EP2404037B1 - Rotor à aubage intégral pour une turbomachine - Google Patents

Rotor à aubage intégral pour une turbomachine Download PDF

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Publication number
EP2404037B1
EP2404037B1 EP10713552.7A EP10713552A EP2404037B1 EP 2404037 B1 EP2404037 B1 EP 2404037B1 EP 10713552 A EP10713552 A EP 10713552A EP 2404037 B1 EP2404037 B1 EP 2404037B1
Authority
EP
European Patent Office
Prior art keywords
rotor according
rotor
sealing elements
blade
inspection
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.)
Not-in-force
Application number
EP10713552.7A
Other languages
German (de)
English (en)
Other versions
EP2404037A1 (fr
Inventor
Frank Stiehler
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2404037A1 publication Critical patent/EP2404037A1/fr
Application granted granted Critical
Publication of EP2404037B1 publication Critical patent/EP2404037B1/fr
Not-in-force legal-status Critical Current
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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing

Definitions

  • the invention relates to an integrally bladed rotor for a turbomachine, in particular for a gas turbine, wherein cavities are provided in the region of the blade necks between adjacent blades, which are formed by recesses in opposite sides of adjacent blade necks.
  • Rotors with integral blading are referred to as a blisk or bling, depending on whether there is a disk-shaped rotor or rotor with a cross-section in cross-section (referred to below as the rotor body).
  • Blisk is the short form of Bladed Disk and Bling of Bladed Ring.
  • an integrally bladed rotor according to the invention for a turbomachine, in particular for a gas turbine.
  • cavities are provided between adjacent blades which are formed by recesses in opposite sides of adjacent blade necks. From each cavity extends an inspection opening radially inwardly, which is accessible from the outside and allows an examination of the cavity from the outside. In this way, an inspection of the cavity is made possible, while the cavity is sealed as well as possible in the axial directions and in the radially outward direction.
  • the inspection openings are closed by sealing elements. After an inspection of the cavities, for example, after the Manufacture of the rotor or maintenance intervals has been performed, the inspection openings can thus be closed.
  • the sealing elements can be cylindrical. This allows a simple geometry of the sealing elements and the inspection opening to be sealed.
  • the sealing elements are made of a nickel-based material. This allows a temperature-resistant design of the sealing elements.
  • the sealing elements can be coated.
  • the surface properties of the sealing elements are improved and adapted in particular to the materials used of the blades.
  • the sealing elements are separately manufactured parts that are attached to the blade necks by press-fitting, positive locking and / or welding. In this way, a good seal of the inspection openings is ensured by the sealing elements and prevents slippage of the sealing elements.
  • the sealing elements are removably attached to the blade necks. This allows for inspection of the cavities at any one time.
  • the sealing elements extend for example over the entire axial length of the associated blade neck. Thus, a positioning of the sealing element in the axial direction is simplified.
  • each inspection opening opens into a channel extending in the axial direction. This channel allows easy access to the inspection opening.
  • the axially extending channel may be a cooling fluid channel. This provides improved cooling of the boundary between the rotor body and the blade necks.
  • a cover plate is arranged in the axial direction upstream and / or downstream of the channel.
  • the cover plate or the cover plates can cover the channel in whole or in part, whereby, for example, an axial movement of the sealing elements is prevented or limited.
  • the cover plate may form a guide for the cooling fluid. This allows, for example, a deflection of the cooling fluid flow from the axial direction of the channel in a radial direction.
  • the channels and the openings are coordinated so that it can be seen from the outside into the cavities. This allows easy inspection of the cavities with the eye or a device.
  • Each blade may be welded to the rotor body via an adapter made of a different material, and the channels may be provided at least between adjacent spacers.
  • the intermediate pieces it is possible to simplify the joining of the blades to the rotor base body, in particular if the blades and the rotor base body are made of different materials, for example in monocrystalline blades and polycrystalline rotor base body or in different alloys in which a fusion welding process is not applicable.
  • adjacent blade necks are separated by a narrow axial and radial gap and the inspection opening is formed by a local enlargement of the gap.
  • This may also be the case, for example, with monocrystalline vanes in which the vanes can not be joined by fusion welding.
  • the blade necks preferably have extensions which together form a cover strip extending in the circumferential direction, wherein the cover strip with adjacent rotors and shrouds forms a circumferential space which is traversed by cooling fluid.
  • a cooling of the rotors is possible.
  • An axially intermediate space and a rear space may be provided, wherein the axially extending channels connect the front space with the rear space. In this way, a flow of cooling fluid from the front gap results in the rear gap.
  • FIGS. 1 to 5 show a sector of an integrally bladed rotor 10.
  • the rotor 10 has a rotor body 12, which in the embodiment shown is a rotor disk.
  • the rotor base body 12 may, however, also be annular, for example.
