a clearance 23 such that a portion of the outer segment 6 passes under the latch 30.
  • the anti-rotation lock 40 of the joint plane shown in Figure 4 is mounted in the same manner as the lock of Figure 3. It is formed of an element 41 which is placed between the two sides of the housing part. The element 41 is extended by an outer edge 42 and an inner edge 43. The outer edge 42 has a lug 44 protruding from the plane of the element 41. The same goes for the lug 45 of the inner edge 43.

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)

Claims (11)

  1. Sektorierter feststehender Leitapparat für einen Verdichter eines Turbotriebwerks, welcher aufweist:
    - kreisbogenförmige Sektoren (5), die jeweils aus einem inneren Segment (7) und einem äußeren Segment (6) bestehen, die durch Schaufeln (8) miteinander verbunden sind,
    - ein kreisförmiges Gehäuse (4), das in den Stator des Verdichters integriert ist und dazu bestimmt ist, die aneinander angrenzenden Sektoren (5) abzustützen, die
    - Drehblockiermittel, die dazu bestimmt sind, die Drehbewegung der von dem Gehäuse gestützten Sektoren zu verhindern,
    - wobei das Gehäuse (4), das von mindestens zwei Teilen (11) gebildet wird, die aneinander grenzen und an Verbindungsebenen aneinander befestigt sind, Mittel aufweist, die eine Gleitschiene bilden,
    - wobei die Sektoren (5) Mittel als Gleitschieber aufweisen, die an die Mittel als Gleitschiene der Teile des Gehäuses angepasst sind,
    - wobei die Drehblockiermittel aus Drehblockiermitteln bestehen, die durch Befestigungsmittel an den Verbindungsebenen der Teile des Gehäuses befestigt sind,
    dadurch gekennzeichnet,
    dass die Drehblockiermittel aus Drehblockiermitteln bestehen, die an den Teilen des Gehäuses durch Arretiermittel in dem Bereich, wo die Sektoren aneinandergrenzen, festgestellt sind.
  2. Sektorierter feststehender Leitapparat nach Anspruch 1,
    dadurch gekennzeichnet,
    dass das Gehäuse (4) von zwei halbkreisförmigen Teilen (11) gebildet wird.
  3. Sektorierter feststehender Leitapparat nach einem der Ansprüche 1 oder 2,
    dadurch gekennzeichnet,
    dass bei dem Gehäuse, das zwei radiale, einander gegenüberliegende Seitenteile (12, 13) aufweist, die Mittel, die eine Gleitschiene bilden, aus zwei einander gegenüberliegenden Auskehlungen (14) bestehen, die in den Seitenteilen ausgeführt sind, wobei die Ränder (21, 22) der äußeren Segments (6) der Sektoren (5) die Mittel darstellen, die Gleitschieber bilden.
  4. Sektorierter feststehender Leitapparat nach Anspruch 3,
    dadurch gekennzeichnet,
    dass die an den Verbindungsebenen befestigten Drehblockiermittel mindestens einen Bügel umfassen, der zwischen den beiden Auskehlungen durch die genannten Befestigungsmittel festgestellt wird und einen Anschlag für einen in einer Gleitschiene des Gehäuses gleitenden Sektor bildet.
  5. Sektorierter feststehender Leitapparat nach Anspruch 4,
    dadurch gekennzeichnet,
    dass der Bügel eine Klemme mit zwei Schenkeln ist, die unter Annähern der beiden Schenkel aneinander in Aufnahmesitze, die in den Auskehlungen vorgesehen sind, eingeführt wird und in diesen Aufnahmen durch Loslassen der beiden Schenkel festgesetzt wird, wobei auf diese Weise die Befestigungsmittel hergestellt werden.
  6. Sektorierter feststehender Leitapparat nach Anspruch 3,
    dadurch gekennzeichnet,
    dass die an den Verbindungsebenen befestigten Drehblockiermittel mindestens einen Drehblockierriegel (40) umfassen, der von einem Element (41) gebildet wird, das Mittel, die Gleitschieber bilden (42, 43), enthält, welche an die Gleitschiene bildenden Mittel der Teile des Gehäuses angepasst sind, wobei das Element auch Arretiermittel (44, 45) zum Arretieren an dem Gehäuse enthält.
  7. Sektorierter feststehender Leitapparat nach Anspruch 6,
    dadurch gekennzeichnet,
    dass die Arretiermittel des Typs Zapfen-Zapfenloch sind, wobei ein Zapfen in ein Zapfenloch eingreift, wenn das Element (41) in der im rechten Winkel zur Gleitrichtung des Elements in dem Gehäuse verlaufenden Richtung verschoben wird, wobei auf diese Weise die genannten Befestigungsmittel hergestellt werden.
  8. Sektorierter feststehender Leitapparat nach Anspruch 7,
    dadurch gekennzeichnet,
    dass das äußere Segment des an dieses Element (41) angrenzenden Sektors an einem seiner Enden eine Aussparung aufweist, damit dieses Element in dieser im rechten Winkel verlaufenden Richtung verschoben werden kann, wenn dieser angrenzende Sektor bis zum Kontakt mit diesem Element geschoben wird.
  9. Sektorierter feststehender Leitapparat nach Anspruch 3,
    dadurch gekennzeichnet,
    dass die an den Teilen des Gehäuses festgestellten Drehblockiermittel mindestens einen Drehblockierriegel (30) umfassen, der von einem Element (31) gebildet wird, das Mittel, die Gleitschieber bilden (32, 33), enthält, welche an die Gleitschiene bildenden Mittel der Teile des Gehäuses angepasst sind, wobei das Element auch Arretiermittel (34, 35) zum Arretieren an dem Gehäuse enthält.
  10. Sektorierter feststehender Leitapparat nach Anspruch 9,
    dadurch gekennzeichnet,
    dass die Arretiermittel des Typs Zapfen-Zapfenloch sind, wobei ein Zapfen in ein Zapfenloch eingreift, wenn das Element (31) in einer im rechten Winkel zur Gleitrichtung des Elements in dem Gehäuse verlaufenden Richtung verschoben wird, wobei auf diese Weise die genannten Arretiermittel hergestellt werden.
  11. Sektorierter feststehender Leitapparat nach Anspruch 10,
    dadurch gekennzeichnet,
    dass das äußere Segment eines an dieses Element (31) angrenzenden Sektors an einem seiner Enden eine Aussparung aufweist, damit dieses Element in dieser im rechten Winkel verlaufenden Richtung verschoben werden kann, wenn dieser angrenzende Sektor bis zum Kontakt mit diesem Element geschoben wird.
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 EP1308630A1 (de) 2003-05-07
EP1308630B1 true 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)

