EP2719864A1 - Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé - Google Patents

Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé Download PDF

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Publication number
EP2719864A1
EP2719864A1 EP12188299.7A EP12188299A EP2719864A1 EP 2719864 A1 EP2719864 A1 EP 2719864A1 EP 12188299 A EP12188299 A EP 12188299A EP 2719864 A1 EP2719864 A1 EP 2719864A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade root
intermediate piece
blade
adapter
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.)
Withdrawn
Application number
EP12188299.7A
Other languages
German (de)
English (en)
Inventor
André Dr. Werner
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
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12188299.7A priority Critical patent/EP2719864A1/fr
Publication of EP2719864A1 publication Critical patent/EP2719864A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/54—Building or constructing in particular ways by sheet metal manufacturing
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2282—Nitrides of boron
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/229—Sulfides
    • F05D2300/2291—Sulfides of molybdenum
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/509—Self lubricating materials; Solid lubricants

Definitions

  • the present invention relates to an adapter for a blade-disk connection in a rotor of a turbomachine, which is designed as a molded part and is adapted in shape to the shape of a blade root and a Schaufelfuß technique a rotor disk, so that the intermediate piece between the blade root and Schaufelfuß technique can be.
  • the invention relates to a rotor of a turbomachine, such as a gas turbine or an aircraft engine, with such an intermediate piece.
  • an intermediate piece which has at least one, preferably a plurality of depressions, in which solid lubricants are arranged.
  • the arrangement of solid lubricants in depressions prevents the lubricant from being pressed out of the contact surfaces and removed by friction. Instead, the solid lubricant is protected in the wells and can be delivered in small doses in the contact areas.
  • Suitable solid lubricants are substances such as molybdenum disulfide, graphite or hexagonal boron nitride (hBN). But other suitable solid lubricants can be used.
  • the recesses may be formed in a variety of forms, for example, as grooves, hollows, score lines, dome, blind holes or otherwise shaped recesses.
  • a plurality of depressions are arranged in rows and or columns next to one another and / or behind one another. Also, any distribution of several wells over the intermediate piece is possible.
  • the depressions can be arranged both on the inner side, with which the intermediate piece bears against the blade root, and on the outer side, which bears against the blade root receiver, or both on the inside and on the outside.
  • the recesses can be provided in each area of the intermediate piece.
  • Fig. 1 shows a side view of a blade root 1 a turbine blade, of which only the shroud is still shown.
  • the blade root 1 has a dovetail shape to be received in a correspondingly shaped receptacle of a rotor disk.
  • an intermediate piece 2 Arranged around the blade root 1 is an intermediate piece 2 according to the invention, which is formed from a shaped sheet metal part which has various sections 3 to 7.
  • two side portions 3, 4 and 6, 7 are provided on two opposite sides of the bottom portion 5, which are arranged according to the dovetail shape of the blade root 1 at an angle to each other, so that a total of a rail-like Form of the intermediate piece 2 results.
  • recesses 8, 8 ' are provided in the intermediate piece, as in the embodiments of the Fig. 2 and 3 are shown.
  • the recesses 8, 8 ' may have any suitable shape suitable for receiving a solid lubricant.
  • the solid lubricant causes a lubricant to reduce the friction between the blade root 1 and the intermediate piece 2 and between the intermediate piece 2 and the Schaufelfuß technique.
  • the friction can be permanently minimized, since only small amounts of lubricant are released from the lubricant reservoirs in the depressions 8, 8 'during the relative movement of the intermediate piece 2 with the blade root 1 or the blade root receiver.
  • the recesses 8, 8 ' may have different shapes, as in the embodiments of the Fig. 2 and 3 is shown.
  • Fig. 2 are depressions or dome-shaped recesses 8 shown, which are arranged regularly in rows and columns next to each other and behind each other on the side portion 6 of the intermediate piece 2.
  • line-shaped recesses 8 ' can be seen, which are formed in the form of score lines or grooves and are arranged in the embodiment shown in a pattern of parallel lines.
  • Both Fig. 2 and 3 only the outer sides in the side portion 6 are provided with corresponding recesses 8, 8 ', but it can of course be provided with corresponding recesses also the inner sides of the intermediate piece 2 and other portions of the intermediate piece 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12188299.7A 2012-10-12 2012-10-12 Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé Withdrawn EP2719864A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12188299.7A EP2719864A1 (fr) 2012-10-12 2012-10-12 Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12188299.7A EP2719864A1 (fr) 2012-10-12 2012-10-12 Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé

Publications (1)

Publication Number Publication Date
EP2719864A1 true EP2719864A1 (fr) 2014-04-16

Family

ID=47080311

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12188299.7A Withdrawn EP2719864A1 (fr) 2012-10-12 2012-10-12 Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé

Country Status (1)

Country Link
EP (1) EP2719864A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3418498A1 (fr) * 2017-06-22 2018-12-26 Siemens Aktiengesellschaft Segment ressort de precontrainte, rotor et procédé de fabrication associés
US10753213B2 (en) 2017-05-03 2020-08-25 MTU Aero Engines AG Wear-resistant shield for a rotating blade of a gas turbine
DE102019210699A1 (de) * 2019-07-19 2021-01-21 MTU Aero Engines AG Zwischenelement für eine Schaufel-Rotorscheiben-Verbindung bei einem Rotor einer Strömungsmaschine und Rotor für eine Strömungsmaschine
KR20210090941A (ko) * 2020-01-13 2021-07-21 한화에어로스페이스 주식회사 팬 블레이드 조립체

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07332006A (ja) * 1994-06-08 1995-12-19 Hitachi Ltd ガスタービン翼固定装置
JPH0814002A (ja) * 1994-06-30 1996-01-16 Ishikawajima Harima Heavy Ind Co Ltd タービン動翼植込部の緩衝材
EP1443180A2 (fr) * 2003-01-31 2004-08-04 General Electric Company Cale encliquetable pour aube de turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07332006A (ja) * 1994-06-08 1995-12-19 Hitachi Ltd ガスタービン翼固定装置
JPH0814002A (ja) * 1994-06-30 1996-01-16 Ishikawajima Harima Heavy Ind Co Ltd タービン動翼植込部の緩衝材
EP1443180A2 (fr) * 2003-01-31 2004-08-04 General Electric Company Cale encliquetable pour aube de turbine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10753213B2 (en) 2017-05-03 2020-08-25 MTU Aero Engines AG Wear-resistant shield for a rotating blade of a gas turbine
EP3418498A1 (fr) * 2017-06-22 2018-12-26 Siemens Aktiengesellschaft Segment ressort de precontrainte, rotor et procédé de fabrication associés
DE102019210699A1 (de) * 2019-07-19 2021-01-21 MTU Aero Engines AG Zwischenelement für eine Schaufel-Rotorscheiben-Verbindung bei einem Rotor einer Strömungsmaschine und Rotor für eine Strömungsmaschine
WO2021013280A1 (fr) * 2019-07-19 2021-01-28 MTU Aero Engines AG Élément intermédiaire pour une liaison aube-disque de rotor dans un rotor d'une turbomachine, rotor associé pour une turbomachine et turbomachine
US11905852B2 (en) 2019-07-19 2024-02-20 MTU Aero Engines AG Intermediate element for a blade/rotor disc connection in a rotor of a turbomachine, associated rotor for a turbomachine, and turbomachine
KR20210090941A (ko) * 2020-01-13 2021-07-21 한화에어로스페이스 주식회사 팬 블레이드 조립체

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