WO2010099784A1 - Rotor à aubage intégral et procédé de fabrication d'un rotor à aubage intégral - Google Patents

Rotor à aubage intégral et procédé de fabrication d'un rotor à aubage intégral Download PDF

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Publication number
WO2010099784A1
WO2010099784A1 PCT/DE2010/000223 DE2010000223W WO2010099784A1 WO 2010099784 A1 WO2010099784 A1 WO 2010099784A1 DE 2010000223 W DE2010000223 W DE 2010000223W WO 2010099784 A1 WO2010099784 A1 WO 2010099784A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
sealing
discharge opening
rotor according
sealing elements
Prior art date
Application number
PCT/DE2010/000223
Other languages
German (de)
English (en)
Inventor
Alexander Böck
Jens Wittmer
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
Priority to ES10713553.5T priority Critical patent/ES2525743T3/es
Priority to EP10713553.5A priority patent/EP2404038B1/fr
Publication of WO2010099784A1 publication Critical patent/WO2010099784A1/fr

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
    • F01D5/34—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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the invention relates to an integrally bladed rotor for a turbomachine, in particular for a gas turbine, and to a method for producing an integrally bladed rotor.
  • Gas turbine rotors with integral blading are referred to as 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 rotor body).
  • Blisk is the short form of Bladed Disk and Bling of Bladed Ring.
  • the object of the invention is to provide an integrally bladed rotor, in which a seal of the discharge openings is realized inexpensively and with low weight, and a simple manufacturing method of such integrally bladed rotor.
  • the object is achieved by an integrally bladed rotor according to the invention for a turbomachine, in particular for a gas turbine.
  • the rotor comprises a rotor base body, extending in the radial edge region in the axial direction Relief openings are provided.
  • a sealing element is provided, which seals the discharge opening in the axial direction. In this way, no separate sealing rings or washers are needed, whereby weight is saved. Since a sealing element is associated with only one relief opening, the construction of the sealing elements is simplified, whereby costs are saved.
  • the sealing elements have a stop, with which they bear against an end face of the rotor. In this way, a simple positioning of the sealing elements and a simple attachment to the rotor are made possible.
  • the sealing elements may have at least one bending extension, which bears against an end face of the rotor.
  • the sealing elements are fixed by bending the bending extension on the rotor.
  • the sealing elements are located as dampers between adjacent blade necks. This allows for improved damping of vibrations of the rotor.
  • the sealing elements each have a sealing plate which is adapted to the cross section of the discharge opening.
  • the sealing plate allows optimal sealing of the discharge opening.
  • the sealing plate can be designed so that the thickness of the sealing plate by at least a factor of 5 is less than the length of the discharge opening. This allows a further saving of weight in the radial edge region of the rotor main body.
  • the sealing plate is located in the discharge opening. In this way, the sealing plate takes no additional space to complete.
  • the sealing plate is provided, for example, in the axial direction substantially in the middle of the discharge opening.
  • the seal of the discharge opening is maintained even with small displacements of the sealing plate in the axial direction.
  • the sealing elements each have two sealing plates.
  • the two sealing plates of the sealing elements are arranged so that they form a plane at the two ends of the discharge opening with the end faces of the rotor in the region of the discharge openings, ie finish flush. In this way, only slight ventilation losses occur in the region of the discharge openings during rotation of the rotor.
  • sealing elements are provided with different masses. This allows a balancing of the rotor by means of the sealing elements.
  • the sealing elements preferably have a radially outer web which has at least one sealing plate protruding from the web and stops at both ends of the web, wherein the stops preferably act on the end faces of the rotor. In this way, the sealing element is attached via the two stops at the ends on the end faces of the rotor, whereby slipping of the sealing plate is prevented.
  • These attacks are z. B. a permanent extension and a bending extension.
  • the invention further relates to a method for producing an integrally bladed rotor with the following method steps.
  • a first step the attachment of blades takes place on a rotor body, wherein in the radial edge region of the rotor body discharge openings are provided, which lie in the region of slots of adjacent blade necks.
