EP1515002A1 - Verdrehsicherung für Turbinenstatorschaufeln in der Gehäusetrennebene - Google Patents

Verdrehsicherung für Turbinenstatorschaufeln in der Gehäusetrennebene Download PDF

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Publication number
EP1515002A1
EP1515002A1 EP04292079A EP04292079A EP1515002A1 EP 1515002 A1 EP1515002 A1 EP 1515002A1 EP 04292079 A EP04292079 A EP 04292079A EP 04292079 A EP04292079 A EP 04292079A EP 1515002 A1 EP1515002 A1 EP 1515002A1
Authority
EP
European Patent Office
Prior art keywords
sector
housing
bar
groove
blade
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
EP04292079A
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English (en)
French (fr)
Other versions
EP1515002B1 (de
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
Original Assignee
SNECMA Moteurs SA
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.)
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Publication date
Application filed by SNECMA Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1515002A1 publication Critical patent/EP1515002A1/de
Application granted granted Critical
Publication of EP1515002B1 publication Critical patent/EP1515002B1/de
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Anticipated expiration legal-status Critical

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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
    • 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 that of the connection between sectors of straightener vanes.
  • a high-pressure compressor of a turbomachine comprises a stator consisting of a carter, which can be in several sectors, for example in two half-shells, in which are housed the ferrules of the rectifiers. These ferrules are not formed on 360 ° but include several sectors of blades. The ends of the blade sectors of rectifier are arranged vis-à-vis to form a ring of stator vanes.
  • aerodynamic forces due to the differences in pressures between the lower and upper surfaces of the straightener vanes and the forces due to friction of the blades on the abradable sectors of the blades of the rectifiers are applied to the sectors of straightener vanes.
  • the invention presents various embodiments that make it possible in particular to these disadvantages.
  • the invention relates to a device for stopping the rotation of at least one blade sector of rectifier mounted in a sector of the turbomachine casing, each blade sector of rectifier comprising a blade support base, the housing area comprising at least one minus two grooves extending in planes perpendicular to the crankcase rotation axis turbomachine and each receiving an edge of the base of the stator blade sector.
  • the device for stopping in rotation comprises an abutment positioned to extend axially, fitting on one side into the housing one of the throats and on the other side in the housing of the other gorge and, after the establishment of the complementary crankcase sector and during the operation of the turbomachine, coming into contact with the axial surface of each housing under the thrust of at least one sector of complementary straightener vanes in order to stop in rotating at least one blade sector, the abutment being either integral with the blade sector, or a bar comprising at least one end with a longitudinal slot for a elastic mounting and a hold in 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 from a first groove to the housing of a second non-adjacent groove axially, the bar bearing against at least two intermediate grooves and forming a stop for at least two sectors of blades adjacent axially.
  • the bar bears against four intermediate grooves and abutment shape for three axially adjacent blade sectors.
  • the bar comprises a plurality of axially extending portions.
  • the abutment integral with the sector blade comprises a stop 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 reported by brazing at the base of the blade sector and positioned at the end of the blade sector.
  • the abutment comprises a first abutment element corresponding to the housing a first groove and a second stop member corresponding to the housing a second throat.
  • each housing comprises a groove of a determined 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 throat and, on the side of the end of the crankcase sector, by an axial surface adapted to retain the bar once in place in the housing.
  • FIG. 1 shows a sector 1 of the casing of a turbo-machine capable of being fixed to a complementary sector to form the complete housing.
  • This sector of semi-cylindrical shape, called half-shell and whose axis is the axis of rotation of the turbomachine, comprises two ends E1 and E2 each provided with a flange 9 adapted to return to 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 includes also a semicircular flange 8 provided with holes.
  • each housing sector 1 has several grooves semi-circular 7 open towards the inside of the housing, each being adapted to receive a rectifier blade sector.
  • a crown of straightener vanes is constituted by at least two sectors of vanes of rectifier each positioned in one of the two crankcase sectors, the ends of the sectors of blades being opposite.
  • a rectifier blade sector comprises a base 3 of cylindrical and radially outer shape, called outer platform. This base cylindrical 3 supports the vanes 5 of the stator fixed to each other by a cylindrical base 4 radially inner, called inner platform.
  • Each groove 7 of the sector of casing 1 is provided with two circular grooves 6 so that each receives one of the two edges of the outer deck of the stator vanes area.
  • the invention presents various embodiments that will notably make it possible to remedy to at least some of these disadvantages.
  • Figures 2 to 7 show a first embodiment according to the invention.
  • FIG. 2 represents a longitudinal bar 16 able to be positioned axially at the end of the ferrule sector.
  • this bar 16 comprises a first end 13 longitudinal followed by a step 14 and a second longitudinal end.
  • the first and second ends are each equipped 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 the end 15 of the bar, a first end arm 20 and a second arm end 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 blade sector of rectifier disposed in a ferrule sector of the turbomachine housing.
  • 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 throat extends axially.
  • Each of the two throats receives a semicircular edge of a platform Stator Blades Sector Outside.
  • Each semicircular gorge ends at least at one of its ends by a housing 17-1, 17-2, 17-3, 17-4 of dimensions greater than those of the corresponding throat.
  • the ends 13 and 15 of the bar 16 are adapted to be placed respectively in the housings 17-1 and 17-2.
  • FIG. 4 illustrates the respective dimensions of the groove 6-1 and the housing 17-1 corresponding.
  • Figure 5 is a right view of Figure 4.
  • the semi-circular groove 6-1 has a radial dimension, that is to say a groove height L3 and leads to its end on a housing 17-1 of radial dimension L2 greater than L3. So, the housing 17-1 defines an axially extending axial contact surface 18-1 and radially beyond the depth and height of the groove.
