EP2402615B1 - Leitschaufelbaugruppe - Google Patents

Leitschaufelbaugruppe Download PDF

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Publication number
EP2402615B1
EP2402615B1 EP10167643.5A EP10167643A EP2402615B1 EP 2402615 B1 EP2402615 B1 EP 2402615B1 EP 10167643 A EP10167643 A EP 10167643A EP 2402615 B1 EP2402615 B1 EP 2402615B1
Authority
EP
European Patent Office
Prior art keywords
rectifier
intermediate piece
blade
outer collar
stator
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
EP10167643.5A
Other languages
English (en)
French (fr)
Other versions
EP2402615A1 (de
Inventor
Hervé Grelin
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 Aero Boosters SA
Original Assignee
Techspace Aero 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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP10167643.5A priority Critical patent/EP2402615B1/de
Priority to US13/169,935 priority patent/US8944752B2/en
Priority to CA2744571A priority patent/CA2744571C/en
Publication of EP2402615A1 publication Critical patent/EP2402615A1/de
Application granted granted Critical
Publication of EP2402615B1 publication Critical patent/EP2402615B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the present invention relates to the field of turbomachines. It relates more particularly to a rectifier architecture in an axial turbomachine compressor.
  • Axial compressors are well known per se and are used inter alia in turbomachines.
  • These low or high pressure compressors comprise several stages of rotating blades which are separated by fixed stages of rectifiers which are intended to reposition the velocity vector of the fluid leaving the previous stage before sending it to the next stage.
  • rectifier stages consist of stationary vanes, also called stator vanes, connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein.
  • the rectifier may be composed of an assembly of several circular stages threaded step by step or may be composed of a one-piece assembly directly integrating several stages optionally via a half-shell technology.
  • the compressor rectifiers are made of metallic material (titanium, steel or aluminum) and the blades in the rectifier are essentially of material and unique profile on the same floor.
  • the outer shell provides the essential mechanical functions.
  • the inner ferrules are themselves relatively flexible, thus ensuring no structural function and providing little stiffness to the system.
  • the blades are reported on the outer ferrules by various assembly technologies (welding, riveting, bolting) and are attached to the inner ferrules by a flexible seal (commonly silicone type).
  • the present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.
  • the present invention aims more particularly to provide a more rigid stator architecture than a conventional architecture while being more easily removable.
  • the present invention also aims to provide a stiffened rectifier architecture for the use of stator blades made in geometries and / or with different materials.
  • the present invention also aims to provide a stiffened rectifier architecture without introducing significant aerodynamic disturbances within the rectifier.
  • Another object of the present invention is to manufacture bladed rectifiers with a low mass and low cost for any compressor consisting of a stator type assembly proposed in conjunction with a rotor type either bladed disks monobloc or drum or other.
  • the present invention also aims to separate the interface functions with the other parts (dawn, abradable) provided by the intermediate piece of the functions of resistance to the loss of fan blade (fan blade out) provided by the ferrule. Such separation is known from the document US 3,070,353 .
  • a first object of the present invention relates to a turbomachine rectifier comprising a plurality of stator blades connecting an inner ferrule to an outer ferrule, each of said vanes comprising a blade and a platform at the top of the blade, characterized in that comprises an intermediate piece disposed between the inner ferrule and the outer ferrule and fixed to the outer ferrule, said intermediate piece having openings for the passage of the blade blades and said blade platforms coming to rest, on one side, on the ferrule external and, on the other hand, on the intermediate piece, said intermediate piece is in the form of a half-shell intended to integrate a plurality of stages of stator vanes.
  • the present invention relates to a turbomachine comprising a rectifier as described above.
  • the present invention relates to a new compressor rectifier architecture.
  • a conventional construction 1, as mentioned above and schematically illustrated to the left of the figure 1 the structural function is ensured by the single outer shell 3.
  • the architecture according to the present invention 2 is constituted for its outer shell of a structural ferrule 3 and a non-structural ferrule holder 6, which will also be called indifferently blade holder, rectifier holder or intermediate piece.
  • the invention is based on a fixing device between the different elements.
  • Each of the stages of the rectifier consists of a combination of blades connected together via the stator head straightener holder, a straightener holder or an inner ferrule at the bottom. The rigidity of the assembly is then brought to the top by the outer shell while the connection between the blades is provided by the blade holder.