  • the integrally bladed rotor 10 is designed for a gas turbine and may be located in the turbine section or in the compressor section.
  • the invention can also be applied to integrally bladed rotors of other turbomachines.
  • a plurality of blades 14 are provided, which are e.g. are connected via separate intermediate pieces 16 with the rotor body 12.
  • the blades 14 are made, for example, from single-crystalline nickel-based materials that do not allow fusion welding.
  • a blade 14 is first connected to an intermediate piece 16 by friction welding, in particular linear friction welding.
  • the intermediate piece 16 is made of a material other than the blade 14, for example of a polycrystalline material.
  • the blade 14 can then be attached to the rotor body 12 via the intermediate piece 16 by various methods.
  • a blade 14 is constructed as follows: radially inwardly a blade neck 18 is provided, from the blade neck 18, the blade 20 extends radially outward, at the outer end of the blade 20, an outer shroud 22 is provided.
  • the construction of the blade neck 18 is in the FIGS. 3 and 4 better to recognize.
  • a lightweight construction for the blade neck 18 is provided in the blade necks 18 .
  • recesses 24 are provided on the sides lying in the circumferential direction. Between adjacent blade necks 18 18 cavities 26 are formed by the recesses 24 in opposite sides of the blade necks (see FIG. 2 ). From each cavity 26, an inspection opening 28 extends radially inwardly and opens into a channel 30 extending in the axial direction. Each inspection opening 28 is assigned a channel 30.
  • the channels 30 are provided substantially between adjacent spacers 16.
  • the blade necks 18 each have a front and rear extension 32 in the axial direction.
  • the extensions 32 together form a running in the circumferential direction inner shroud 34.
  • the inner shroud 34 forms with adjacent rotors and optionally axial shrouds extending in the circumferential direction gap.
  • Such a space is formed in the axial direction in front of and behind the rotor base body 12, wherein this front and rear space is traversed by cooling fluid in order to cool the rotor 10 and in particular the rotor base body 12.
  • the channels 30 connect the front gap to the rear gap, thus allowing a flow of cooling fluid between the two spaces.
  • a cover plate 36 is arranged and fixed to the rotor base body 12.
  • the cover plate 36 forms a guide for the cooling fluid, wherein the cooling fluid is deflected in the present embodiment after flowing through the axially extending channels 30 in the radial direction to the outside.
  • a cover plate 36 is provided on the rear side of the rotor body 12.
  • a cover plate 36 may also be provided on the front side of the rotor main body or on both sides.
  • the gaps 38 are as narrow as possible in order not to reduce the efficiency of the turbomachine. The gaps 38 therefore do not provide access to the cavity 26 through which inspection of the cavity 26 would be possible.
  • the radially inwardly extending gap 38 may have a local enlargement, which forms the inspection opening 28.
  • the inspection opening 28 is increased relative to the gap 38 with respect to its width by a factor of at least three.
  • FIG. 2 shown detail view of the blade neck portion of the rotor 10 shows the cavity 26 and the inspection opening 28 enlarged.
  • the inspection opening 28 and the channel 30 are arranged and dimensioned so that it can be seen from the outside into the cavities 26 and thus a visual inspection can be performed.
  • inspection tools such as a lamp, light pipe or camera, may be routed through the channels 30 and the inspection openings 28 into the cavities 26.
  • the inspection openings 28 are closed by sealing elements 40.
  • the sealing elements 40 are cylindrical and made of a nickel-based material, they can also be coated, for example with a powder coating.
  • the sealing elements 40 fit against the blade necks 18 in a form-fitting manner and close off the inspection opening 28.
  • they are e.g. attached to the blade necks 18 by a press connection, positive connection, material connection or fastening means.
  • This press connection is releasable, so that the sealing elements 40 are removable from the blade necks 18, in particular to allow access to the inspection opening 28.
  • the sealing elements 40 extend over the entire axial length of the blade neck 18 and the adjacent intermediate pieces 16.
  • the arrangement of the sealing elements 40 and the cover plate 36 is coordinated so that a movement of the sealing elements 40 in the axial direction is limited by the cover plate 36.
  • the manufacture of the integrally bladed rotor 10 takes place, for example, according to the method described below.
  • the blades 14 are made in one piece, for example by a casting process.
  • the intermediate pieces 16 are connected to the blades 14 by linear friction welding, for example.
  • the blades 14 are now joined together to form a blade ring, wherein the recesses 24 each form a cavity 26 in opposite sides of adjacent blade necks 18.
  • the recesses 24 are designed so that from the radially inner side of an inspection opening 28 is formed in the cavity 26.
  • the vane ring is now connected to the rotor body 12, and the channels 30 are formed.
  • the cavities 26 of the integrally bladed rotor 10 are evaluated after the connection of the rotor base body 12 and blades 14 or blade ring via the inspection openings 28. After inspection, the sealing elements 40 are attached to the blade necks 18 and close the inspection openings 28th
  • the seal members 40 are removably attached.
  • the cover plate 36 is mounted to guide a flow of cooling fluid through the channels 30 and restrict axial movement of the seal member 40.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (16)