  • FIG. 6 shows the end D35 of the semi-circular groove 6-2 facing the throat semicircular 6-1.
  • This semicircular groove 6-2 of radial dimension L3 ends with a housing 17-2 of radial dimension L2 greater than L3.
  • This housing 17-2 defines a axial contact surface 18-2 extending axially and radially beyond the depth and height of the throat.
  • grooves opposite may have different dimensions, one of the other.
  • Figure 7 shows the left view of Figure 6.
  • the arms ends 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 of so that the end arms 23, 22 and 20, 21 respectively come into contact with each other. with the contact surface 18-1, respectively 18-2.
  • the end arms can then to be released.
  • the dimension L1 corresponding to the width of one end of the bar released must be equal to or greater than the dimension L2 corresponding to the dimension radial (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 mounting elastic.
  • housings 17-1 and 17-2 may have radial dimensions and different axial, it is the same for the ends 13 and 15 of the bar 16 put in place in these dwellings.
  • Figure 13 shows three rectifier blade sectors set up in one sector.
  • crankcase rotatably stopped by rotation devices comprising the housings end of the semi-circular grooves and the bars 16 whose ends are set place in these dwellings, abut against the contact surface of these dwellings and are held elastically by the pressure of the end arms against the surfaces perpendicular to the contact surface of these dwellings.
  • the bars 16 comprise a portion of recess longitudinal dimension more or less big. In general, the greater the radial distance between two dwellings opposite is important, the longer the longitudinal dimension of the step part. is tall.
  • the bar 16-1 has a relatively big.
  • the slots 12 of this bar extend along the ends of the bar up to part of the step portion.
  • FIG. 12 represents a partial section in a transverse plane of the assembly of a casing sector 1 to a casing sector 2 at the stop device in rotation of rectifier blade sectors.
  • the bar 16 is pushed against the axial contact surface 18-2 by the base 3 of the stator blade sector which exerts a pressing force F against the axial surface of the bar 16 parallel to the axial surface of the bar placed in contact with 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 grooves semi-circular turbomachine housing shell and a stop disposed in end of the straightener blade sector. As illustrated in FIG. 14, this stop can be carried out in a single block with the outer platform of the blade sector of rectifier or can be welded by soldering to this same platform.
  • FIG. 14 illustrates an abutment comprising an abutment disposed on an edge cross section of the outer platform of the stator vane sector, this abutment comprising a first portion 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 portions 41 and 42 have a radial dimension (or height) less than or equal to radial dimension L2 of the housing illustrated in FIGS. 4 to 7 and greater than or equal to 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 disassembling the crankcase sectors. This realization also makes it possible to have no leakage of fluid between the stages of the turbine engine.
  • 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 sector of blades of rectifier is shown slid in the grooves opposite 6-1 and 6-2. This sector includes the blades 5 and an inner platform 4.
  • the device for stopping rotation of the sector of straightener vanes comprises a bar 26 arranged in suitable housings. This device is more particularly detailed in Figure 9.
  • the outer platform 3 of the stator vane sector is provided with axially on its edges of semicircular hooks 34-1 and 34-2 of radial dimensions (or height) and axial less than the dimensions (height and depth) of 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.
  • 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 semicircular groove by a 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.
  • These axial surfaces 31-1, respectively 31-2, and 32-1 have dimensions greater than the section of the corresponding throat.
  • the bar 26 comprises a first end 23 and a second end 25, this last end comprising a longitudinal slot opening. On both sides 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 a surface axial 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 with on their outer periphery a shoulder defined in particular by an axial surface 28-1, respectively 29-1 adapted to contact the surface 31-2 of the groove of the housing 30-2 to serve as a stop.
  • the arms ends 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.
  • a inserted in the housing 30-2, the two end arms 28 and 29 are released from in such a way that the axial surfaces 28-1 and 29-1 are in contact with the axial surface 31-2 of the groove of housing 30-2.
  • the dwellings 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 25 of the bar when the arms 28 and 29 are brought into contact by pinching, is smaller than the radial dimension of the opening of the housing 30-1, 30-2.
  • the end 25 of the bar can be inserted in 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 slot longitudinally adapted to be placed in a housing according to the realization of the 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 sector of stator vanes.
  • only one bar is used in correspondence with the appropriate housing, as a stopping device in rotation of several sectors of stator vanes.
  • the intermediate gorges between the first housing receiving one end of the bar and the second receiving housing the second end of the bar do not have housing but a groove in which is housed the bar.
  • the bar 46 is configured in several connected parts between them by connecting parts so that the ends of the grooves semicirculars arranged in different radial positions lead to a part 46. These parts are configured to be in contact with elements of the housing at certain points of the bar 46, for example at the contact points 50, 52, 54, 56. However, games remain between the bar and the housing, for example games J, J1 to J8, leaving room for fluid leaks between the stages of the compressor rectifiers.
  • FIG. 11 shows schematically the bar 46 represented by a continuous line when it is in a T1 state, that is, when it is inserted into the slots correspondents.
  • the triangles symbolize the points of contact of the bar with the housing.
  • the stop (bar or abutment fixed to the blade sector) of the rectifier sector rotation stop device has the advantage of not getting lost during disassembly of the ferrule sectors of the turbomachine.
  • the invention is not limited either to the embodiments of the stop device in described above, only as an example, but 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 Verdrehsicherung für Turbinenstatorschaufeln in der Gehäusetrennebene Active EP1515002B1 (de)

