EP1515002B1 - Arrêt en rotation des secteurs d'aubes de redresseurs dans les plans de joint du carter - Google Patents

Arrêt en rotation des secteurs d'aubes de redresseurs dans les plans de joint du carter Download PDF

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Publication number
EP1515002B1
EP1515002B1 EP04292079A EP04292079A EP1515002B1 EP 1515002 B1 EP1515002 B1 EP 1515002B1 EP 04292079 A EP04292079 A EP 04292079A EP 04292079 A EP04292079 A EP 04292079A EP 1515002 B1 EP1515002 B1 EP 1515002B1
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EP
European Patent Office
Prior art keywords
sector
vanes
stop
seat
bar
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
EP04292079A
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German (de)
English (en)
French (fr)
Other versions
EP1515002A1 (fr
Inventor
Jean-Louis Bertrand
Léopold Jean-Marie De-Verduzan
Jean-François Laurent Chabot
Francis Dome
Stéphanie Pariset
Julien Girardot
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
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SNECMA SAS
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Publication of EP1515002A1 publication Critical patent/EP1515002A1/fr
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Publication of EP1515002B1 publication Critical patent/EP1515002B1/fr
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    • 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
    • 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

Definitions

  • the invention relates to the field of high-pressure turbojet compressors, and more particularly to the connection between sectors of straightener vanes.
  • a high-pressure compressor of a turbomachine comprises a stator consisting of a housing, which may be in several sectors, for example two half-shells, in which are housed the rings of the rectifiers. These ferrules are not formed over 360 ° but include several sectors of blades. The ends of the stator vanes sectors are arranged facing each other to form a stator vanes crown.
  • aerodynamic forces due to pressure differences between the lower surface and the upper surface of the stator vanes and the forces due to the friction of the blades on the abradable vanes of the stator vanes are applied to the rectifier blade sectors. These forces cause the rotation of the blade sectors in their housing which can come overlapping the joint plane of the two half-shells of the housing, which prevents disassembly of the latter during a maintenance operation.
  • the invention presents various embodiments which make it possible in particular to overcome these drawbacks.
  • the invention relates to a device for stopping the rotation of at least one sector of stator vanes mounted in a sector of the turbomachine casing, each sector of stator vanes comprising a base for supporting the blades, the sector of the casing. including at minus two grooves extending in planes perpendicular to the axis of rotation of the turbomachine casing and each receiving an edge of the base of the stator blade sector.
  • the rotational stop device comprises an abutment positioned to extend axially, fitting on one side in the housing of one of the grooves and on the other side in the housing of the other groove and, after the establishment of the complementary crankcase sector and during the operation of the turbomachine, coming into contact against the axial surface of each housing under the pressure of at least one blade sector of complementary rectifier in order to stop in rotation at least one blade sector, the stop being either integral with the blade sector, or a bar comprising at least one end with a longitudinal slot for resilient mounting and retention in the housing.
  • the bar comprises two ends of radial dimensions greater than those of the corresponding housing, said bar comprising a longitudinal slot at each of its ends.
  • the bar extends from the housing of a first groove to the housing of a second non-adjacent groove axially, the bar being in abutment against at least two intermediate grooves and forming a stop for at at least two axially adjacent blade sectors.
  • the bar bears against four intermediate grooves and forms a stop for three axially adjacent sectors of blades.
  • the bar comprises a plurality of axially extending portions.
  • the abutment integral with the blade sector comprises an abutment made in one block with the base of the blade sector and positioned at the end of the blade sector.
  • the abutment integral with the blade sector comprises an abutment soldered to the base of the blade sector and positioned at the end of the blade sector.
  • the abutment comprises a first abutment member corresponding to the housing of a first groove and a second abutment member corresponding to the housing of a second groove.
  • each housing comprises a groove of a predetermined width extending axially and delimited, on the side of the groove, by the axial surface of dimensions greater than the dimensions of the section of the groove and , on the side of the end of the sector of the housing, by an axial surface adapted to retain the bar once in place in the housing.
  • Figure 1 shows a sector 1 of the housing of a turbo-machine adapted to be attached to a complementary sector to form the complete housing.
  • This sector of semi-cylindrical shape called half-shell and having axis axis of rotation of the turbine engine, comprises two ends E1 and E2 each provided with a flange 9 adapted to enter contact with a flange of the complementary sector.
  • These flanges 9 are provided with holes 10 positioned opposite the holes of the flange of the complementary sector so as to fix the two complementary sectors between them.
  • Each ferrule sector also includes a semicircular flange 8 provided with holes.
  • Each housing sector 1 comprises a plurality of semi-circular grooves 7 open towards the inside of the housing, each being adapted to receive a sector of stator vanes.
