EP2394026B1 - Aube de turbine à gaz pour turbomachine - Google Patents

Aube de turbine à gaz pour turbomachine Download PDF

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Publication number
EP2394026B1
EP2394026B1 EP10798489.0A EP10798489A EP2394026B1 EP 2394026 B1 EP2394026 B1 EP 2394026B1 EP 10798489 A EP10798489 A EP 10798489A EP 2394026 B1 EP2394026 B1 EP 2394026B1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine blade
turbomachine
blade
connecting element
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
EP10798489.0A
Other languages
German (de)
English (en)
Other versions
EP2394026A2 (fr
Inventor
Frank Stiehler
Hans Peter Borufka
Patrick Prokopczuk
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 EP2394026A2 publication Critical patent/EP2394026A2/fr
Application granted granted Critical
Publication of EP2394026B1 publication Critical patent/EP2394026B1/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
    • F01D5/12—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
    • 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
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to a gas turbine blade, in particular a compressor and / or turbine blade, for a turbomachine.
  • each gas turbine blades When joining gas turbine blades and rotor disks or rings during assembly, repair or maintenance, each gas turbine blades must be positioned, displaced or rotated relative to adjacent gas turbine blades and thereby provided with a bias (so-called pre-twist).
  • pre-twist a bias
  • the US 3,328,867 describes an opening on a turbine blade tip over which a mechanical load can be introduced by means of a tool.
  • the EP 1 939 401 A2 describes a method and apparatus for load transfer in rotor assemblies.
  • the US Pat. No. 3,572,968 A describes a turbine having at least one stage of radial blades and a conversion assembly extending in a circle around the tips of the blades.
  • the DE 10 2005 030516 A1 describes a rotor for a turbine, which is provided for receiving one or more rows of blades with a corresponding number of grooves which are each arranged in a direction perpendicular to the longitudinal axis of the rotor extending radial plane.
  • the JP 2004 108290 A describes turbine rotor blades of a steam turbine which, for safe operation, prevents stop switches located between fixed blades and adjacent rotor blades from becoming loose or damaged.
  • the US 5,393,200 describes a steam turbine blade having a blade profile according to given tables.
  • a disadvantage of the known fasteners is the fact that they are relatively expensive, do not allow optimum load transfer into the gas turbine blade and even damage the gas turbine blade in the load application.
  • the object of the present invention is to enable an improved possibility for load introduction into a gas turbine blade.
  • the gas turbine blade comprises at least one receptacle for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade.
  • a geometry of the gas turbine blade according to the invention is designed such that the gas turbine blade has a receptacle which forms an integral interface for the form-fitting arrangement of a corresponding connecting element. Due to the integrated receptacle, the gas turbine blade and the connecting element can engage in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners.
  • the connecting element which is designed as a tool, pin or mandrel is in this way easily and without affecting the other gas turbine blade areas form fit introduced or inserted into the receptacle and can be solved if necessary correspondingly easy again from the gas turbine blade. Mechanical loads can thereby be introduced easily, flexibly and without damaging the gas turbine blade.
  • the gas turbine blade can be formed weight neutral or even reduced weight and allows due to the simple structural design a short tolerance chain with a correspondingly high repeatability.
  • the respective geometry of the receptacle for example its arrangement, form-fitting depth or boundary, may be selected depending on the geometry or the intended use of the respective gas turbine blade.