  1. Rotor à aubage intégré (10) pour une turbomachine, en particulier pour une turbine à gaz, où des cavités (26) sont prévues au niveau des cols d'aube (18) entre des aubes (14) contiguës, lesquelles sont formées par des évidements (24) sur des faces opposées de cols d'aube (18) contigus, où
    une ouverture d'inspection (28) s'étend radialement vers l'intérieur depuis chaque cavité (26), laquelle est accessible de l'extérieur et permet d'examiner la cavité (26) de l'extérieur, et où
    les ouvertures d'inspection (28) sont obturées par des éléments d'étanchéité (40).
  2. Rotor selon la revendication 1, caractérisé en ce que les éléments d'étanchéité (40) sont de forme cylindrique.
  3. Rotor selon la revendication 1 ou 2, caractérisé en ce que les éléments d'étanchéité (40) sont fabriqués dans un matériau à base de nickel.
  4. Rotor selon l'une des revendications 1 à 3, caractérisé en ce que les éléments d'étanchéité (40) sont revêtus.
  5. Rotor selon l'une des revendications 1 à 4, caractérisé en ce que les éléments d'étanchéité (40) sont des pièces fabriquées séparément, qui sont appliquées sur les cols d'aube (18) par assemblage à ajustement serré, à correspondance de forme et/ou par soudage.
  6. Rotor selon l'une des revendications 1 à 5, caractérisé en ce que les éléments d'étanchéité (40) sont appliqués de manière amovible sur les cols d'aube (18).
  7. Rotor selon l'une des revendications 1 à 6, caractérisé en ce que les éléments d'étanchéité (40) s'étendent sur toute la longueur axiale du col d'aube (18) correspondant.
  8. Rotor selon l'une des revendications précédentes, caractérisé en ce que chaque ouverture d'inspection (28) débouche dans un canal (30) s'étendant en direction axiale.
  9. Rotor selon la revendication 8, caractérisé en ce que le canal (30) s'étendant en direction axiale est un canal de fluide de refroidissement.
  10. Rotor selon la revendication 8 ou 9, caractérisé en ce qu'une plaque de couverture (36) est disposée en amont et/ou en aval du canal (30) dans la direction axiale.
  11. Rotor selon les revendications 9 et 10, caractérisé en ce que la plaque de couverture (36) forme un guidage pour le fluide de refroidissement.
  12. Rotor selon l'une des revendications 8 à 11, caractérisé en ce que les canaux (30) et les ouvertures d'inspection (28) sont ajustés les uns aux autres de manière à permettre de voir l'intérieur des cavités (26) depuis l'extérieur.
  13. Rotor selon l'une des revendications 8 à 12, caractérisé en ce que chaque aube (14) est soudée au corps de base (12) du rotor par l'intermédiaire d'une pièce intercalaire (16) fabriquée dans un autre matériau, et en ce que les canaux (30) sont prévus au moins entre des pièces intercalaires (16) contiguës.
  14. Rotor selon l'une des revendications précédentes, caractérisé en ce que les cols d'aube (18) présentent des saillies (32) qui forment ensemble une bande de couverture s'étendant dans la direction périphérique, la bande de couverture formant avec des rotors et des bandes de couverture contigus un interstice s'étendant dans la direction périphérique et par où passe le fluide de refroidissement.
  15. Rotor selon l'une des revendications 8 à 13 et selon la revendication 15, caractérisé en ce qu'un interstice avant dans la direction axiale et un interstice arrière sont prévus, les canaux (30) s'étendant dans la direction axiale reliant l'interstice avant à l'interstice arrière.
  16. Rotor selon l'une des revendications précédentes, caractérisé en ce que des cols d'aube (18) contigus sont séparés l'un de l'autre par une fente (38) étroite s'étendant axialement et radialement, et en ce que l'ouverture d'inspection (28) est un agrandissement local de la fente (38).
EP10713552.7A 2009-03-05 2010-02-27 Rotor à aubage intégral pour une turbomachine Not-in-force EP2404037B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200910011965 DE102009011965A1 (de) 2009-03-05 2009-03-05 Integral beschaufelter Rotor für eine Strömungsmaschine
PCT/DE2010/000222 WO2010099783A1 (fr) 2009-03-05 2010-02-27 Rotor aubagé monobloc pour turbomachine