  • a ring of stator vanes is constituted by at least two sectors of stator vanes each positioned in one of the two housing sectors, the ends of the vane sectors facing each other.
  • a rectifier blade sector comprises a base 3 of cylindrical and radially outer shape, called outer platform. This cylindrical base 3 supports the stator vanes 5 fixed to each other by a cylindrical base 4 radially inner, called inner platform.
  • Each groove 7 of the housing sector 1 is provided with two circular grooves 6 so that each receives one of the two edges of the outer platform of the stator blade sector.
  • the invention presents various embodiments that will in particular remedy at least some of these disadvantages.
  • Figures 2 to 7 show a first embodiment according to the invention.
  • Figure 2 shows a longitudinal bar 16 adapted to be positioned axially at the end of the ferrule sector.
  • this bar 16 comprises a first longitudinal end 13 followed by a recess 14 and a second longitudinal end.
  • the first and the second end are each provided with a longitudinal slot 12.
  • the slot 12 of the end 13 of the bar defines a first end arm 23 and a second end arm 22 on either side of the slot 12.
  • a first arm end 20 and a second end arm 21 are defined on either side of the slot 12.
  • the width of each end of the bar in the relaxed state is denoted L1.
  • This bar 16 is adapted to be put in place once a rectifier blade sector disposed in a ferrule sector of the casing of the turbomachine.
  • FIG. 3 illustrates an end E1 of a ferrule sector of the casing of the turbomachine.
  • Each groove 7-1, 7-2 of the end of the ferrule sector comprises two semicircular grooves 6-1 and 6-2, 6-3 and 6-4 positioned opposite. The depth of each groove extends axially.
  • Each of the two grooves receives a semicircular edge of an outer strut vanes platform.
  • Each semicircular groove terminates at least at one of its ends by a housing 17-1, 17-2, 17-3, 17-4 of larger dimensions than those of the corresponding groove.
  • the ends 13 and 15 of the bar 16 are adapted to be placed respectively in the housings 17-1 and 17-2.
  • the ends D34 of the groove 6-1 and D35 of the groove 6-2 are more specifically detailed respectively in FIGS. 4 and 5, FIGS. 6 and 7.
  • FIG. 4 illustrates the respective dimensions of the groove 6-1 and the corresponding housing 17-1.
  • FIG. 5 is a right view of FIG. 4.
  • the semicircular groove 6-1 has a radial dimension, that is to say a groove height L3 and opens at its end on a housing 17-1 of FIG. radial dimension L2 greater than L3.
  • the housing 17-1 defines an axial contact surface 18-1 extending axially and radially beyond the depth and height of the groove.
  • FIG. 6 shows the end D35 of the semicircular groove 6-2 facing the semicircular groove 6-1.
  • This semicircular groove 6-2 of radial dimension L3 terminates in a housing 17-2 of radial dimension L2 greater than L3.
  • This housing 17-2 defines an axial contact surface 18-2 extending axially and radially beyond the depth and height of the groove.
  • grooves facing each other may have different dimensions from one another.
  • Figure 7 shows the left view of Figure 6.
  • the end arms 23, 22 respectively 20, 21 of the bar are pressed together.
  • the ends 13 and 15 are respectively placed in the housings 17-1 and 17-2 so that the end arms 23, 22 and 20, 21 respectively come into contact with the contact surface 18-1, respectively 18-2.
  • the end arms can then be released.
  • the dimension L1 corresponding to the width of one end of the strip released must be equal to or greater than the dimension L2 corresponding to the radial dimension (or width) of the corresponding housing.
  • the bar 16 is held elastically by each of its ends in the corresponding housing.
  • each end of the bar must have a width L less than the dimension L2 of the corresponding housing so as to insert the end into the housing, which is called elastic mounting.
  • housings 17-1 and 17-2 may have different radial and axial dimensions, the same is true for the ends 13 and 15 of the bar 16 placed in these housing.
  • FIG. 13 shows three rectifier blade sectors set up in a crankcase sector, stopped in rotation by rotation devices comprising the housings at the end of the semicircular grooves and the bars 16 whose ends are put in place in these housings abut against the contact surface of these housings and are held elastically by the pressure of the end arms against the surfaces perpendicular to the contact surface of these housing.
  • the bars 16 comprise a recess portion of greater or lesser longitudinal dimension. In general, the greater the radial distance between two housings facing each other, the greater the longitudinal dimension of the recess portion.
  • the bar 16-1 has a relatively large step portion.
  • the slots 12 of this bar extend along the ends of the bar to a portion of the recess portion.
  • Figure 12 shows a partial sectional view in a transverse plane of the assembly of a housing sector 1 to a housing sector 2 at the rotational stop device of the sectors of the stator vanes.
  • the bar 16 is pushed against the axial contact surface 18-2 by the base 3 of the rectifier blade sector which exerts a pressing force F against the axial surface of the bar 16 parallel to the axial surface of the bar contacted with the axial contact surface 18-2.
  • FIG. 14 represents a second embodiment according to the invention.
  • the rotational stop device comprises the housings disposed at the end of the semicircular grooves of the ferrule housing of the turbomachine casing and an abutment disposed at the end of the rectifier blade sector. As illustrated in FIG. 14, this stop may be made in one piece with the outer platform of the stator vane sector or may be soldered by soldering to this same platform.
  • FIG. 14 illustrates an abutment comprising an abutment disposed on a transverse edge of the outer platform of the rectifier blade sector, this abutment comprising a first part 41 disposed at one end of the transverse edge and a second portion 42 disposed at the other end of the transverse edge.