  • the rectifier according to the invention is built according to a multi-stage rectifier architecture via a half shell technology.
  • a schematic view, a sectional view and an exploded three-dimensional view of the various elements constituting the rectifier according to the invention are respectively presented on the figures 2 , 3 and 4 .
  • the rectifier comprises the inner ferrule 4, the outer ferrule 3, the intermediate piece 6, the stator vanes 5 and the fastening elements 8 to connect the ferrule. intermediate part 6 and the outer shell 3.
  • the stator blade 5 comprises a blade 11 and a platform at the top of blade 10, it may optionally include a platform at the bottom of the blade.
  • the intermediate piece 6 is in the form of a half-shell incorporating, for example, three stages of rectifier as in the examples illustrated in FIGS. figures 3 and 4 , and comprises perforations 14 for the passage of the blades 11.
  • the platform at the top of blade 10 then comes from one side to rest on the intermediate part 6 while, on the other side, it rests on the outer shell 3.
  • the blade holder 6 further comprises zones 13 arranged between the rectifying stages and intended to receive the abradables 7 usually deposited on the outer shell 3. Preferably, these zones are housings as illustrated in FIG. figure 2 .
  • a shock absorbing joint 9 may optionally be disposed between the platform of the blade 10 and the blade holder 6 and / or between the platform of the blade 10 and the outer shell 3.
  • the seal 9 is in the form of a half-ring and has openings 14 for the passage of the blade blades as shown in FIG. figure 4 .
  • the attachment between the blade holder 6 and the outer shell 3 can be made at the abradable level 7 as illustrated in FIGS. figures 2 and 3 , and / or at the level of the assembly flanges between outer shells 12 and / or at the level of the blade platforms 10. It is effected via fastening elements 8 which can be metal (rivets, lockbolts, bolts, etc.) or composites (eg clips ...) or welding.
  • stator vanes 5 can be rigidly attached to the inner ferrule 4 by means of fasteners as mentioned above in order to stiffen the assembly by the inner ferrule and thus impart increased rigidity to the rectifier (not shown).
  • the stiffened architecture according to the present invention may comprise stator vanes of different materials and / or geometries.
  • the stator vanes can be made of a composite or metallic material or comprise a mixture of both.
  • the outer shell and the blade holder can be made respectively of a composite material or metal.
  • This architecture has the advantage of stiffening all the stators by their outer shell, the rectifier holder being used to position the rectifiers and maintain them in position (separation of the functions of rigidity and interface / positioning).
  • the axial displacement along the motor axis is reduced by the rigidity of the blade holder and the outer shell.
  • the advantage of the device lies in the fact that it is more rigid than a conventional assembly (no or few openings in the outer shell) while being more easily removable. It thus makes it possible to produce completely composite rectifiers but also makes it possible to interchangeably mount composite blades, metal blades or a mixture of the two.
  • the rigidified architecture according to the present invention makes it possible not only to combine blades made of different materials but also blades with different geometries. The combination of different vanes can thus be optimized according to the required functions (aerodynamics, stiffness, mechanical strength).
  • the stiffened architecture according to the invention has fewer fastening elements than a conventional architecture with fixing by lockbolts or rivets independent on each blade.
  • the rectifiers thus obtained will gain in mass compared to the existing one, by the use of composite materials for the bladders and for the outer shells as well as by the suppression of a maximum of fixing elements.
  • This architecture separates the structural functions provided by the outer shell of the connection function performed by the blade holder. This allows a better tolerance to damage, the most damaged part in case of impact (absorption of foreign bodies) being then the blade holder and not the shell. This allows the maximum use of composite technologies, the process and material can be selected closer to the needs of each room.
  • the use of an intermediate piece in the form of a half-shell incorporating several stages has the advantage that the geometric accidents generating stress (open, abradable) are absorbed by this intermediate piece (non-structural) and not by the ferrule external (structural).
  • the outer shell can be better sized for the loss of fan blade (fan blade) by a simpler geometry.
  • the architecture according to the invention also has the advantage that the outer shell and the ferrule holder are mounted rigidly relative to each other.
  • An intermediate piece in the form of a complete ring can be mounted only if the outer shell remains half-shell because two annular parts can not be assembled rigidly without deformation of one or both parts.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (14)

