WO2011054342A1 - Disque aubagé monobloc, turbine à gaz et procédé de fabrication d'un tel disque aubagé monobloc - Google Patents

Disque aubagé monobloc, turbine à gaz et procédé de fabrication d'un tel disque aubagé monobloc Download PDF

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Publication number
WO2011054342A1
WO2011054342A1 PCT/DE2010/001280 DE2010001280W WO2011054342A1 WO 2011054342 A1 WO2011054342 A1 WO 2011054342A1 DE 2010001280 W DE2010001280 W DE 2010001280W WO 2011054342 A1 WO2011054342 A1 WO 2011054342A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade segments
blisk
gas turbine
rotor disk
rotor
Prior art date
Application number
PCT/DE2010/001280
Other languages
German (de)
English (en)
Inventor
Thomas Uihlein
Erich Steinhardt
Jürgen Kraus
Frank Stiehler
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 WO2011054342A1 publication Critical patent/WO2011054342A1/fr

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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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses

Definitions

  • the invention relates to a blisk for a gas turbine according to the preamble of patent claim 1, a method for producing such a blisk and a gas turbine according to the preamble of patent claim 12.
  • blisk stands for "bladed disk” and is generally used for an integrally bladed rotor disk
  • vanes or vanes joined together to form vane segments are not positively and non-positively connected to the rotor but also attached integrally to the rotor disk as shown, for example, in U.S. Patent US 7,431,564 B2
  • the blades may also be integrally formed with the rotor disk, however, the rotor disk and the blade segments shown separately in the U.S. Patent the advantage that they consist of a different material and may have different structural states than the rotor disk, so that the material properties of the blades or blade segments can be adjusted specifically to the respective requirements.
  • the object of the present invention is to provide a blisk for a gas turbine, which eliminates the aforementioned disadvantages and is easy to produce in terms of production, to provide a method for producing such a blisk as well as a gas turbine with an improved rotor.
  • a blisk according to the invention for a gas turbine in particular for an aircraft gas turbine, has a multiplicity of blades, which are combined to form vane segments arranged in a row.
  • the blade segments each have a foot, via which they are materially connected to a rotor disk.
  • at least one respective cavity or chamber is formed between the feet of adjacent blade segments.
  • the vane segments are joined to sockets of the rotor disc. This has the advantage that the respective position of the blade segments is predetermined, so that complex adjustments can be omitted in the connection of the blade segments on the rotor disk.
  • damping elements for influencing the vibration behavior of the blade segments are arranged in the cavities in one embodiment.
  • the shrouds may also define a gap between them and thus be laterally spaced from each other.
  • the blade segments are preferably made hollow, so that the blade segments are also cooled from the inside.
  • An exemplary vane segment includes at least two individual vanes.
  • cast blade segments it is advantageous if at least three individual blades to a Blade segment are joined together, since then a high pouring rate can be achieved by casting.
  • more than three individual blades can be connected to a blade segment.
  • the manufacturing costs are reduced exponentially with the number of integrated individual blades.
  • the rotor disk and the blade segments are produced separately from one another. Subsequently, the blade segments in the region of their feet on the outer circumference of the rotor disc cohesively or otherwise integrally added, wherein between the feet of adjacent blade segments at least one cavity is formed in each case.
  • the method according to the invention has the particular advantage that the production costs are significantly reduced compared to the known production methods. For example, blade root and shroud loops and the number of joints required are reduced. In addition, the production is facilitated by the fact that the available space per blade foot is increased. Furthermore, a higher rigidity of the blade segments is achieved than with individual blades.
  • the joining of the blade segments to the rotor disk preferably takes place by friction welding, inductive high-frequency pressure welding or hot isostatic pressing.
  • the blade segments can be grouted to bases of the rotor disks, which are executed directly in the formation of the rotor disk with or subsequently formed in a preparation of a rotor disk-side joining surface.
  • the geometry of the joining surface depends, among other things, on the joining method to be used.
  • the joining surface is preferably flat, for example, during friction welding. However, it can also be curved or have a different course.
  • the base cuboid, cylindrical and drgl. Are executed.
  • the blade segments are preferably cast. However, they can also be forged or generatively produced, for example. The type of production depends, among other things, on the position in the turbine. Thus, blade segments for the turbine side are preferred as castings and blade segments for the
  • a gas turbine according to the invention in particular an aircraft gas turbine, has a rotor which is composed of a multiplicity of rotor disks.
  • Each rotor disk has a multiplicity of blades, which are combined to form blade segments arranged in a row and connected in a material-locking manner to the rotor disk.
  • the blades are spaced apart from one another on the foot side, so that a multiplicity of cavities extending in the axial direction is formed.
  • the cavities are connected to a cooling system so that the rotor disk can be cooled on the outer peripheral side and the blade segments on the foot side.
  • the temperature gradients are specifically adjustable, in particular in the foot region of the blade segments, which has a direct effect on the radial length of the joint zone.
  • the present invention also relates to and comprises integrally bladed rotor rings, so-called bling or “bladed rings.”
  • bling integrally bladed rotor rings
  • the terms “blisk” and “bling” are treated synonymously and as synonymous in the context of the present invention not limited to the turbine side of a gas turbine, but also extends to the compressor side.
  • FIGURE shows a section of a blisk according to the invention.
  • a turbine blisk 2 according to the invention for a gas turbine has a rotor disk 4 and a multiplicity of blade segments 6, which are fastened on the outer circumference of the rotor disk 4 and arranged in a row of blades.
  • the rotor disk 4 is for example a forged part or produced by powder metallurgy and has on the outer circumference a plurality of integral and cuboidal bases 8.
  • the base 8 are spaced apart in the circumferential direction and each have a flat joining surface 10 on the circumference. However, the joining surface 10 may also be curved.
  • the blade segments 6 are castings, on the compressor side also forged parts, and each have two blades 12, which are arranged between an inner shroud 14 and an outer shroud 16. They are each hollow with two oppositely oriented side core exits 18.
  • the blade segments 6 each have an approximately cuboid base 20 with a plane facing away from the blades 12 flat connecting surface 22, with which they cohesively on the respective joining surface 10 of the base 8, in particular by means a friction welding process, are connected.
  • the cross section of the connecting surface 22 preferably corresponds to the cross section of the joining surface 10, wherein the feet 20 are tapered in the direction of their respective connecting surface 22.
  • a cavity or a chamber 24 is formed, which is delimited in the radial direction by a circumferential surface section 26 of the rotor disk 4 and by shroud surface sections 28, 30 of the inner cover strips 14.
  • the feet 20 with the sockets 8 each have two opposite side surfaces 32, 34.
  • the side surfaces 32, 34 are planar and extend radially to the rotor disk 4, so that they are employed accordingly and the cavities 24 of the peripheral surface portion 26 in the direction of Shroud surface portions 28, 30 are extended. They open the rotor disk side via a rounded transition region 36 in the peripheral surface portion 26 which is concave.
  • Inside cover band side open the side surfaces 32, 34 in the shroud surface portions 28, 30.
  • the shroud surface portions 28, 30 are also concave, but they have a stronger curvature than that
  • the cavities 24 are connected on the foot side with a cooling system for cooling the blade segments 6 and on the outer peripheral side for cooling the rotor disk 4.
  • Damping elements or inserts arranged, for example, as material thickening in Foot area or in the cavity-side transition region may be formed by the feet 20 to the inner shroud 14.
  • the inner cover strips 14 are slightly spaced apart in the region of their lateral wedge surfaces 38, so that a fluidically favorable closed or virtually closed inner side inner band surface 40 is provided.
  • the outer shrouds 16 are based at least during operation due to the thermal expansion of the blade segments 6 with their contact surfaces 42 against each other, wherein to achieve a positive connection and thus improve the support effect their contact surfaces 42, for example, Z-shaped formed. However, they can also be double-Z-shaped and similar.
  • the rotor disk 4 and the blade segments 6 are produced separately from one another.
  • the rotor disk 4 is a forged part, but it can also be produced by a generative manufacturing method.
  • the pedestals 8 can be formed on the outer circumference of the rotor disk 4 via a generative manufacturing process.
  • the blade segments 6 are preferably castings and have at least two blades 12 at a time. After the separate production of the rotor disk 4 and the blade segments 6, these are added via their foot-side connecting surfaces 22 to the socket-side joining surfaces 10 of the rotor disk 4 by a friction welding process. In this case, a cavity 24 is formed between adjacent legs 20 due to the spacing between the base 8 and the same cross-sections of the base 8 and the feet 20.
  • the blade segments 6 can also be connected to the rotor disk 4 by high-frequency induction-pressure welding (IHFP) or hot isostatic pressing (HIP) and the like.
  • IHFP high-frequency induction-pressure welding
  • HIP hot isostatic pressing

