EP1706589A1 - Rotor a renfort de fibres pour turbogenerateur - Google Patents

Rotor a renfort de fibres pour turbogenerateur

Info

Publication number
EP1706589A1
EP1706589A1 EP04802782A EP04802782A EP1706589A1 EP 1706589 A1 EP1706589 A1 EP 1706589A1 EP 04802782 A EP04802782 A EP 04802782A EP 04802782 A EP04802782 A EP 04802782A EP 1706589 A1 EP1706589 A1 EP 1706589A1
Authority
EP
European Patent Office
Prior art keywords
rotor
fiber
blades
blade
rotor according
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Withdrawn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
EP04802782A
Other languages
German (de)
English (en)
Inventor
Erwin Bayer
Bertram Kopperger
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 GmbH
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 GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1706589A1 publication Critical patent/EP1706589A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/028—Blade-carrying members, e.g. rotors the rotor disc being formed of sheet laminae
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C2204/00—End product comprising different layers, coatings or parts of cermet
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments
    • 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
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/702—Reinforcement
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a rotor for a turbomachine, in particular for a gas turbine, according to the preamble of patent claim 1.
  • the integrally bladed rotors are called BLISK (BJaded Disk) or BLING (Biaded Ring) depending on whether there is a disk-shaped or an annular rotor base body.
  • BLISK BJaded Disk
  • BLING Bit Ring
  • the blades are firmly connected to the ring-shaped or disk-shaped rotor base body and are therefore an integral part of the rotor base body.
  • the manufacture of such integrally bladed rotors is complex and can be done, for example, by milling from the solid on a 5-axis milling machine.
  • a disadvantage of integrally bladed rotors in BLING design or BLISK design is the poor possibility of repairing the same.
  • Rotors in which the blades are inserted into the basic rotor body via blade feet are easier to manufacture and easier to repair than integrally bladed rotors, but they are significantly more difficult compared to integrally bladed rotors, since the connection of the moving blades to the basic rotor body via the blade feet is strong due to centrifugal forces is claimed and must therefore be carried out constructively safely.
  • the rotor base body is designed in the form of a disk.
  • the present invention is based on the problem of proposing a novel rotor for a turbomachine, in particular for a gas turbine.
  • the rotor base body is formed by at least one ring-shaped element made of a metal matrix composite material (MMC material), the rotor blades being connected to the rotor base body by means of blade feet in such a way that the blade feet are positioned in a fiber-free area of the rotor base body.
  • MMC material metal matrix composite material
  • a rotor for a turbomachine which, on the one hand, has a preferably low weight and, on the other hand, can be easily manufactured and repaired.
  • the basic rotor body is formed from at least one ring-shaped element made of a metal matrix composite material.
  • the execution of the basic rotor body as at least one ring-shaped element and the execution of the same in MMC technology allow a significant weight reduction compared to the rotors known from the prior art.
  • individual rotor blades can be easily replaced when repairing the rotor.
  • the basic rotor body is formed from two annular elements made of a metal matrix composite material (MMC material), the rotor blades being fastened to the radially outer end between the two annular elements.
  • Blade feet of the rotor blades engage in a corresponding depression or recess in the area of the ring-shaped elements, specifically between fiber-reinforced areas of the two ring-shaped elements.
  • Each of the blades is preferably positioned with a platform between radially outer circumferential projections of the two annular elements, ends of the platforms abutting the circumferential projections.
  • the rotor base body is formed from an annular element made of a metal matrix composite (MMC material), axially outer portions of the annular element being fiber-reinforced and an intermediate portion being fiber-free, and the blade roots of the rotor blades being fiber-free Section are attached. Bores extending in the radial direction are preferably made in the fiber-free section of the ring-shaped element, each rotor blade being anchored in a bore with a blade root.
  • MMC material metal matrix composite
  • Figure 1 shows a section of a rotor according to the invention according to a first embodiment of the invention in a schematic, perspective side view.
  • FIG. 2 shows an enlarged detail of the rotor according to FIG. 1;
  • FIG. 3 shows the rotor according to FIG. 1 in an exploded view
  • Fig. 4 shows a detail of a rotor according to the invention according to a second embodiment of the invention in a schematic, perspective side view.
  • FIGS. 1 to 3 show a rotor 10 according to the invention for a turbomachine, in particular for a gas turbine, in different representations.
  • 1 shows a section from the rotor 10 in a perspective side view, FIG. 1 showing approximately a 90 ° section or a quarter circle section from the rotor 10, which is closed per se.
  • FIG. 2 shows an enlarged detail of the rotor 10 in the area of two rotor blades
  • FIG. 3 shows an exploded view of the rotor 10.
