WO2007065411A1 - Turbomachine dotee d'un blocage axial des aubes mobiles - Google Patents

Turbomachine dotee d'un blocage axial des aubes mobiles Download PDF

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Publication number
WO2007065411A1
WO2007065411A1 PCT/DE2006/002150 DE2006002150W WO2007065411A1 WO 2007065411 A1 WO2007065411 A1 WO 2007065411A1 DE 2006002150 W DE2006002150 W DE 2006002150W WO 2007065411 A1 WO2007065411 A1 WO 2007065411A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
axial direction
blade ring
base body
sealing element
Prior art date
Application number
PCT/DE2006/002150
Other languages
German (de)
English (en)
Inventor
Wilfried Weidmann
Moritz Wirth
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 US12/096,759 priority Critical patent/US20090028712A1/en
Priority to EP06818118A priority patent/EP1957755A1/fr
Publication of WO2007065411A1 publication Critical patent/WO2007065411A1/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
    • F01D5/30—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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade 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
    • 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
    • F05D2240/56—Brush seals

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of patent claim 1.
  • Turbomachines in particular gas turbines, have a plurality of rotor blades positioned one behind the other in the axial direction, both in the region of a turbine and in the region of a compressor, each rotor blade ring having an in particular disk-shaped rotor base body and a plurality of rotor blades rotating with the rotor base body.
  • the present invention relates to a turbomachine, in particular a gas turbine, in which the rotor blades of the rotor blade rings are fastened via their blade feet in grooves which run essentially in the axial direction of the basic rotor body, that is to say in so-called axial grooves.
  • the rotor blades of the rotor blade rings must be secured in their assembly position or their anchoring position in the axial grooves of the basic rotor body against displacement in the axial direction.
  • wire locks are usually used to axially secure the rotor blades of a rotor blade ring, which are fastened via their blade feet in axial grooves of a rotor base body.
  • a wire-shaped locking element is threaded into a groove which is formed between the blade roots of the rotor blades and the rotor base body, in order to secure the rotor blades against displacement in the axial direction.
  • a separate wire-shaped securing element is usually used for each rotor blade, which causes complex assembly of the wire securing devices.
  • wire fuses are subject to tolerances.
  • locking plates are used, which are also referred to as locking plates or locking plates.
  • Such locking plates are guided both in an annular groove of the basic rotor body and in an annular groove of the rotor blades anchored in the basic rotor body.
  • Such locking plates increase the load on the blade root of the moving blades and thus the edge loads that occur.
  • the present invention is based on the problem of creating a new type of turbomachine.
  • This problem is solved in that the turbomachine mentioned at the outset is further developed by the features of the characterizing part of patent claim 1.
  • the rotor blades of at least one rotor blade ring have hook-like securing elements which, in the anchoring position, bear against the rotor base body of the rotor blade body in the anchoring position, the hook-like securing elements between the rotor base body of the rotor blade ring and a sealing element which is located between the rotor base body and a rotor base body Low pressure side adjoining blade ring extends, are fixed on both sides in the axial direction.
  • the rotor blades to be secured in their axial position have hook-like securing elements which are fixed on both sides between the rotor base body of the respective rotor blade ring and the sealing element by clamping.
  • This provides a completely new type of protection of rotor blades guided in axial grooves against unintentional displacement in the axial direction, which is characterized by simple assembly and disassembly and by means of which leakage flows in the radially inner region of the rotor blade rings can be minimized.
  • the axial securing of the rotor blades according to the invention does not increase the load acting on the blade roots of the rotor blades.
  • the sealing element is preferably fastened in a bayonet-like manner to the rotor base body of the rotor blade ring, the rotor blades of which are to be secured against displacement in the axial direction, via a section adjacent to the hook-like securing elements, this section of the sealing element fixing the hook-like securing elements of the rotor blades in the axial direction on both sides.
  • Fig. 2 a section of a gas turbine according to the invention according to a second embodiment of the invention.
  • FIG. 1 shows a section of a turbine 10 of a gas turbine according to the invention, namely a gas turbine aircraft engine, in the area of two rotating rotor blade rings 11, 12 arranged one behind the other in the axial direction, a fixed guide blade ring 13 being arranged between the two rotor blade rings 11, 12 shown.
  • the turbine 10 is flowed through in the direction of arrow 14 shown in FIG. 1 in the axial direction.
  • Each of the two rotor blade rings 11, 12 shown in FIG. 1 has a preferably disk-shaped rotor base body 15 or 16, with rotor blades 17 or 18 of the rotor blade rings 11 or 12 via blade feet 19 or 20 in so-called axial grooves of the respective rotor base body 15 or 16 are attached or anchored.