Landscapes

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

Abstract

L'invention concerne un disque aubagé monobloc (2) pour une turbine à gaz, le disque comportant une pluralité de segments d'aube (6) présentant une pluralité de pales (12) et respectivement un pied (20) destiné à être fixé au disque de rotor (4), au moins un espace creux (24) étant formé respectivement entre les pieds (20). L'invention concerne également un procédé de fabrication d'un tel disque aubagé monobloc (2), ainsi qu'une turbine à gaz munie d'un rotor constitué de plusieurs disques aubagés monoblocs (2) de ce type.
PCT/DE2010/001280 2009-11-07 2010-10-30 Disque aubagé monobloc, turbine à gaz et procédé de fabrication d'un tel disque aubagé monobloc WO2011054342A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009052305.7 2009-11-07
DE102009052305A DE102009052305A1 (de) 2009-11-07 2009-11-07 Blisk, Gasturbine und Verfahren zur Herstellung einer derartigen Blisk

Publications (1)

Publication Number Publication Date
WO2011054342A1 true WO2011054342A1 (fr) 2011-05-12

Family

ID=43430833

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2010/001280 WO2011054342A1 (fr) 2009-11-07 2010-10-30 Disque aubagé monobloc, turbine à gaz et procédé de fabrication d'un tel disque aubagé monobloc

Country Status (2)