  • the relief openings are closed by sealing elements. This allows a simple production of the rotor, which can be dispensed with elaborately manufactured and heavy sealing rings or washers, whereby weight and cost can be saved.
  • the balancing of the rotor takes place by means of differently heavy sealing elements. This makes it possible to perform the sealing of the discharge openings and the balancing of the rotor in one method step.
  • Figure 1 is a perspective view of an integrally bladed rotor according to a first embodiment of the invention
  • Figure 2 is a detail view of a sealing element according to the embodiment shown in Figure 1;
  • Figure 3 is a plan view of the end face of the rotor shown in Figure 1;
  • Figure 4 is a sectional view taken along the section plane IV-IV shown in Figure 3;
  • Figure 5 is a perspective view of an integrally bladed rotor according to a second embodiment of the invention.
  • Figure 6 is a detail view of a sealing element according to the embodiment shown in Figure 5;
  • Figure 7 is a plan view of the end face of the rotor shown in Figure 5.
  • FIG. 8 shows a sectional view along the sectional plane VIII-VIII shown in FIG.
  • An integrally bladed 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 connected in the embodiment shown via separate intermediate pieces 16 with the rotor base body 12.
  • 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 airfoil 20, an outer shroud 22 is provided.
  • the blades 14 are made, for example, from single-crystalline nickel-based materials that do not allow fusion welding. Such a blade 14 is first connected by friction welding, in particular linear friction welding, with an intermediate piece 16.
  • 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 via the intermediate piece 16 by means of various methods on the rotor body 12. Of course, it is also possible for the blades 14 to be fastened directly to the rotor base body 12 by suitable methods.
  • a lightweight construction for the blade neck 18 is provided. Recesses 24 are provided in the blade necks 18 on the sides lying in the circumferential direction (cf., FIG. 1 and FIG. 4). Between adjacent blade necks 18 cavities 18 are formed by the recesses 24 in opposite sides of the blade necks.
  • the blade necks 18 each have a front and rear extension in the axial direction.
  • the extensions together form a running in the circumferential direction inner shroud 26th
  • relief openings 28 are provided in the radially outer edge region of the rotor base body 12 extending in the axial direction.
  • the relief openings 28 are used, for example, to reduce stresses in the rotor base body 12 due to thermal stresses by hot gases that are passed through the turbomachine.
  • a sealing element 30 is provided in each case, which seals the discharge opening 28 in the axial direction.
  • FIG. 2 shows a detailed view of one of the sealing elements 30 according to a first embodiment of the invention.
  • the sealing element 30 has a radially outer web 32. At the left end of the web 32, a thickening is provided, which forms a first stop 34, which bears against a first end face 36 of the rotor 10 (cf., FIG. 1 or FIG.
  • a bending extension 38 is formed on the right end of the web 32.
  • the bending extension 38 is bent after insertion of the sealing element 30 in the discharge opening 28 of the rotor 10 by about 90 ° upwards, so that it rests with its upper surface on the second end face 36 of the rotor 10. It is of course also possible to arrange one or more bending extensions 38 on the sealing element 30 in such a way that they can be bent in different directions, for example laterally, in the bent state.
  • a sealing plate 40 projects from the web 32 downwards.
  • the shape of the sealing plate 40 is adapted to the cross section of the discharge opening 28 in order to achieve an optimal seal.
  • the sealing plate 40 is arranged substantially in the middle of the radially outer web 32 and is thus arranged in the mounted state within the discharge opening 28 more precisely in the axial direction substantially in the middle of the discharge opening 28.
  • the thickness of the sealing plate 40 is at least a factor of 5 less than the length of the discharge opening 28 in the axial direction. In this way, 28 material is saved in the region of the discharge opening, whereby the weight of the rotor 10 is reduced.
  • the relief opening 28 is chosen to be as large as possible without impairing the stability of the rotor 10.
  • the sealing element 30 is arranged so that it abuts against the first stop 34 on the first end face 36 and with a second stop, which is formed by the bent bending extension 38, on the second end face 36 of the rotor 10, whereby a movement of the sealing element 30 in the axial direction is prevented (see Figure 4).
  • the radially outer web 32 of the sealing element 30 is a damper between adjacent blade necks 18.
  • the damper is used in particular for reducing vibrations of the blades 14.