  • the axial grooves of the basic rotor bodies 15 and 16, in which the rotor blades 17 and 18 are anchored via their blade feet 19 and 20, run essentially in the axial direction of the turbine 10.
  • Radially close to the blade feet 19, 20 of the rotor blades 17, 18 External blades 21, 22, wherein blade root platforms 23, 24 are formed between the blade roots 19, 20 and the blade blades 21, 22 of the moving blades 17, 18.
  • the guide vane ring 13 positioned between the two rotor blade rings 11, 12 comprises a plurality of fixed guide vanes 25, a platform 27 being formed on a radially inner end of the airfoil blades 26 of the fixed guide vanes 25, on which a seal 28 in the form of the embodiment in FIG. 1 is formed a brush seal is attached, but other types of seals can be used.
  • the stator-side seal 28 interacts with a rotor-side sealing element 29 positioned between the two rotor blade rings 11, 12, so as to seal a radially inner gap between the rotating rotor blade rings 11, 12 and the fixed guide blade ring 13.
  • the rotor blades 17 of the rotor blade ring 11 are assigned hook-like securing elements 30, which in the anchoring position on a low-pressure side of the rotor blade ring 11 bear against the rotor base body 15 of the same.
  • the securing elements 30 are assigned to the blade feet 19 of the rotor blades 17 and rest with a radially inner section 31 on the rotor base body 15 of the rotor blade ring 11.
  • the hook-like securing elements 30 are axially secured on both sides in the axial direction between the rotor base body 15 of the rotor blade ring 11 and the sealing element 29, which extends between the rotor base body 15 of the rotor blade ring 11 and the rotor base body 16 of the rotor blade ring 12 which adjoins on the low-pressure side. 1, the hook-like securing elements 30 are clamped on both sides between the rotor base body 15 of the rotor blade ring 11, which includes the rotor blades 17 to be secured with regard to their axial position, and the rotor-side sealing element 29.
  • the rotor-side sealing element 29 is fastened in a bayonet-like manner to the rotor base body 15 of the rotor blade ring 11 via a section 32, which is positioned adjacent to the hook-like securing elements 30 of the rotor blades 17.
  • the section 32 of the sealing element 29 has a nose-like projection 33, which can be inserted into a groove 34 of the basic rotor body 15 in the axial direction via an opening (not shown).
  • the sealing element 29 can be rotated in the circumferential direction, in order for the bayonet-type fastening of the sealing element 29 on the rotor base body 15 of the rotor blade ring 11, the rotor blades 17 of which to be displaced in the axial direction are to be secured.
  • the hook-like securing elements 30 are clamped between the rotor base body 15 and the sealing element 29, in order to fix the rotor blades 17 and 18 on both sides.
  • FIG. 2 shows a further exemplary embodiment of a gas turbine according to the invention, a section of a turbine 35 also being shown in the exemplary embodiment of FIG. 2.
  • the embodiment of FIG. 2 corresponds in many details to the embodiment of FIG. 1, so that the same reference numbers are used to avoid unnecessary repetitions for the same modules. In the following, only the details are dealt with, by which the embodiment of FIG. 2 differs from the embodiment of FIG. 1.
  • the rotor blades 17 have hook-like securing elements 30 which, in the anchoring position, bear against the rotor base body 15 on a low-pressure side of the rotor blade ring 11.
  • the hook-like securing elements 30 are in turn fixed between the rotor base body 15 of the rotor blade ring 11 and the sealing element 29 in the axial direction, the sealing element 29 being located between the rotor base body 15 of the rotor blade ring 11, the rotor blades of which are to be secured against displacement in the axial direction, and the rotor base body 16 of the rotor blade ring 12 adjoining on the low pressure side extends.
  • the sealing element 29 is not connected in a bayonet-like manner to the basic rotor body 15 of the rotor blade ring 11, as in the exemplary embodiment in FIG. 1, rather a projection 36 of the sealing element 29 is between two flanges 37 and 38 of the basic rotor bodies 15 and 12 positioned one behind the other in the axial direction 16 fastened by screwing.
  • a section 39 of the sealing element 29 adjoining the projection 36 serves to fix the hook-like securing elements 30 on both sides between the rotor base body 15 and the sealing element 29, in order to prevent the blades 17 of the rotor blade ring 11 from being moved unintentionally in the axial direction.
  • rotor blades of rotor blade rings which are guided in axial grooves are thus secured against unwanted axial displacement by fixing hook-like securing elements associated with the blade roots of the rotor blades between the rotor base body of the rotor blade ring and a rotor-side sealing element of a so-called inner air seal seal, namely on both sides in the axial direction, with all the blades of two adjacent rotor blade rings 11 and 12 being axially secured by a component 29.
  • the sealing element is preferably attached to the corresponding rotor base body in a bayonet-like manner.
  • the invention has the advantage that rotor blades can be assembled and disassembled on the rotor base body relatively easily. All the blades of a blade ring can be fixed together in the axial direction using a sealing element.

