EP2366061B1 - Turbinenrad mit einem axialrückhaltesystem für schaufeln - Google Patents

Turbinenrad mit einem axialrückhaltesystem für schaufeln Download PDF

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Publication number
EP2366061B1
EP2366061B1 EP09803867.2A EP09803867A EP2366061B1 EP 2366061 B1 EP2366061 B1 EP 2366061B1 EP 09803867 A EP09803867 A EP 09803867A EP 2366061 B1 EP2366061 B1 EP 2366061B1
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EP
European Patent Office
Prior art keywords
disk
blades
turbine wheel
wheel according
teeth
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.)
Active
Application number
EP09803867.2A
Other languages
English (en)
French (fr)
Other versions
EP2366061A1 (de
Inventor
Jean-Baptiste Arilla
Michel Beaucoueste
Denis Chanteloup
Michel Clastre
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.)
Safran Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
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Publication date
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Priority to PL09803867T priority Critical patent/PL2366061T3/pl
Publication of EP2366061A1 publication Critical patent/EP2366061A1/de
Application granted granted Critical
Publication of EP2366061B1 publication Critical patent/EP2366061B1/de
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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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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 generally to turbine wheels in gas turbines and more particularly to the axial retention of vanes carried by the wheels.
  • the field of application of the invention is in particular that of industrial gas turbines and aeronautical gas turbine engines.
  • the blades are mounted on the periphery of a disk, each blade having a blade with a foot secured to a fastener axially engaged in a housing or cell opening at the periphery of the disk and extending between two opposite sides of the disc.
  • Axial retention devices for the vanes are necessary to avoid axial displacement due to vibration or thermal effects despite the pressure generated by the centrifugal force between the contacting surface portions of the blade attachments and disk housings.
  • the axial support between a blade and a corresponding tooth of the disk is positioned substantially at the extrados of the blade under the blade root.
  • the retaining flange exerts an axial lateral support on lateral faces of the teeth of the disc or of the blade attachments.
  • the retaining flange advantageously has a limited radial dimension to abut only in the lower part of the teeth of the disc or the blade attachments.
  • the axial support between the blades and the rotor and the maintenance of this axial support can be advantageously provided without consumption of the radial clearance between the rotor and an adjacent stator.
  • the retaining flange may be supported on the lateral faces of the teeth of the disc or the fasteners of the blades with prestressing.
  • the retaining flange may be mounted on the rotor being immobilized axially by a retaining ring.
  • At least one opening forming a viewing window is formed in the rotor to allow a visual control of the positioning of the retaining ring.
  • the invention further relates to a turbomachine comprising a turbine wheel according to the invention.
  • the figure 1 shows a turbine rotor 10, for example a high-pressure turbine rotor (HP) in a gas turbine engine.
  • the rotor 10 is secured to a disk 12 carrying at its periphery a plurality of blades 20.
  • the blades 20 each comprise a blade 22 which extends in the annular passage 30 for the gas flow through the turbine, which passage is delimited on the outer side by a turbine ring (not shown) adjacent to the apices of the blades.
  • Each blade 20 has its foot secured to a platform 24 carrying a fastener (or stagger) 26 by which the blade is connected to the disk 12.
  • the fastener has a profile in the form of "fir ".
  • the platforms 24 of the vanes delimit the passage 30 on the inner side.
  • the fasteners 26 are engaged axially in housings (or cells) 14 of corresponding shape distributed and opening at the periphery of the disc 10.
  • the housings 14 extend axially over the entire distance between the upstream (or front) side faces 12 a and downstream (or rear) 12 b of the disk and are separated from each other by teeth 16 of the disk.
  • the upstream and downstream terms are used herein with reference to the flow direction of the gas stream in the turbine.
  • One or more reliefs 28, for example two circumferentially aligned reliefs, may be formed on the lower face of the platform 24 of a blade 20 to bear against a stop 18 in the form of a rib.
  • a rib-shaped relief 28 formed on the lower face of the platform 24 of a blade 20 may bear against a plurality of stops 18 formed on a corresponding tooth 16 of the disk, for example two abutments 18 aligned circumferentially.
  • Fasteners 26 extend along the housing 14 and the upstream side faces 26 a and 26 b downstream of the fasteners are located substantially in the same planes as, respectively, the side faces 12 has upstream and downstream 12b at the periphery of the disc 12.
  • the trailing edge BF at the base of the blades 22 is not substantially cantilevered with respect to the fasteners 26 of the blades and an overload is not generated on the fasteners 26 on the downstream side .