  • An option to achieve the damping effect is that the Top of the web 32 rests against the top of the discharge opening 28 and is absorbed by friction kinetic energy.
  • the various sealing elements 30, which are each associated with a discharge opening 28, may have different masses, whereby a balancing of the rotor 10 by means of the sealing elements 30 is made possible.
  • the sealing elements 30 thereby additionally serve as balancing masses.
  • FIGs 5 to 8 show a second embodiment of the invention.
  • the construction of rotor body 12 and blades 14 are identical to the first embodiment shown in Figures 1 to 4.
  • the second embodiment differs from the first embodiment by an altered sealing element 30.
  • Figure 6 shows a detailed view of the sealing element 30 of the second embodiment of the rotor 10.
  • two sealing plates 40 are attached, which are each adapted to the cross section of the discharge opening 28.
  • a first stop 34 and a bending extension 38 are provided analogously to the first embodiment.
  • the arrangement of the sealing elements 30 in the mounted state in the rotor 10 can be seen particularly well in FIG.
  • the sealing element 30 rests with the first stop 34 on the left end side 36 of the rotor 10 and with the bent bending extension 38, which forms a second stop, on the right end face 36 of the rotor 10 at.
  • the two sealing plates 40 of the sealing elements 30 are arranged so that they form a plane at the two ends of the discharge opening 28 with the end faces 36 of the rotor 10 and terminate flush. In this way, only slight flow losses through the sealing elements 30 result upon rotation of the rotor 10.
  • the bending extensions 38 are bent by approximately 180 ° and lie with their end face against the end face 36 of the rotor 10.
  • the bending extensions 38 analogously to the first embodiment (cf., FIG. 4) by only about 90 °, so that the bending extensions 38 lie with their upper surface against the end face 36 of the rotor 10.
  • the bending extensions 38 of the first embodiment can be bent by approximately 180 ° analogously to the second embodiment. It is also conceivable to bend a plurality of bending extensions 38 in different directions.
  • a method of manufacturing an integrally bladed rotor 10 according to the present invention will be described.
  • the blades 14 are fastened to a rotor base body 12. This can be done by various methods, in particular using an intermediate piece 16 to facilitate welding processes.
  • relief openings 28 are provided which lie in the region of slots of adjacent blade necks 18. The discharge openings 28 can thereby arise, for example, in the attachment of individual blades 14 on the rotor base body 12, process-related, or they can after mounting the blades 14 on the rotor body 12, for example by drilling or milling, arise.
  • the relief openings 28 are closed and sealed by the sealing elements 30.
  • the sealing elements 30 are introduced with the bending extension 38 ahead in the discharge openings 28 until the first stop 34 bears against the end face 36 of the rotor 10.
  • the bending extension 38 which protrudes on the other side of the rotor 10 from the discharge opening 28, bent upwards until it rests against the end face 36 of the rotor 10 and thus forms a second stop, whereby the sealing element 30 fixed in the discharge opening 28th is held.
  • the mass of the respective sealing elements 30 is adjusted so that simultaneously with the sealing of the discharge openings 28, a balancing of the rotor 10 takes place.
  • a bending extension 38 is provided instead of the first stop 34 in the form of a thickening of the sealing element 30 on both sides of the sealing element 30, wherein during the assembly of the sealing element 30, the bending extensions 38 are bent on both sides of the sealing element and in each case abut against the end face 36 of the rotor 10 and form a stop.
  • Such a sealing element 30 is formed symmetrically, for example, whereby the orientation of the sealing element 30 during assembly does not have to be considered.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un rotor à aubage intégral (10) destiné à une turbomachine, notamment à une turbine à gaz, comportant un corps de base de rotor (12) dont la partie marginale radiale comprend des ouvertures de délestage (28) s'étendant dans la direction axiale. Chaque ouverture de délestage (28) contient un élément d'étanchéité (30) étanchant l'ouverture de délestage (28) dans la direction radiale.
PCT/DE2010/000223 2009-03-05 2010-02-27 Rotor à aubage intégral et procédé de fabrication d'un rotor à aubage intégral WO2010099784A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
ES10713553.5T ES2525743T3 (es) 2009-03-05 2010-02-27 Rotor de álabe integral y método para fabricar un rotor de álabe integral
EP10713553.5A EP2404038B1 (fr) 2009-03-05 2010-02-27 Rotor à aubage intégral et procede de fabrication d'un rotor à aubage intégral