Landscapes

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

Abstract

L'invention concerne le rotor d'une turbomachine et en particulier le rotor d'une turbine à gaz qui présente plusieurs couronnes (11, 12) d'aubes mobiles disposées les unes derrière les autres dans la direction axiale et associées à une turbine ou à un compresseur. Chaque couronne d'aubes mobiles présente un corps de base (15, 16) de rotor doté de plusieurs aubes mobiles (17, 18) et les aubes mobiles d'une couronne d'aubes mobiles sont ancrées par des pieds (19, 20) d'aube dans des rainures axiales qui s'étendent essentiellement dans la direction axiale dans le corps de base de rotor concerné et le blocage desdites aubes mobiles dans leur position d'ancrage dans le corps de base du rotor empêche leur déplacement dans la direction axiale. Les aubes mobiles (17) d'au moins une couronne (11) d'aubes mobiles présentent des éléments de blocage (30) en forme de crochet qui, dans la position d'ancrage, reposent sur le corps de base (15) du rotor du côté basse pression de la couronne (11) d'aubes mobiles, les éléments de blocage en forme de crochet étant fixés des deux côtés dans la direction axiale entre le corps de base (15) du rotor de la couronne (11) d'aubes mobiles et un élément d'étanchéité (29) qui s'étend entre le corps de base (15) du rotor et un corps de base (16) du rotor d'une couronne (12) d'aubes mobiles adjacentes du côté basse pression.
PCT/DE2006/002150 2005-12-10 2006-12-05 Turbomachine dotee d'un blocage axial des aubes mobiles WO2007065411A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US12/096,759 US20090028712A1 (en) 2005-12-10 2006-12-05 Turbomachine having axial rotor blade securing
EP06818118A EP1957755A1 (fr) 2005-12-10 2006-12-05 Turbomachine dotee d'un blocage axial des aubes mobiles

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005059084.5 2005-12-10
DE102005059084A DE102005059084A1 (de) 2005-12-10 2005-12-10 Turbomaschine, insbesondere Gasturbine

Publications (1)

Publication Number Publication Date
WO2007065411A1 true WO2007065411A1 (fr) 2007-06-14

Family

ID=37887331

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2006/002150 WO2007065411A1 (fr) 2005-12-10 2006-12-05 Turbomachine dotee d'un blocage axial des aubes mobiles

Country Status (4)

