EP1657404A1 - Rotor d'une turbomachine, notamment rotor d'une turbine à gaz - Google Patents

Rotor d'une turbomachine, notamment rotor d'une turbine à gaz Download PDF

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Publication number
EP1657404A1
EP1657404A1 EP05024246A EP05024246A EP1657404A1 EP 1657404 A1 EP1657404 A1 EP 1657404A1 EP 05024246 A EP05024246 A EP 05024246A EP 05024246 A EP05024246 A EP 05024246A EP 1657404 A1 EP1657404 A1 EP 1657404A1
Authority
EP
European Patent Office
Prior art keywords
rotor
base body
blades
closure
plates
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.)
Granted
Application number
EP05024246A
Other languages
German (de)
English (en)
Other versions
EP1657404B1 (fr
Inventor
Joachim Wulf
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 EP1657404A1 publication Critical patent/EP1657404A1/fr
Application granted granted Critical
Publication of EP1657404B1 publication Critical patent/EP1657404B1/fr
Expired - Fee Related 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the invention relates to a rotor of a turbomachine, in particular a gas turbine rotor, according to the preamble of patent claim 1.
  • Rotors of a turbomachine such as gas turbine rotors
  • the present invention relates to a rotor of a turbomachine, in particular a gas turbine rotor, in which the blades are fastened via their blade roots in grooves which extend in the axial direction of the rotor body, ie in axial grooves.
  • closure plates In gas turbine rotors, in which the blades are anchored via their blade roots in axial grooves of the rotor body, are used for axial securing of the blades so-called closure plates are used, which are also referred to as locking plates.
  • the closure plates are guided in the assembled state in an annular groove of the rotor body and in an annular groove of the rotor blades anchored in the rotor body.
  • the closure plates are designed like a rectangle, which must be moved in the axial direction of one or more blades in the preassembled rotor assembly for mounting these rectangular-shaped shutter plate in the annular grooves of the rotor body and blades, so that the shutter plates can be inserted into the annular grooves.
  • an increased clearance between the blade roots of the blades and the respective axial grooves of the rotor body is required.
  • such increased foot play has a negative impact on the strength of the blades.
  • the present invention based on the problem to provide a novel rotor of a turbomachine.
  • the closure platelets have a dragon-like, in particular a parallelogram-like or diamond-like, outline, such that the closure platelets can be inserted in an insertion position between the rotor base body and the blade platforms of the rotor blades and in an assembly position rotated relative to this insertion position into the annular grooves Rotor body and blade platforms are screwed.
  • a radial width thereof is smaller than the distance between an edge defining the annular groove of the rotor base body and an edge defining the annular groove of the blade platforms;
  • a radial width of the closure plates is greater than the distance between the edge defining the annular groove of the rotor base body and the edge defining the annular groove of the blade platforms.
  • a rotor of a turbomachine in particular a gas turbine rotor
  • the closure plates for Axialfix ist or axial securing formed in axial grooves on their blade feet blades are formed kite similar.
  • the closure plates are designed parallelogram-like or rhombus-like, wherein edges of the closure plates can be either rectilinear or circular arc-shaped and are adapted to the groove diameter. Due to the contour of the closure plates according to the invention, they can be inserted easily or without problems between the rotor base body and the blade platforms of the moving blades. To insert the same into the annular grooves of the rotor base body and rotor blades, the closure plates are merely twisted. This makes it possible to minimize the play between the blade root of the blades and the axial grooves of the rotor body. This increases the strength of the blade root.
  • a connecting line between two radially opposite corner points of a closure plate passes through a center of the rotor base body.
  • a focus of the shutter plate is offset from the connecting line extending through the center of the rotor body such that the shutter plates automatically stabilize in their mounting position during operation of the rotor.
  • FIG. 1 and 2 show a known from the prior art gas turbine rotor 10 having a rotor body 11 and a plurality of blades 12.
  • Each of the rotor blades 12 has an airfoil 13 and a blade root 14, wherein a blade platform 15 is formed between the airfoil 13 and the blade root 14.
  • a plurality of axially extending axial groove 16 are introduced, each blade 12 is anchored with its blade root 14 in such axial groove 16 in the rotor body 11.
  • the axial grooves 16 can be set in the circumferential direction.
  • closure plate 17 which are also referred to as locking plates.
  • the closure plates 17 are guided on the one hand in an annular groove 18 of the rotor base body 11 and on the other hand in annular grooves 19 of the blade platforms 15. 1 and 2, the closure plates 17 according to the prior art have a rectangular-like outline, whereby it is necessary to insert the closure plates 17 in the annular grooves 18 and 19, one or more blades 12 in the pre-assembled rotor assembly in Move axial direction.