  • first and second parts 41 and 42 have a radial dimension (or height) less than or equal to the radial dimension L2 of the housing illustrated in Figures 4 to 7 and greater than or equal to the radial dimension L3 of the corresponding semicircular groove.
  • the stop is integrated in the sector of stator vanes, which avoids losing it during a maintenance operation including the disassembly of the crankcase sectors. This embodiment also makes it possible to have no leakage of fluid between the stages of the turbomachine.
  • Figures 8 and 9 illustrate a third embodiment of the invention.
  • Figure 8 shows a relief view of the end of a crankcase sector. This end comprises the flanges 9 and 8 described above.
  • a rectifier blade sector is shown slid into the grooves 6-1 and 6-2 opposite. This sector comprises the blades 5 and an inner platform 4.
  • the device for stopping the rotation of the stator blade sector comprises a bar 26 arranged in suitable housings. This device is more particularly detailed in FIG. 9.
  • the outer platform 3 of the stator vane sector is provided axially on its edges with semicircular hooks 34-1 and 34-2 of radial dimensions. (or height) and axial less than the dimensions (height and depth) of the grooves 6-1 and 6-2 so that these hooks can slide in the corresponding grooves.
  • the groove 6-1, 6-2 is terminated by a housing 30-1, 30-2.
  • the housing 30-1 defines a groove extending in an axial plane (plane passing through the axis of rotation), the groove comprising a bottom surface 33-1 framed on the side of the semi-circular groove by an axial surface 32 -1 and, facing this surface, by an axial surface 31-1.
  • the housing 30-2 is made in an equivalent manner axially opposite the housing 30-1.
  • the bar 26 comprises a first end 23 and a second end 25, the latter end comprising a longitudinal slot opening. On either side of this slot are defined a first end arm 28 and a second end arm 29.
  • the end 23 of the bar 26 has a thickness greater than the width of the bottom of the groove 33-1.
  • this end 23 is provided on its periphery with a shoulder defined by an axial surface 24 adapted to come into contact with the axial surface 31. 1 of the groove of the housing 30-1 to serve as a stop.
  • the end arms 28 and 29 are provided on their outer periphery with a shoulder defined in particular by an axial surface 28-1, respectively 29-1 adapted to come into contact with the surface 31-2 of the groove of the housing 30-2 to serve as a stop.
  • the end arms 28 and 29 are brought together by pinching, the end 23 is slid into the groove of the housing 30-1, the end 25 is inserted into the groove of the housing 30. 2. Once inserted in the housing 30-2, the two end arms 28 and 29 are released so that the axial surfaces 28-1 and 29-1 are in contact with the axial surface 31-2 of the groove. housing 30-2.
  • the housings 30-1 and 30-2 thus define the contact surfaces 32-1 and 31-1, 31-2, with the bar 26, the latter being in abutment in one direction of rotation and in the other direction of rotation. against these contact surfaces.
  • the radial dimension of the end of the bar when the end arms 28 and 29 are in pinch contact, is smaller than the radial dimension of the opening of the housing 30-1, 30 -2.
  • the end 25 of the bar may be inserted into the groove of the housing 30-2 after pinching the end arms 28 and 29.
  • This embodiment makes it possible to maintain the bar in the housings.
  • Figures 10 and 11 illustrate a fourth embodiment of the invention.
  • the bar 46 comprises two ends 47 and 48 as defined in the first embodiment.
  • each end 47, 48 comprises a longitudinal slot adapted to be placed in a housing according to the embodiment of FIG. 3.
  • This bar 46 has a length such that it extends from a first housing corresponding to a first rectifier blade sector, to a second opposite housing corresponding to a third rectifier blade sector.
  • a single strip is used in correspondence with the appropriate housings, as a stop device in rotation of several rectifier blade sectors.
  • the intermediate grooves between the first housing receiving one end of the bar and the second housing receiving the second end of the bar do not include a housing but a groove in which is housed the bar.
  • the bar 46 is configured in several parts interconnected by connecting parts so that the ends of the semicircular grooves arranged in different radial positions open on a portion of the bar 46. These portions are configured to be in position. contact with elements of the casing at certain points of the bar 46, for example at the contact points 50, 52, 54, 56. However, gaps remain between the bar and the casing, for example the games J, J1 to J8, leaving room for fluid leaks between the stages of the compressor rectifiers.
  • Figure 11 shows schematically the bar 46 represented by a solid line when in a state T1, that is to say when it is inserted in the corresponding housing.
  • the triangles symbolize the points of contact of the bar with the housing.
  • the abutment (bar or abutment fixed to the blade sector) of the device for rotating the rectifier sector has the advantage of not being lost during disassembly of the ferrule sectors of the turbomachine.
  • the invention is not limited either to the embodiments of the rotation stop device described above, only by way of example, but it encompasses all variants that may be considered by those skilled in the art.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04292079A 2003-09-10 2004-08-24 Arrêt en rotation des secteurs d'aubes de redresseurs dans les plans de joint du carter Active EP1515002B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0310647 2003-09-10
FR0310647A FR2859509B1 (fr) 2003-09-10 2003-09-10 Arret en rotation des secteurs d'aubes de redresseurs par des barrettes dans les plans de joint du carter