  1. Leitschaufel einer Strömungsmaschine, aufweisend:
    - eine Vielzahl von Statorschaufeln (5), die einen Innenring (4) mit einem Außenring (3) verbinden, wobei jede der Schaufeln (5) ein Schaufelblatt (11) und eine Schaufelblattkopfplattform (10) aufweist,
    - ein Zwischenstück (6), das zwischen dem Innenring (4) und dem Außenring (3) angeordnet ist und am Außenring (3) befestigt ist, wobei das Zwischenstück (6) Aufschnitte (14) für den Durchgang der Schaufelblätter (11) der Schaufel aufweist, und wobei die Schaufelplattformen (10) auf einer Seite auf dem Außenring (3) und auf der anderen Seite auf dem Zwischenstück (6) ruhen,
    dadurch gekennzeichnet, dass das Zwischenstück (6) in Form von einer Halbschale, die für die Integration einer Vielzahl von Statorschaufelstufen (5) bestimmt ist, gebaut ist.
  2. Leitschaufel nach Anspruch 1, dadurch gekennzeichnet, dass das Zwischenstück (6) Zonen (13), die zwischen den Statorschaufelstufen (5) angeordnet sind und zur Aufnahme der Abriebdichtungen (7) des Außenrings (3) bestimmt sind, aufweist.
  3. Leitschaufel nach irgendeinem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Befestigung des Zwischenstückes (6) am Außenring (3) im Bereich der Abriebdichtungen (7) und/oder im Bereich von Verbindungsflanschen (12) zwischen Außenringen (3) und/oder im Bereich der Schaufelplattformen (10) erfolgt.
  4. Leitschaufel nach Anspruch 3, dadurch gekennzeichnet, dass die Befestigung mit Hilfe von Befestigungsmitteln (8) erfolgt.
  5. Leitschaufel nach Anspruch 3, dadurch gekennzeichnet, dass die Befestigung durch Schweißen erfolgt.
  6. Leitschaufel nach irgendeinem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass sie ferner eine Stoßdämpferdichtung (9), die zwischen der Schaufelplattform (10) und dem Zwischenstück (6) und/oder zwischen der Schaufelplattform (10) und dem Außenring (3) angeordnet ist, aufweist.
  7. Leitschaufel nach Anspruch 6, dadurch gekennzeichnet, dass die Dämpferdichtung (9) in Form von einem Halbring gebaut ist und Aufschnitte (14) für den Durchgang der Schaufelblätter der Schaufel (11) hat.
  8. Leitschaufel nach irgendeinem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Statorschaufeln (5) mit Hilfe von Befestigungsmitteln (8) am Innenring (4) starr befestigt sind, um der Leitschaufel eine höhere Steifigkeit zu verleihen.
  9. Leitschaufel nach Anspruch 4 oder 8, dadurch gekennzeichnet, dass die Befestigungsmittel (8) aus metallischem Material oder aus Verbundwerkstoff sind.
  10. Leitschaufel nach Anspruch 9, dadurch gekennzeichnet, dass die Befestigungsmittel (8) Nieten, Verriegelungsbolzen, Bolzen oder Klammern sind.
  11. Leitschaufel nach irgendeinem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass sie Statorschaufeln (5) aus metallischem Material und/oder aus Verbundwerkstoff aufweist.
  12. Leitschaufel nach irgendeinem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass sie Statorschaufeln (5) verschiedener Geometrien aufweist.
  13. Leitschaufel nach irgendeinem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass der Außenring (3) und das Zwischenstück (6) jeweils aus einem metallischen Material oder aus einem Verbundwerkstoff hergestellt sind.
  14. Strömungsmaschine, die eine Leitschaufel nach irgendeinem der Ansprüche 1 bis 13 aufweist.
EP10167643.5A 2010-06-29 2010-06-29 Leitschaufelbaugruppe Active EP2402615B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP10167643.5A EP2402615B1 (de) 2010-06-29 2010-06-29 Leitschaufelbaugruppe
US13/169,935 US8944752B2 (en) 2010-06-29 2011-06-27 Compressor rectifier architecture
CA2744571A CA2744571C (en) 2010-06-29 2011-06-27 Compressor rectifier architecture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10167643.5A EP2402615B1 (de) 2010-06-29 2010-06-29 Leitschaufelbaugruppe