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 true EP1515002A1 (de) 2005-03-16
EP1515002B1 EP1515002B1 (de) 2006-10-18

Family

ID=34130785

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04292079A Active EP1515002B1 (de) 2003-09-10 2004-08-24 Verdrehsicherung für Turbinenstatorschaufeln in der Gehäusetrennebene

Country Status (9)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2943658B1 (de) 2013-01-08 2017-03-29 United Technologies Corporation Statordrehschutzvorrichtung

Families Citing this family (6)

* 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 (de) * 2012-11-27 2017-04-05 Safran Aero Boosters SA Leitrad einer axialen Turbomaschine mit segmentiertem Innendeckband und zugehöriger Verdichter
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

Citations (6)

* 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
US5318402A (en) * 1992-09-21 1994-06-07 General Electric Company Compressor liner spacing device
EP1104836A2 (de) * 1999-12-03 2001-06-06 General Electric Company Haltefeder für Leitschaufelsektoren und deren Halterung
EP1308630A1 (de) * 2001-10-31 2003-05-07 Snecma Moteurs Statorsektor für einen Verdichter eines Turbotriebwerks
FR2832179A1 (fr) * 2001-11-14 2003-05-16 Snecma Moteurs Stator d'une machine et procedes de montage et demontage

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 (6)

* 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
US5318402A (en) * 1992-09-21 1994-06-07 General Electric Company Compressor liner spacing device
EP1104836A2 (de) * 1999-12-03 2001-06-06 General Electric Company Haltefeder für Leitschaufelsektoren und deren Halterung
EP1308630A1 (de) * 2001-10-31 2003-05-07 Snecma Moteurs Statorsektor für einen Verdichter eines Turbotriebwerks
FR2832179A1 (fr) * 2001-11-14 2003-05-16 Snecma Moteurs Stator d'une machine et procedes de montage et demontage

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2943658B1 (de) 2013-01-08 2017-03-29 United Technologies Corporation Statordrehschutzvorrichtung

Also Published As

Publication number Publication date
JP4056508B2 (ja) 2008-03-05
CA2478890C (fr) 2012-01-03
DE602004002823T2 (de) 2007-08-23
DE602004002823D1 (de) 2006-11-30
FR2859509A1 (fr) 2005-03-11
CA2478890A1 (fr) 2005-03-10
ES2271807T3 (es) 2007-04-16
US7059832B2 (en) 2006-06-13
RU2293187C2 (ru) 2007-02-10
JP2005083388A (ja) 2005-03-31
EP1515002B1 (de) 2006-10-18
FR2859509B1 (fr) 2006-01-13
RU2004127166A (ru) 2006-02-20
US20050079047A1 (en) 2005-04-14
UA79771C2 (uk) 2007-07-25

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