Publications (2)

Publication Number Publication Date
EP1515002A1 EP1515002A1 (fr) 2005-03-16
EP1515002B1 true EP1515002B1 (fr) 2006-10-18

Family

ID=34130785

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04292079A Active EP1515002B1 (fr) 2003-09-10 2004-08-24 Arrêt en rotation des secteurs d'aubes de redresseurs dans les plans de joint du carter

Country Status (9)

Country Link
US (1) US7059832B2 (ja)
EP (1) EP1515002B1 (ja)
JP (1) JP4056508B2 (ja)
CA (1) CA2478890C (ja)
DE (1) DE602004002823T2 (ja)
ES (1) ES2271807T3 (ja)
FR (1) FR2859509B1 (ja)
RU (1) RU2293187C2 (ja)
UA (1) UA79771C2 (ja)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2911923B1 (fr) * 2007-01-25 2011-07-08 Snecma Redresseur acoustique pour carter de soufflante de turboreacteur
US20110189008A1 (en) * 2010-01-29 2011-08-04 General Electric Company Retaining ring for a turbine nozzle with improved thermal isolation
US9650905B2 (en) * 2012-08-28 2017-05-16 United Technologies Corporation Singlet vane cluster assembly
EP2735707B1 (fr) * 2012-11-27 2017-04-05 Safran Aero Boosters SA Redresseur de turbomachine axiale avec virole interne segmentée et compresseur associé
US9353767B2 (en) 2013-01-08 2016-05-31 United Technologies Corporation Stator anti-rotation device
JP6614407B2 (ja) * 2015-06-10 2019-12-04 株式会社Ｉｈｉ タービン
CN111486129B (zh) * 2020-04-20 2021-05-14 中国航发湖南动力机械研究所 静子整流环结构、压气机及航空发动机

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1009619A (en) * 1963-10-24 1965-11-10 Rolls Royce Improvements relating to compressors and turbines
DE3341871A1 (de) * 1983-11-19 1985-05-30 Brown, Boveri & Cie Ag, 6800 Mannheim Axialverdichter
US5141395A (en) * 1991-09-05 1992-08-25 General Electric Company Flow activated flowpath liner seal
US5318402A (en) * 1992-09-21 1994-06-07 General Electric Company Compressor liner spacing device
US5846050A (en) * 1997-07-14 1998-12-08 General Electric Company Vane sector spring
US6296443B1 (en) * 1999-12-03 2001-10-02 General Electric Company Vane sector seating spring and method of retaining same
FR2831615B1 (fr) * 2001-10-31 2004-01-02 Snecma Moteurs Redresseur fixe sectorise pour compresseur d'une turbomachine
FR2832179B1 (fr) * 2001-11-14 2004-02-27 Snecma Moteurs Stator d'une machine et procedes de montage et demontage

Also Published As

Publication number Publication date
ES2271807T3 (es) 2007-04-16
US20050079047A1 (en) 2005-04-14
CA2478890A1 (fr) 2005-03-10
FR2859509A1 (fr) 2005-03-11
CA2478890C (fr) 2012-01-03
JP4056508B2 (ja) 2008-03-05
JP2005083388A (ja) 2005-03-31
FR2859509B1 (fr) 2006-01-13
DE602004002823D1 (de) 2006-11-30
DE602004002823T2 (de) 2007-08-23
EP1515002A1 (fr) 2005-03-16
US7059832B2 (en) 2006-06-13
UA79771C2 (uk) 2007-07-25
RU2004127166A (ru) 2006-02-20
RU2293187C2 (ru) 2007-02-10

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