  • the rotor 10 is preferably used in a turbine or a compressor of an aircraft engine.
  • the rotor 10 according to FIGS. 1 to 3 has a rotor base body 11 and a plurality of rotor blades 12 distributed over the circumference of the rotor base body 11.
  • the rotor base body 11 consists of at least one annular element from one Metal matrix composite material is formed, and that the blades 12 are connected to the rotor base body via blade feet in such a way that the blade feet are positioned in a fiber-free region of the rotor base body 11.
  • the basic rotor body 11 is formed from two ring-shaped elements 13 and 14, both ring-shaped elements 13 and 14 being formed from a metal matrix composite material.
  • FIGS. 2 and 3 schematically show the tensile fibers 15 integrated into the metal matrix material of the annular elements 13 and 14.
  • each of the two ring-shaped elements 13 and 14 has a corresponding region 16 and 17, in which the tensile fibers 15 run, that is to say they are fiber-reinforced.
  • the blades 12 are attached to the radially outer end of the rotor base body 12 between the two annular elements 13 and 14, each of the blades 12 being positioned with a blade root 18 between the fiber-reinforced regions 16 and 17 of the two annular elements 13 and 14.
  • a depression or recess 19 is made in each of the two annular elements 13 and 14, into which the blade feet 18 engage when the rotor 10 is assembled.
  • the inner contour of the recesses 19 is accordingly adapted to the outer contour of the blade feet 18.
  • a platform 20 of the rotor blades 12 adjoins the blade root 18 of the rotor blades 12, with axially outer ends of the platforms 20 on radially outer circumferential projections 28 of the two annular elements 13 in the assembled state of the rotor 10 and 1 concern.
  • the platforms 20 of the rotor blades 12 accordingly close flush with the projections 38 of the ring-shaped elements at the radially outer end of the ring-shaped elements 13 and 14. from elements 13 and 14. Starting from the platforms 20, the blades 21 of the blades 12 extend radially outward.
  • the two annular elements 13 and 14 of the basic rotor body 11 are connected to one another at radially inner sections 22 and 23, respectively.
  • the radially inner sections 22 and 23, on which the annular elements 13 and 14 are connected to one another, are designed to be fiber-free. In these radially inner sections 22 and
  • FIG. 4 shows a second exemplary embodiment of a rotor 26 according to the invention.
  • the rotor 26 of the exemplary embodiment in FIG. 4 also has a rotor base body 27, as well as a plurality of rotor blades 28 distributed over the circumference of the rotor base body 27.
  • annular element 29 is formed, the annular element 29 being formed from a metal matrix composite material.
  • the annular element 29 of the exemplary embodiment in FIG. 4 has a fiber-reinforced region 30 and 31, respectively, on axially outer sections, FIG. 4 schematically showing the tensile fibers 32 that run within the fiber-reinforced regions 30 and 31.
  • the ring-shaped element 29 In an axially inner section, that is between the two regions 30 and 31, the ring-shaped element 29 has a fiber-free section 33.
  • the rotor blades 28 are fastened to the ring-shaped element 29 of the basic rotor body 27 with blade feet 34.
  • bores 35 running in the radial direction are made in the fiber-free section 33 of the annular element 29.
  • the rotor blades 28 can be inserted into the bores 35 from a radially inner side, wherein according to FIG. 4 a rotor blade 28 can be inserted into a bore 35 starting with the airfoil 36. The rotor blade 28 is then pushed radially outward until the blade root 34 of the rotor blade 28 comes to rest against a stop 37 integrated into the bore 35. The stop 37 accordingly limits the outward, radial displaceability of the blades 28 within the bores 35.
  • the blades 36 inserted into the bores 35 are held in this position by a retaining ring (not shown).
  • the retaining ring bears against the radially inner end of the bores 35 over the entire circumference of the annular element 29 and presses radially outward, so that the moving blades 28 are rigidly and gas-tightly connected to the annular element 29.
  • the tensile fibers 32 in the area of the bores 35 can be placed around the bores 35 in a sinusoidal or cosine shape.
  • the two exemplary embodiments have in common that at least one ring-shaped element made of a metal matrix composite material is used as the basic rotor body.
  • the or each annular element of the basic rotor body has at least one fiber-reinforced section or area and at least one fiber-free area, blade roots of rotor blades running in the fiber-free area of the or each annular element.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention a trait à un rotor pour un turbogénérateur comportant un corps de base de rotor (11) et une pluralité d'aubes (12) qui sont réparties autour de la périphérie dudit corps (11). Le corps de base de rotor (11) est constitué à partir d'au moins un élément annulaire (13, 14) réalisé en un matériau à matrice composite. Selon l'invention, les aubes (12) sont reliées au corps de base de rotor (11) par des talons d'aubes (18) de sorte que les talons d'aubes sont positionnées dans une zone du corps de base de rotor exempte de fibres.
EP04802782A 2003-12-13 2004-11-20 Rotor a renfort de fibres pour turbogenerateur Withdrawn EP1706589A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10358421A DE10358421A1 (de) 2003-12-13 2003-12-13 Rotor für eine Turbomaschine
PCT/DE2004/002571 WO2005056983A1 (fr) 2003-12-13 2004-11-20 Rotor a renfort de fibres pour turbogenerateur