Publications (2)

Publication Number Publication Date
EP2402615A1 EP2402615A1 (de) 2012-01-04
EP2402615B1 true EP2402615B1 (de) 2015-08-12

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Application Number Title Priority Date Filing Date
EP10167643.5A Active EP2402615B1 (de) 2010-06-29 2010-06-29 Leitschaufelbaugruppe

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US (1) US8944752B2 (de)
EP (1) EP2402615B1 (de)
CA (1) CA2744571C (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6012222B2 (ja) * 2012-03-30 2016-10-25 三菱重工業株式会社 静翼セグメント、これを備える軸流流体機械及びその静翼連結方法
EP2811121B1 (de) * 2013-06-03 2019-07-31 Safran Aero Boosters SA Verbundgehäuse für einen Kompressor einer axialen Turbomaschine mit Metallbefestigungsflansch
EP2930308B1 (de) 2014-04-11 2021-07-28 Safran Aero Boosters SA Facettengehäuse einer axialen Turbomaschine

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US3070353A (en) * 1958-12-03 1962-12-25 Gen Motors Corp Shroud assembly
US4643636A (en) * 1985-07-22 1987-02-17 Avco Corporation Ceramic nozzle assembly for gas turbine engine
US4655682A (en) * 1985-09-30 1987-04-07 United Technologies Corporation Compressor stator assembly having a composite inner diameter shroud
FR2600379B1 (fr) * 1986-06-18 1988-09-02 Snecma Redresseur de soufflante de turboreacteur multiflux
US4907946A (en) * 1988-08-10 1990-03-13 General Electric Company Resiliently mounted outlet guide vane
US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
US5272869A (en) * 1992-12-10 1993-12-28 General Electric Company Turbine frame
US5474419A (en) * 1992-12-30 1995-12-12 Reluzco; George Flowpath assembly for a turbine diaphragm and methods of manufacture
FR2702242B1 (fr) * 1993-03-03 1995-04-07 Snecma Etage d'aubes libres à une extrémité.
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
US5690469A (en) * 1996-06-06 1997-11-25 United Technologies Corporation Method and apparatus for replacing a vane assembly in a turbine engine
US5765993A (en) * 1996-09-27 1998-06-16 Chromalloy Gas Turbine Corporation Replacement vane assembly for fan exit guide
DE60026687T2 (de) * 2000-12-06 2006-11-09 Techspace Aero S.A. Statorstufe eines Verdichters
GB2388161A (en) * 2002-05-02 2003-11-05 Rolls Royce Plc Gas turbine engine compressor casing
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EP2075413B1 (de) * 2007-12-26 2011-10-26 Techspace Aero Vorrichtung zur Versteifung eines Stators einer Strömungsmaschine und deren Anwendung in Luftfahrzeugmotoren

Also Published As

Publication number Publication date
EP2402615A1 (de) 2012-01-04
US20110318174A1 (en) 2011-12-29
CA2744571A1 (en) 2011-12-29
US8944752B2 (en) 2015-02-03
CA2744571C (en) 2017-01-10

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