  • an enlargement of a foot clearance between the blade roots 14 and the respective axial groove 16 is required in the prior art, which is disadvantageous for reasons of strength. This is especially true for blades with outer shroud and so-called Z-toothing in the area of the outer shroud.
  • FIGS. 3a to 3d show highly schematic different views of a gas turbine rotor 20 according to the invention, which in turn has a rotor main body 21 and a plurality of rotor blades 22.
  • Each of the rotor blades 22 has an airfoil 23, a blade root 24 and a blade platform 25, wherein the blade platform 25 is positioned between the blade root 24 and the airfoil 23.
  • the blades 22 are anchored with their blade roots 24 in axial grooves 26 of the rotor body 21, wherein an axial fixation or axial securing of the blades 22 is accomplished in the axial grooves 26 via closure plate 27.
  • the closure plates 27 engage, on the one hand, in an annular groove 28 of the rotor base body 21 and in the annular groove 29 of the blade platform 25.
  • the annular groove 28 of the rotor main body 21 is defined by a radially inner edge 30 and a radially outer edge 31; the annular groove 29 of the rotor blades 22 is defined by a radially inner edge 32 and a radially outer edge 33 defined.
  • the shutter plate 27 For Axialfix ist or axial securing of the blades 22, the shutter plate 27 must engage in the annular grooves 28 and 29, that in the projection a radially outer edge 34 of the shutter plate 27 of the radially inner edge 32 of the annular groove 29 of the blades 22 and a radially inner edge 35 of the closure plate 27 is covered by the radially outer edge 31 of the annular groove 28 of the rotor base body 21.
  • the closure plate 27 For insertion of the closure plate 27 into the annular grooves 28 and 29, however, the same must be threaded between the radially outer edge 31 of the annular groove 28 of the rotor base 21 and the radially inner edge 32 of the annular groove 29 of the blade 22.
  • the closure flakes 27 have a kite-like, in particular a parallelogram-like or diamond-like, outline, so that the closure flakes 27 can be inserted between the rotor base body 21 and the rotor blades 22 in an insertion position (see FIGS. 3a and 3b) are, namely between the radially outer edge 31 of the annular groove 28 of the rotor body 21 and the radially inner edge 32 of the annular groove 29 of the blades 22.
  • a kite-like, in particular a parallelogram-like or diamond-like, outline are, namely between the radially outer edge 31 of the annular groove 28 of the rotor body 21 and the radially inner edge 32 of the annular groove 29 of the blades 22.
  • the shutter plates 27 engage with their edges 34 and 35 in the annular grooves 28 and 29, their edges 34 and 35 are therefore hidden in the mounting position of the radially outer edge 31 of the annular groove 28 of the rotor base 21 and the radially inner edge 32 of the annular groove 29 of the blades 22.
  • the procedure is such that the closure plates 27 are pushed in their twisted insertion position (see FIG. 3 a) in the direction of the arrow 36 between the rotor base 21 and the rotor blade 22, in order then to be inserted therein Position in the direction of the arrow 37 (see Fig. 3b) to be rotated in its mounting position.
  • a closure plate 27 twisted into the mounting position is then displaced in the circumferential direction in the direction of the arrow 38 (see FIG. 3c) until it comes into contact with an already mounted closure plate 27.
  • Locking plates 27 twisted into their mounting position in this manner are fixed by at least one plastically deformable closing element 39, which is pressed into the annular grooves 28 and 29 in the direction of the arrow 40 (see FIG. 3d).
  • a connecting line 41 extends between two radially opposite corner points 42 and 43 of a closure plate 27 through a center of the rotor base 21, not shown.
  • a center of gravity 44 of the closure plates 27 is opposite the connecting line 41 offset.
  • the center of gravity 44 relative to the connecting line 41 is offset such that the shutter plates 27 automatically stabilize in its mounting position during operation of the rotor.
  • Fig. 5 visualizes with the arrow 45 on the shutter plate 27 during operation centrifugal forces acting due to the position of the center of gravity 44 relative to the connecting line 41 and defined by the corner point 43 pivot point of the shutter plate 27 self-stabilization of the shutter plate 27 at centrifugal force effect , Accordingly, the position of the center of gravity 44 stabilizes the position of the closure plates 27 automatically, so that loss of a single closure plate 27 or a closure element 39 during operation does not necessarily mean that other closure plates 27 are lost. This increases the safety of the axial fixation of the rotor blades 22.
  • the closure plates 27 are all designed parallelogram-like with rectilinear edges. Each two opposite edges are essentially parallel to each other. As shown in FIG. 6, the closure plates 27 may also have circular arc-shaped edges. As a result, a better contour adjustment of the closure plate 27 to the annular grooves 28 and 29 is possible, the manufacturing cost of the closure plate 27 with circular arc extending edges, however, is higher than the production cost of closure plate 27 with rectilinear edges.
EP05024246A 2004-11-13 2005-11-08 Rotor d'une turbomachine, notamment rotor d'une turbine à gaz Expired - Fee Related EP1657404B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102004054930A DE102004054930A1 (de) 2004-11-13 2004-11-13 Rotor einer Turbomaschine, insbesondere Gasturbinenrotor