  • a flange 40 On the upstream side, the axial retention of the blades is provided by a flange 40.
  • the flange 40 has teeth 42 which protrude and are supported laterally on the upstream side faces 26 are fasteners 26, without contact with the upstream side face 12a of the disk 12.
  • the flange 40 has a continuous peripheral rim 46 projecting which comes into lateral contact against the upstream side face 12a of the disk 12, to the teeth 16.
  • the mounting flange 40 can then be made with axial prestressing pressure to ensure bearing teeth 42 on the teeth 16 of the rotor.
  • axial dimensions of the fasteners 26 and teeth 16 are such that the upstream side, the fasteners 26 do not protrude out of the plane of the upstream face 12 a of the disc 12, to the teeth 16.
  • the retaining flange 40 has at its periphery an extra thickness 41 forming a cantilevered mass on the side opposite to that resting on the teeth 16 or fasteners 26. This avoids an opening of the flange at its peripheral portion with loss of support on the teeth 16 or fasteners 26 under the effect of the deformation induced by the rotation.
  • flange 40 on the rotor 10 with axial locking may be adopted, for example a bayonet mount.
  • axial retention means of the blades may be reversed, with stops formed on the upstream sides of the disc teeth cooperating with the ribs formed under the platforms of the blades and a retaining flange located on the downstream side exerting a bearing on the downstream lateral faces of the teeth or blade attachments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Turbinenrad, umfassend:
    - eine Vielzahl von Schaufeln (20),
    - einen Rotor (10) mit einer Scheibe (12), die gegenüberliegende Seitenflächen aufweist und an deren Umfang die Schaufeln angebracht sind, wobei eine jede Schaufel ein Blatt (22) mit einem Fuß aufweist, der mit einer Plattform (24) fest verbunden ist, welche eine Halterung (26) mit gegenüberliegenden Seitenflächen, die in eine sich am Umfang der Scheibe öffnende Aufnahme (14) eingesteckt ist, trägt, wobei die Aufnahmen durch Zähne (16) bildende Teile der Scheibe voneinander getrennt sind, und
    - Vorrichtungen zum axialen Festhalten der Schaufeln an der Scheibe, wobei das axiale Festhalten der Schaufeln an einer, oder ersten, der stromauf- und stromabwärtigen Seiten der Scheibe mittels eines Halteflansches bewerkstelligt wird und an der anderen oder zweiten Seite der Scheibe durch Anlage zwischen einer Erhebung, die am Umfang der Scheibe radial vorspringt, und einer Erhebung (28), die unter den Plattformen der Schaufeln ausgebildet ist, bewerkstelligt wird,
    wobei die Aufnahmen der Halterungen (26) der Schaufeln sich axial über die gesamte Distanz zwischen den gegenüberliegenden Seitenflächen der Scheibe (12) erstrecken und auf der zweiten Seite der Scheibe das axiale Festhalten der Schaufeln durch axiale Anlage zwischen den unter den Plattformen der Schaufeln gebildeten Erhebungen (28) und an den Zähnen (16) der Scheibe gebildeten Erhebungen (18) sichergestellt wird, und wobei die Seitenflächen der Halterungen (26) der Schaufeln und der Scheibe (12) an ihrem Umfang im Wesentlichen in einer gleichen Ebene auf jeder Seite der Scheibe gelegen sind,
    dadurch gekennzeichnet, dass die axiale Anlage gegenüber den Seitenflächen der Halterungen, welche auf der zweiten Seite der Scheibe gelegen sind, zurückgesetzt ist.
  2. Turbinenrad nach Anspruch 1, dadurch gekennzeichnet, dass der Halteflansch (40) eine axiale seitliche Unterstützung auf Seitenflächen der Zähne (16) der Scheibe (12) ausübt.
  3. Turbinenrad nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, dass der Halteflansch (40) eine axiale seitliche Unterstützung auf Seitenflächen der Halterungen (26) ausübt.
  4. Turbinenrad nach einem der Ansprüche 2 und 3, dadurch gekennzeichnet, dass der Halteflansch (40) an den Zähnen (16) der Scheibe oder den Halterungen (26) der Schaufeln mit Vorspannung in Anlage ist.
  5. Turbinenrad nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, dass der Halteflansch (40) eine begrenzte radiale Abmessung aufweist, um nur an unteren Teilen der Zähne (16) der Scheibe oder der Halterungen (26) der Schaufeln in Anlage zu kommen.
  6. Turbinenrad nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die axiale Anlage zwischen den Schaufeln (20) und der Scheibe (12) ohne Verbrauch von axialem Spiel zwischen dem Rotor (10) und einem benachbarten Stator hergestellt ist und aufrechterhalten wird.
  7. Turbinenrad nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der Halteflansch (40) an seinem Umfang eine Überdicke (41), welche eine auskragende Masse bildet, aufweist.
  8. Turbinenrad nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass der Halteflansch (40) an dem Rotor (10) unter axialem Festlegen durch einen Haltering (44) angebracht ist.
  9. Turbinenrad nach Anspruch 8, dadurch gekennzeichnet, dass wenigstens eine ein Inspektionsfenster (10b) bildende Öffnung in dem Rotor (10) ausgebildet ist, um eine Sichtkontrolle der Positionierung des Haltrings (44) zu ermöglichen.
  10. Turbomaschine, die ein Turbinenrad nach einem der Ansprüche 1 bis 9 umfasst.
EP09803867.2A 2008-12-17 2009-12-16 Turbinenrad mit einem axialrückhaltesystem für schaufeln Active EP2366061B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09803867T PL2366061T3 (pl) 2008-12-17 2009-12-16 Koło turbinowe z osiowym systemem utrzymywania łopatek