Publications (2)

Publication Number Publication Date
EP2404037A1 EP2404037A1 (fr) 2012-01-11
EP2404037B1 true EP2404037B1 (fr) 2014-12-10

Family

ID=42270283

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10713552.7A Not-in-force EP2404037B1 (fr) 2009-03-05 2010-02-27 Rotor à aubage intégral pour une turbomachine

Country Status (3)

Country Link
EP (1) EP2404037B1 (fr)
DE (1) DE102009011965A1 (fr)
WO (1) WO2010099783A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2514923A1 (fr) 2011-04-18 2012-10-24 MTU Aero Engines GmbH Dispositif de diaphragme, corps de base de rotor à aubage intégral, procédé et turbomachine
EP2520768A1 (fr) 2011-05-02 2012-11-07 MTU Aero Engines AG Dispositif étanche pour un corps de base de rotor à aubage intégral d'une turbomachine
US9938831B2 (en) 2011-10-28 2018-04-10 United Technologies Corporation Spoked rotor for a gas turbine engine
EP2586969B1 (fr) * 2011-10-28 2020-03-25 United Technologies Corporation Rotor à disques pour un moteur à turbine à gaz

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2831958A (en) * 1955-12-01 1958-04-22 Gen Electric Bladed rotor
US3262674A (en) * 1964-05-27 1966-07-26 Chrysler Corp Turbine wheel
IT1025260B (it) * 1973-11-16 1978-08-10 Mtu Muenchen Gmbh Turbina a raffreddamento interno della corona e con posizioni prescritte di rottura
DE19801804C2 (de) * 1998-01-19 1999-10-28 Siemens Ag Turbinenschaufel sowie Verfahren zur Inspektion und/oder Reinigung einer Turbinenschaufel
DE10361882B4 (de) * 2003-12-19 2013-08-22 Rolls-Royce Deutschland Ltd & Co Kg Rotor für die Hochdruckturbine eines Flugtriebwerks
US7758311B2 (en) * 2006-10-12 2010-07-20 General Electric Company Part span shrouded fan blisk
US7887299B2 (en) * 2007-06-07 2011-02-15 Honeywell International Inc. Rotary body for turbo machinery with mistuned blades
DE102007037208B4 (de) * 2007-08-07 2013-06-20 Mtu Aero Engines Gmbh Turbinenschaufel mit zumindest einer Einsatzhülse zum Kühlen der Turbinenschaufel
US9133720B2 (en) * 2007-12-28 2015-09-15 United Technologies Corporation Integrally bladed rotor with slotted outer rim

Also Published As

Publication number Publication date
WO2010099783A1 (fr) 2010-09-10
DE102009011965A1 (de) 2010-09-09
EP2404037A1 (fr) 2012-01-11

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