  • a radially inner end region of the gas turbine blade for connecting the gas turbine blade to a rotor disk or a rotor ring of the turbomachine and / or a radially outer end region of the gas turbine blade is designed as a shroud segment.
  • the gas turbine blade can be designed as a compressor and / or turbine blade.
  • a radially outer end region designed as a shroud segment serves for damping blade vibrations and is particularly suitable when using the gas turbine blades in a rear turbine stage.
  • the shroud segment reduces the flow around the gas turbine blade tip and thereby increases the efficiency of the associated turbomachine.
  • the shroud segment can in principle be formed in one piece or in several parts with the gas turbine blade.
  • the receptacle is formed on the radially outer end region of the gas turbine blade.
  • the receptacle is particularly accessible.
  • a corresponding connecting element for example a tool, can be correspondingly easily introduced into the receptacle in order to apply a mechanical load to the gas turbine blade.
  • a weight optimization of the gas turbine blade is made possible in that it is designed as a hollow blade and at least one cavity.
  • the receptacle is formed as a core exit region of the cavity. This allows a particularly space-saving arrangement of the recording without affecting the other gas turbine blade areas.
  • gas turbine blade being integrally formed with the receptacle and / or as a cast part.
  • the gas turbine blade mechanically particularly stable, inexpensive and easy to manufacture.
  • the actual geometry of the gas turbine blade can be approximated completely or at least largely to a desired geometry.
  • electrochemical Drilling methods PECM drilling
  • a further aspect of the invention relates to a shroud segment for arrangement on a gas turbine shovel, in particular a gas turbine blade according to one of the preceding embodiments, wherein an improved possibility for load introduction into a gas turbine blade according to the invention is made possible by the shroud segment a receptacle for the positive arrangement of a connecting element, by means of which a mechanical load can be introduced into the shroud segment comprises.
  • the resulting advantages are to be taken from the preceding descriptions, wherein advantageous embodiments of the gas turbine blade are to be regarded as advantageous embodiments of the shroud segment and vice versa.
  • the shroud segment can in principle be formed in one piece with the gas turbine blade or initially manufactured as a single part and then connected to the gas turbine blade.
  • the shroud segment has two oppositely arranged and in longitudinal section substantially Z-shaped contact surface for attaching corresponding contact surfaces of two further shroud segments.
  • connection system with a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, and with a connecting element, by means of which a mechanical load in the gas turbine blade can be introduced, wherein an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the gas turbine blade comprises a correspondingly formed with the connecting element receptacle for the positive arrangement of the connecting element. Due to the integrated receptacle, the gas turbine blade and the corresponding connecting element can interlock positively, so that mechanical Loads normal, that is, can be transmitted at right angles to the surfaces of the two connection partners.
  • the gas turbine blade can be provided, for example, before connecting to a shaft of the turbomachine particularly simple and damage-free with a so-called pre-twist.
  • the gas turbine blade can be provided in the context of a repair or overhaul with a so-called re-twist, so that the gas turbine blade can be readjusted.
  • the receptacle are formed as a polygon socket, in particular as a hexagon socket, and the connecting element as a polygonal key, in particular as a hexagon key, for acting on the gas turbine blade with a torque.
  • the connecting element as a polygonal key, in particular as a hexagon key, for acting on the gas turbine blade with a torque.
  • the receptacle and the connecting element may alternatively or in addition to an Allen-like configuration basically also slot, Pozidriv, Torx, Tri-Wing, Torq set or tensioner-like design.