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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
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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
FR2948736B1 (fr) * 2009-07-31 2011-09-23 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
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
FR2975124B1 (fr) 2011-05-09 2013-05-24 Snecma Virole annulaire de moteur d'aeronef comportant une fenetre d'introduction d'aubes
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
US9353767B2 (en) 2013-01-08 2016-05-31 United Technologies Corporation Stator anti-rotation device
US9745864B2 (en) * 2014-04-16 2017-08-29 United Technologies Corporation Systems and methods for anti-rotational features
US10190434B2 (en) * 2014-10-29 2019-01-29 Rolls-Royce North American Technologies Inc. Turbine shroud with locating inserts
CN107208491B (zh) * 2014-11-03 2019-08-06 诺沃皮尼奥内股份有限公司 用于涡轮的级的组件的区段和对应的制造方法
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

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Also Published As

Publication number Publication date
RU2287090C2 (ru) 2006-11-10
US20030082051A1 (en) 2003-05-01
CA2409972C (en) 2011-04-12
DE60214106T2 (de) 2007-04-12
EP1308630A1 (de) 2003-05-07
DE60214106D1 (de) 2006-10-05
JP2003161297A (ja) 2003-06-06
US6890151B2 (en) 2005-05-10
FR2831615B1 (fr) 2004-01-02
JP4181375B2 (ja) 2008-11-12
UA75069C2 (en) 2006-03-15
FR2831615A1 (fr) 2003-05-02
CA2409972A1 (en) 2003-04-30
ES2266430T3 (es) 2007-03-01

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