Publications (2)

Publication Number Publication Date
EP1657404A1 true EP1657404A1 (fr) 2006-05-17
EP1657404B1 EP1657404B1 (fr) 2008-01-02

Family

ID=35708619

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05024246A Expired - Fee Related EP1657404B1 (fr) 2004-11-13 2005-11-08 Rotor d'une turbomachine, notamment rotor d'une turbine à gaz

Country Status (4)

Country Link
US (1) US7306435B2 (fr)
EP (1) EP1657404B1 (fr)
DE (2) DE102004054930A1 (fr)
ES (1) ES2298908T3 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6769866B1 (en) 1999-03-09 2004-08-03 Siemens Aktiengesellschaft Turbine blade and method for producing a turbine blade
EP1905955A1 (fr) * 2006-09-25 2008-04-02 Siemens Aktiengesellschaft Rotor de turbine avec plaques de verrouillage et procédé d'assemblage associé
JP2010507747A (ja) * 2006-10-26 2010-03-11 シーメンス アクチエンゲゼルシヤフト タービン羽根アセンブリ
WO2012028653A3 (fr) * 2010-09-03 2012-04-26 Siemens Aktiengesellschaft Joints de blocage axiaux pour pale de turbine arrière amovible

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2511584B (en) 2013-05-31 2015-03-11 Rolls Royce Plc A lock plate
CN110578557A (zh) * 2019-10-29 2019-12-17 北京动力机械研究所 一种涡轮叶片锁紧装置及其装配方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1536134A (fr) * 1966-09-13 1968-08-09 Rolls Royce Rotor à aubes
GB1209419A (en) * 1968-06-24 1970-10-21 Westinghouse Electric Corp Side plates for turbine blades
US3656865A (en) * 1970-07-21 1972-04-18 Gen Motors Corp Rotor blade retainer
US3904317A (en) * 1974-11-27 1975-09-09 Gen Electric Bucket locking mechanism
EP0761930A1 (fr) * 1995-08-24 1997-03-12 ROLLS-ROYCE plc Segments d'étanchéité et de rétention pour les aubes d'une turbomachine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3043562A (en) * 1961-04-10 1962-07-10 Gen Electric Combination sealing and restraining member for long-shank turbo-machine buckets
US5256035A (en) * 1992-06-01 1993-10-26 United Technologies Corporation Rotor blade retention and sealing construction

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1536134A (fr) * 1966-09-13 1968-08-09 Rolls Royce Rotor à aubes
GB1209419A (en) * 1968-06-24 1970-10-21 Westinghouse Electric Corp Side plates for turbine blades
US3656865A (en) * 1970-07-21 1972-04-18 Gen Motors Corp Rotor blade retainer
US3904317A (en) * 1974-11-27 1975-09-09 Gen Electric Bucket locking mechanism
EP0761930A1 (fr) * 1995-08-24 1997-03-12 ROLLS-ROYCE plc Segments d'étanchéité et de rétention pour les aubes d'une turbomachine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6769866B1 (en) 1999-03-09 2004-08-03 Siemens Aktiengesellschaft Turbine blade and method for producing a turbine blade
EP1905955A1 (fr) * 2006-09-25 2008-04-02 Siemens Aktiengesellschaft Rotor de turbine avec plaques de verrouillage et procédé d'assemblage associé
WO2008037550A1 (fr) * 2006-09-25 2008-04-03 Siemens Aktiengesellschaft Rotor de turbine avec des plaques de verrouillage et procédé d'assemblage correspondant
US8128373B2 (en) 2006-09-25 2012-03-06 Siemens Aktiengesellschaft Turbine rotor with locking plates and corresponding assembly method
JP2010507747A (ja) * 2006-10-26 2010-03-11 シーメンス アクチエンゲゼルシヤフト タービン羽根アセンブリ
US8096776B2 (en) 2006-10-26 2012-01-17 Siemens Aktiengesellschaft Turbine blade assembly
WO2012028653A3 (fr) * 2010-09-03 2012-04-26 Siemens Aktiengesellschaft Joints de blocage axiaux pour pale de turbine arrière amovible
US9109457B2 (en) 2010-09-03 2015-08-18 Siemens Energy, Inc. Axial locking seals for aft removable turbine blade

Also Published As

Publication number Publication date
US7306435B2 (en) 2007-12-11
US20060239822A1 (en) 2006-10-26
DE502005002392D1 (de) 2008-02-14
ES2298908T3 (es) 2008-05-16
EP1657404B1 (fr) 2008-01-02
DE102004054930A1 (de) 2006-05-18

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