  • Another aspect of the invention relates to a method for connecting a gas turbine blade, in particular a compressor and / or turbine blade for a turbomachine, with a connecting element, by means of which a mechanical load can be introduced into the gas turbine blade, wherein an improved possibility for load introduction into the gas turbine blade according to the invention is thereby made possible that the connecting element is arranged positively in a correspondingly formed with the connecting element receptacle of the gas turbine blade.
  • the gas turbine blade and the corresponding connecting element can be arranged in one another in a form-fitting manner, so that mechanical loads can be transmitted normally, that is to say at right angles to the surfaces of the two connection partners.
  • a further aspect of the invention relates to a rotor for a turbomachine with a rotor disk joined with a blade ring or with a rotor ring joined with a blade ring, wherein according to the invention it is provided that the blade ring has at least one gas turbine blade which comprises at least one exception for the form-fitting arrangement of a connecting element , wherein by means of the connecting element, a mechanical load in the gas turbine blade can be introduced.
  • the rotor is designed as a blisk ("bladed disk”) or as a bling ("bladed ring”) for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine. As a result, a particularly high structural freedom is given.
  • Fig. 1 shows a schematic perspective view of three gas turbine blades 10 according to the invention, which are arranged on a rotor disk 12.
  • an integrally bladed rotor (so-called blisk or "bladed disk”) can be produced for a compressor and / or for a turbine of a turbomachine, in particular a thermal gas turbine.
  • a rotor ring (not shown) may also be used, whereby a so-called bling (“bladed ring”) can be produced.
  • a radially outer end portion 14a is formed as a shroud segment 16 (see FIG. Fig. 2 ).
  • each gas turbine blade 10 also has an integral receptacle 18, in which a connecting element (not shown) can be arranged in a form-fitting manner.
  • the receptacles 18 are each formed at the radially outer end portion 14a of the gas turbine blades 10 in the shroud segments 16 as mecanicsechskantworkn.
  • connection region hexagonal key-shaped connecting element can be easily inserted into the respective receptacle 18 releasably to pressurize the gas turbine blade 10 in question with a torque.
  • each gas turbine blade 10 can be easily, without damage and provided without the need for special tool with a so-called pre-twist.
  • Fig. 2 shows an enlarged view of the in Fig. 1
  • each shroud segment 16 has two contact surfaces which are arranged opposite one another and are substantially Z-shaped in longitudinal section (so-called Z-Shroud) for attaching corresponding contact surfaces 20 of the adjacent shroud segments 16 having.
  • each shroud segment 16 comprises two opposing sealing fins 22 which, in particular during a rotation of the rotor 12 in a abradable region, rub against a sealing structure of an associated turbomachine.
  • FIG. 3 shows for further clarification a schematic side view of one of in Fig. 1 shown gas turbine blades 10.
  • Fig. 3 is described below in synopsis with 4 and FIG. 5 be explained.
  • Fig. 4 shows here a schematic bottom view of in Fig. 3 shown gas turbine blade 10, while in Fig. 5 a schematic sectional side view of the gas turbine blade 10 along in in Fig. 4 shown section line VV is shown. It is especially in Fig. 5 recognizable that the gas turbine blade 10 in the present case is designed as a hollow blade and at least one cavity 24 includes.
  • the receptacle 18 is in turn formed as a core exit region of the cavity 24. Furthermore, in Fig.
  • a Tannenbaum für 26 formed on a radially inner end portion 14b of the gas turbine blade for joining the gas turbine blade 10 with the rotor disk 12 recognizable.
  • the geometry and form-fitting depth of the receptacle 18 can be formed as a function of the shroud segment geometry, wherein, for example, the core exit region of the cavity 24, the arrangement of the contact surfaces 20 and / or a geometry of the sealing fins 22 can be taken into account.