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009011879.9 2009-03-05
DE200910011879 DE102009011879A1 (de) 2009-03-05 2009-03-05 Integral beschaufelter Rotor und Verfahren zur Herstellung eines integral beschaufelten Rotors

Publications (1)

Publication Number Publication Date
WO2010099784A1 true WO2010099784A1 (fr) 2010-09-10

Family

ID=42272549

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2010/000223 WO2010099784A1 (fr) 2009-03-05 2010-02-27 Rotor à aubage intégral et procédé de fabrication d'un rotor à aubage intégral

Country Status (4)

Country Link
EP (1) EP2404038B1 (fr)
DE (1) DE102009011879A1 (fr)
ES (1) ES2525743T3 (fr)
WO (1) WO2010099784A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012149925A3 (fr) * 2011-05-02 2013-02-28 Mtu Aero Engines Gmbh Dispositif de recouvrement, corps de base de rotor intégralement à aubage, procédé et turbomachine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010053123A1 (de) 2010-12-01 2012-06-06 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines Wuchtgewichtes, Wuchtgewicht und Rotorgrundkörper
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
US11111804B2 (en) 2019-03-11 2021-09-07 Raytheon Technologies Corporation Inserts for slotted integrally bladed rotor

Citations (2)

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Publication number Priority date Publication date Assignee Title
US3262675A (en) 1964-05-27 1966-07-26 Chrysler Corp Turbine wheel
US4872810A (en) 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system

Family Cites Families (9)

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Publication number Priority date Publication date Assignee Title
US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
CH494896A (de) * 1968-08-09 1970-08-15 Sulzer Ag Halterung von Laufschaufeln im Rotor einer Turbomaschine
BE791375A (fr) * 1971-12-02 1973-03-01 Gen Electric Deflecteur et amortisseur pour ailettes de turbomachines
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
US5313786A (en) * 1992-11-24 1994-05-24 United Technologies Corporation Gas turbine blade damper
US5518369A (en) * 1994-12-15 1996-05-21 Pratt & Whitney Canada Inc. Gas turbine blade retention
EP1916382A1 (fr) * 2006-10-25 2008-04-30 Siemens AG Dispositif et procédé pour sécuriser un élément d'étanchéité sur un rotor
EP1944472A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'un rotor de turbine, élément d'étanchéité pour un rotor équipé d'aubes de rotor d'une turbine et rotor de turbine
US8425194B2 (en) * 2007-07-19 2013-04-23 General Electric Company Clamped plate seal

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3262675A (en) 1964-05-27 1966-07-26 Chrysler Corp Turbine wheel
US4872810A (en) 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012149925A3 (fr) * 2011-05-02 2013-02-28 Mtu Aero Engines Gmbh Dispositif de recouvrement, corps de base de rotor intégralement à aubage, procédé et turbomachine

Also Published As

Publication number Publication date
EP2404038A1 (fr) 2012-01-11
ES2525743T3 (es) 2014-12-29
EP2404038B1 (fr) 2014-10-08
DE102009011879A1 (de) 2010-09-16

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