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0858689A FR2939834B1 (fr) 2008-12-17 2008-12-17 Roue de turbine avec systeme de retention axiale des aubes
PCT/FR2009/052553 WO2010076493A1 (fr) 2008-12-17 2009-12-16 Roue de turbine avec système de rétention axiale des aubes

Publications (2)

Publication Number Publication Date
EP2366061A1 EP2366061A1 (de) 2011-09-21
EP2366061B1 true EP2366061B1 (de) 2017-03-22

Family

ID=40677565

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09803867.2A Active EP2366061B1 (de) 2008-12-17 2009-12-16 Turbinenrad mit einem axialrückhaltesystem für schaufeln

Country Status (11)

Country Link
US (1) US8721293B2 (de)
EP (1) EP2366061B1 (de)
JP (1) JP5497063B2 (de)
KR (1) KR101667827B1 (de)
CN (1) CN102257245B (de)
CA (1) CA2746979C (de)
ES (1) ES2622837T3 (de)
FR (1) FR2939834B1 (de)
PL (1) PL2366061T3 (de)
RU (1) RU2511915C2 (de)
WO (1) WO2010076493A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3123681A1 (fr) * 2021-06-08 2022-12-09 Safran Helicopter Engines Roue de rotor pour une turbomachine d’aéronef

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2963806B1 (fr) * 2010-08-10 2013-05-03 Snecma Dispositif de blocage d'un pied d'une aube de rotor
US9567857B2 (en) 2013-03-08 2017-02-14 Rolls-Royce North American Technologies, Inc. Turbine split ring retention and anti-rotation method
FR3018849B1 (fr) * 2014-03-24 2018-03-16 Safran Aircraft Engines Piece de revolution pour un rotor de turbomachine
FR3021993B1 (fr) * 2014-06-06 2016-06-10 Snecma Procede de dimensionnement d'une turbomachine
FR3026429B1 (fr) * 2014-09-30 2016-12-09 Snecma Aube mobile de turbomachine, comprenant un ergot engageant une entaille de blocage d'un disque de rotor
KR101628613B1 (ko) * 2015-04-01 2016-06-08 두산중공업 주식회사 버켓의 축방향 고정장치
US11085309B2 (en) 2017-09-22 2021-08-10 General Electric Company Outer drum rotor assembly
FR3116298B1 (fr) * 2020-11-16 2023-05-19 Safran Aircraft Engines Disque pour roue mobile de module de turbomachine d’aeronef, comprenant une butee de retention axiale d’aube integree au disque
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
FR3127255A1 (fr) * 2021-09-23 2023-03-24 Safran Aircraft Engines Ensemble rotatif pour turbomachine

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Publication number Priority date Publication date Assignee Title
FR3123681A1 (fr) * 2021-06-08 2022-12-09 Safran Helicopter Engines Roue de rotor pour une turbomachine d’aéronef

Also Published As

Publication number Publication date
CA2746979C (fr) 2017-01-17
RU2011129609A (ru) 2013-01-27
FR2939834A1 (fr) 2010-06-18
CN102257245A (zh) 2011-11-23
PL2366061T3 (pl) 2017-07-31
ES2622837T3 (es) 2017-07-07
RU2511915C2 (ru) 2014-04-10
FR2939834B1 (fr) 2016-02-19
KR20110102908A (ko) 2011-09-19
CA2746979A1 (fr) 2010-07-08
US8721293B2 (en) 2014-05-13
US20110250071A1 (en) 2011-10-13
JP2012512360A (ja) 2012-05-31
EP2366061A1 (de) 2011-09-21
JP5497063B2 (ja) 2014-05-21
KR101667827B1 (ko) 2016-10-19
CN102257245B (zh) 2014-07-16
WO2010076493A1 (fr) 2010-07-08

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