Landscapes

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

Claims (5)

  1. Aube de turbine à gaz (10), en particulier aube de compresseur et/ou de turbine, destinée à une turbomachine, l'aube de turbine à gaz (10) comprenant au moins un logement (18) servant à recevoir par complémentarité de forme un élément de raccordement, au moyen duquel une charge mécanique peut être introduite dans l'aube de turbine à gaz (10), l'aube de turbine à gaz (10) étant réalisée sous la forme d'une aube creuse et comprenant au moins une cavité (24), et le logement (18) étant réalisé sous la forme d'une zone de sortie centrale de la cavité (24), caractérisée en ce que le logement (18) est configuré pour recevoir l'élément de raccordement configuré sous la forme d'un outil, d'un tourillon ou d'un mandarin et destiné à être introduit et/ou enfiché par complémentarité de forme dans le logement (18) aux fins de l'introduction de charges mécaniques dans l'aube de turbine à gaz.
  2. Aube de turbine à gaz (10) selon la revendication 1, caractérisée en ce qu'une zone d'extrémité (14b) radialement intérieure de l'aube de turbine à gaz (10) est réalisée afin de raccorder l'aube de turbine à gaz (10) à un disque de rotor (12) ou à une bague de rotor de la turbomachine, et/ ou en ce qu'une zone d'extrémité (14a), radialement extérieure, de l'aube de turbine à gaz (10) est réalisée sous la forme d'un segment de bande (16) de recouvrement.
  3. Aube de turbine à gaz (10) selon la revendication 1 ou 2, caractérisée en ce que le logement (18) est réalisé au niveau de la zone d'extrémité (14a), radialement extérieure, de l'aube de turbine à gaz (10).
  4. Aube de turbine à gaz (10) selon l'une quelconque des revendications 1 à 3, caractérisée en ce que ladite aube de turbine à gaz est réalisée en une seule partie avec le logement (18) et/ou sous la forme d'une pièce moulée.
  5. Aube de turbine à gaz (10) selon l'une quelconque des revendications 1 à 4, caractérisée en ce qu'au moins une zone de surface de l'aube de turbine à gaz (10) est usinée avec précision.
EP10798489.0A 2009-11-13 2010-11-12 Aube de turbine à gaz pour turbomachine Not-in-force EP2394026B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009052881A DE102009052881A1 (de) 2009-11-13 2009-11-13 Gasturbinenschaufel für eine Strömungsmaschine
PCT/DE2010/001334 WO2011057622A2 (fr) 2009-11-13 2010-11-12 Aube de turbine à gaz pour turbomachine

Publications (2)

Publication Number Publication Date
EP2394026A2 EP2394026A2 (fr) 2011-12-14
EP2394026B1 true EP2394026B1 (fr) 2013-07-17

Family

ID=43901923

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10798489.0A Not-in-force EP2394026B1 (fr) 2009-11-13 2010-11-12 Aube de turbine à gaz pour turbomachine

Country Status (4)

Country Link
US (1) US8622704B2 (fr)
EP (1) EP2394026B1 (fr)
DE (1) DE102009052881A1 (fr)
WO (1) WO2011057622A2 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10428660B2 (en) * 2017-01-31 2019-10-01 United Technologies Corporation Hybrid airfoil cooling

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE634692A (fr) * 1962-07-11 1963-11-18
US3572968A (en) * 1969-04-11 1971-03-30 Gen Electric Turbine bucket cover
US3626568A (en) * 1969-04-23 1971-12-14 Avco Corp Method for bonding pins into holes in a hollow turbine blade
US4136516A (en) * 1977-06-03 1979-01-30 General Electric Company Gas turbine with secondary cooling means
US5393200A (en) * 1994-04-04 1995-02-28 General Electric Co. Bucket for the last stage of turbine
US6158104A (en) * 1999-08-11 2000-12-12 General Electric Co. Assembly jig for use with integrally covered bucket blades
JP2004108290A (ja) 2002-09-19 2004-04-08 Toshiba Corp タービン動翼
US6883700B2 (en) * 2002-09-26 2005-04-26 Siemens Westinghouse Power Corporation Turbine blade closure system
DE10250779A1 (de) * 2002-10-30 2004-05-19 Alstom (Switzerland) Ltd. Notkühlsystem für ein hitzebelastetes Bauteil
DE102005030516A1 (de) 2005-06-28 2007-01-04 Man Turbo Ag Rotor für eine Turbine sowie Verfahren und Vorrichtung zur Herstellung des Rotors
US20080145227A1 (en) 2006-12-19 2008-06-19 Mark Stefan Maier Methods and apparatus for load transfer in rotor assemblies
SG155788A1 (en) * 2008-03-18 2009-10-29 Turbine Overhaul Services Pte Methods and apparatuses for correcting twist angle in a gas turbine engine blade

Also Published As

Publication number Publication date
DE102009052881A1 (de) 2011-05-26
US8622704B2 (en) 2014-01-07
WO2011057622A2 (fr) 2011-05-19
US20120230825A1 (en) 2012-09-13
WO2011057622A3 (fr) 2011-10-13
EP2394026A2 (fr) 2011-12-14

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