Country Link
US (1) US20090028712A1 (fr)
EP (1) EP1957755A1 (fr)
DE (1) DE102005059084A1 (fr)
WO (1) WO2007065411A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009007664A1 (de) 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine
US8235656B2 (en) * 2009-02-13 2012-08-07 General Electric Company Catenary turbine seal systems
US11021976B2 (en) * 2014-12-22 2021-06-01 Raytheon Technologies Corporation Hardware geometry for increasing part overlap and maintaining clearance
DE102016202519A1 (de) 2016-02-18 2017-08-24 MTU Aero Engines AG Leitschaufelsegment für eine Strömungsmaschine
US10633992B2 (en) 2017-03-08 2020-04-28 Pratt & Whitney Canada Corp. Rim seal
CN109209995B (zh) * 2017-06-30 2020-04-28 中国航发商用航空发动机有限责任公司 轴流压气机
US11629645B2 (en) * 2019-08-08 2023-04-18 Raytheon Technologies Corporation Hydrostatic seal with extended carrier arm

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2689682A (en) * 1951-01-06 1954-09-21 A V Roe Canada Ltd Gas turbine compressor
US2972470A (en) * 1958-11-03 1961-02-21 Gen Motors Corp Turbine construction
US3056579A (en) * 1959-04-13 1962-10-02 Gen Electric Rotor construction
US3295825A (en) * 1965-03-10 1967-01-03 Gen Motors Corp Multi-stage turbine rotor
GB1527074A (en) * 1974-09-28 1978-10-04 Rolls Royce Bladed rotors
US4526508A (en) * 1982-09-29 1985-07-02 United Technologies Corporation Rotor assembly for a gas turbine engine
US4884950A (en) * 1988-09-06 1989-12-05 United Technologies Corporation Segmented interstage seal assembly
GB2274688A (en) * 1993-01-27 1994-08-03 Snecma Retaining and sealing arrangement for the blades of a rotor disc
GB2286431A (en) * 1994-02-10 1995-08-16 Snecma Turbomachine rotor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935296A (en) * 1951-12-26 1960-05-03 Gen Motors Corp Blade retaining means
FR2663997B1 (fr) * 1990-06-27 1993-12-24 Snecma Dispositif de fixation d'une couronne de revolution sur un disque de turbomachine.
US6131911A (en) * 1992-11-19 2000-10-17 General Electric Co. Brush seals and combined labyrinth and brush seals for rotary machines
US5733103A (en) * 1996-12-17 1998-03-31 General Electric Company Vibration damper for a turbine engine
US6749400B2 (en) * 2002-08-29 2004-06-15 General Electric Company Gas turbine engine disk rim with axially cutback and circumferentially skewed cooling air slots
FR2868807B1 (fr) * 2004-04-09 2008-12-05 Snecma Moteurs Sa Dispositif d'equilibrage d'une piece en rotation en particulier d'un rotor de turboreacteur
PL1944471T3 (pl) * 2007-01-09 2010-02-26 Siemens Ag Osiowy segment wirnika dla wirnika turbiny

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2689682A (en) * 1951-01-06 1954-09-21 A V Roe Canada Ltd Gas turbine compressor
US2972470A (en) * 1958-11-03 1961-02-21 Gen Motors Corp Turbine construction
US3056579A (en) * 1959-04-13 1962-10-02 Gen Electric Rotor construction
US3295825A (en) * 1965-03-10 1967-01-03 Gen Motors Corp Multi-stage turbine rotor
GB1527074A (en) * 1974-09-28 1978-10-04 Rolls Royce Bladed rotors
US4526508A (en) * 1982-09-29 1985-07-02 United Technologies Corporation Rotor assembly for a gas turbine engine
US4884950A (en) * 1988-09-06 1989-12-05 United Technologies Corporation Segmented interstage seal assembly
GB2274688A (en) * 1993-01-27 1994-08-03 Snecma Retaining and sealing arrangement for the blades of a rotor disc
GB2286431A (en) * 1994-02-10 1995-08-16 Snecma Turbomachine rotor

Also Published As

Publication number Publication date
EP1957755A1 (fr) 2008-08-20
US20090028712A1 (en) 2009-01-29
DE102005059084A1 (de) 2007-06-14

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