Publications (1)

Publication Number Publication Date
EP1706589A1 true EP1706589A1 (fr) 2006-10-04

Family

ID=34638662

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04802782A Withdrawn EP1706589A1 (fr) 2003-12-13 2004-11-20 Rotor a renfort de fibres pour turbogenerateur

Country Status (4)

Country Link
US (1) US8123487B2 (fr)
EP (1) EP1706589A1 (fr)
DE (1) DE10358421A1 (fr)
WO (1) WO2005056983A1 (fr)

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US7766623B2 (en) * 2006-11-08 2010-08-03 General Electric Company System for manufacturing a rotor having an MMC ring component and an airfoil component having monolithic airfoils
US7775772B2 (en) * 2006-11-08 2010-08-17 General Electric Company System for manufacturing a rotor having an MMC ring component and an airfoil component having MMC airfoils
US7784182B2 (en) * 2006-11-08 2010-08-31 General Electric Company System for manufacturing a rotor having an MMC ring component and a unitary airfoil component
US8251651B2 (en) * 2009-01-28 2012-08-28 United Technologies Corporation Segmented ceramic matrix composite turbine airfoil component
RU2571680C2 (ru) * 2009-07-28 2015-12-20 Снекма Балка подвески турбинного двигателя к конструкции летательного аппарата
US10280768B2 (en) 2014-11-12 2019-05-07 Rolls-Royce North American Technologies Inc. Turbine blisk including ceramic matrix composite blades and methods of manufacture
US10370971B2 (en) 2014-11-17 2019-08-06 United Technologies Corporation Reinforced gas turbine engine rotor disk
US10648481B2 (en) * 2014-11-17 2020-05-12 United Technologies Corporation Fiber reinforced spacer for a gas turbine engine
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DE102016219818A1 (de) * 2016-10-12 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Laufschaufelbaugruppe mit ringsegment- oder scheibensegmentförmigem Schaufelträger und radial innenliegender Versteifungsstruktur
US10294954B2 (en) 2016-11-09 2019-05-21 Rolls-Royce North American Technologies Inc. Composite blisk
US10563665B2 (en) 2017-01-30 2020-02-18 Rolls-Royce North American Technologies, Inc. Turbomachine stage and method of making same
US11268389B2 (en) 2018-05-14 2022-03-08 Rolls-Royce North American Technologies Inc. Blisk bonded CMC airfoil having attachment
US10787916B2 (en) 2018-06-22 2020-09-29 Rolls-Royce Corporation Turbine wheel assembly with ceramic matrix composite components
US10934863B2 (en) 2018-11-13 2021-03-02 Rolls-Royce Corporation Turbine wheel assembly with circumferential blade attachment

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Also Published As

Publication number Publication date
WO2005056983A1 (fr) 2005-06-23
US8123487B2 (en) 2012-02-28
DE10358421A1 (de) 2005-07-07
US20080025844A1 (en) 2008-01-31

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