Country Link
DE (1) DE102009052305A1 (fr)
WO (1) WO2011054342A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150098802A1 (en) * 2013-10-08 2015-04-09 General Electric Company Shrouded turbine blisk and method of manufacturing same
US10247015B2 (en) 2017-01-13 2019-04-02 Rolls-Royce Corporation Cooled blisk with dual wall blades for gas turbine engine
US10415403B2 (en) 2017-01-13 2019-09-17 Rolls-Royce North American Technologies Inc. Cooled blisk for gas turbine engine
US10718218B2 (en) 2018-03-05 2020-07-21 Rolls-Royce North American Technologies Inc. Turbine blisk with airfoil and rim cooling
US10934865B2 (en) 2017-01-13 2021-03-02 Rolls-Royce Corporation Cooled single walled blisk for gas turbine engine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201206269D0 (en) * 2012-04-05 2012-05-23 Napier Turbochargers Ltd Axial Flow Turbine Blisc
ES2532582T3 (es) * 2012-08-09 2015-03-30 Mtu Aero Engines Gmbh Método para fabricar un segmento de corona de álabes de TiAl para una turbina de gas, así como un correspondiente segmento de corona de álabes
US20150354374A1 (en) * 2014-06-09 2015-12-10 General Electric Company Turbine blisk and method of manufacturing thereof
US9551230B2 (en) * 2015-02-13 2017-01-24 United Technologies Corporation Friction welding rotor blades to a rotor disk
DE102018217597A1 (de) * 2018-10-15 2020-04-16 Siemens Aktiengesellschaft Regelradanordnung für eine Dampfturbine sowie Verfahren zum Herstellen einer Regelradanordnung
WO2020099184A1 (fr) * 2018-11-15 2020-05-22 Rolls-Royce Deutschland Ltd & Co Kg Procédé de fabrication d'un composant pour une turbomachine

Citations (6)

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Publication number Priority date Publication date Assignee Title
DE2423036A1 (de) * 1973-05-14 1974-12-05 British Leyland Uk Ltd In einem stueck gegossene turbinenscheibe
US20060099078A1 (en) * 2004-02-03 2006-05-11 Honeywell International Inc., Hoop stress relief mechanism for gas turbine engines
US20070059181A1 (en) 2005-01-26 2007-03-15 Mtu Aero Engines Gmbh Apparatus and method for securing a rotor blade in a rotor of a turbine-type machine
US7431564B2 (en) 2004-04-16 2008-10-07 Rolls Royce Plc Turbine blisk
EP2000631A2 (fr) * 2007-06-07 2008-12-10 Honeywell International Inc. Rotor aubagé et procédé de fabrication associé
EP2045443A2 (fr) * 2007-10-04 2009-04-08 General Electric Company Disque de rotor d'une turbomachine et son procédé de fabrication

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH305819A (de) * 1951-02-26 1955-03-15 Power Jets Res & Dev Ltd Verfahren zur Herstellung eines Schaufelrotors einer Turbomaschine und nach diesem Verfahren hergestellter Schaufelrotor.
DE10361882B4 (de) * 2003-12-19 2013-08-22 Rolls-Royce Deutschland Ltd & Co Kg Rotor für die Hochdruckturbine eines Flugtriebwerks
DE102007037208B4 (de) * 2007-08-07 2013-06-20 Mtu Aero Engines Gmbh Turbinenschaufel mit zumindest einer Einsatzhülse zum Kühlen der Turbinenschaufel

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2423036A1 (de) * 1973-05-14 1974-12-05 British Leyland Uk Ltd In einem stueck gegossene turbinenscheibe
US20060099078A1 (en) * 2004-02-03 2006-05-11 Honeywell International Inc., Hoop stress relief mechanism for gas turbine engines
US7431564B2 (en) 2004-04-16 2008-10-07 Rolls Royce Plc Turbine blisk
US20070059181A1 (en) 2005-01-26 2007-03-15 Mtu Aero Engines Gmbh Apparatus and method for securing a rotor blade in a rotor of a turbine-type machine
EP2000631A2 (fr) * 2007-06-07 2008-12-10 Honeywell International Inc. Rotor aubagé et procédé de fabrication associé
EP2045443A2 (fr) * 2007-10-04 2009-04-08 General Electric Company Disque de rotor d'une turbomachine et son procédé de fabrication

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150098802A1 (en) * 2013-10-08 2015-04-09 General Electric Company Shrouded turbine blisk and method of manufacturing same
US10247015B2 (en) 2017-01-13 2019-04-02 Rolls-Royce Corporation Cooled blisk with dual wall blades for gas turbine engine
US10415403B2 (en) 2017-01-13 2019-09-17 Rolls-Royce North American Technologies Inc. Cooled blisk for gas turbine engine
US10934865B2 (en) 2017-01-13 2021-03-02 Rolls-Royce Corporation Cooled single walled blisk for gas turbine engine
US10718218B2 (en) 2018-03-05 2020-07-21 Rolls-Royce North American Technologies Inc. Turbine blisk with airfoil and rim cooling

Also Published As

Publication number Publication date
DE102009052305A1 (de) 2011-05-12

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