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EP1092081B1 - Rotor pour turbomachine - Google Patents

Rotor pour turbomachine Download PDF

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Publication number
EP1092081B1
EP1092081B1 EP99939943A EP99939943A EP1092081B1 EP 1092081 B1 EP1092081 B1 EP 1092081B1 EP 99939943 A EP99939943 A EP 99939943A EP 99939943 A EP99939943 A EP 99939943A EP 1092081 B1 EP1092081 B1 EP 1092081B1
Authority
EP
European Patent Office
Prior art keywords
flange
rotor
accordance
several
recesses
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.)
Expired - Lifetime
Application number
EP99939943A
Other languages
German (de)
English (en)
Other versions
EP1092081A1 (fr
Inventor
Hermann Klingels
Martin Fischer
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 EP1092081A1 publication Critical patent/EP1092081A1/fr
Application granted granted Critical
Publication of EP1092081B1 publication Critical patent/EP1092081B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps

Definitions

  • the invention relates to a rotor for a turbomachine, with at least two bladed Steps whose discs are detachably connected to each other.
  • Turbomachinery rotors generally have a plurality of vaned blades Stages whose discs in different ways, e.g. by welding or releasably connected by screwing, with each other. Present will be considered only releasably interconnected stages.
  • the discs are substantially in the axial direction extending, cylindrical or conical shells on, at the end portions thereof each disc-annular flanges are provided, to which adjacent Slices with screws, stud bolts od. Like. Are connected. If one Interstage seal is not integrated in the shells, it is between each sandwiched the flanges. Such a connection can only be at Relatively low peripheral speed components, e.g. slowly running low-pressure turbines, use as the centrifugal forces at for high peripheral speeds designed discs too high hoop stresses in the flange connection. The holes in the flanges make local Voltage increments causing notching and restrict the cyclic Durable life of the component.
  • DE-OS 2 104 172 discloses a turbine rotor and a method for its production, at the adjacent discs with inwardly directed flanges with aligned bolt holes through which a bolt is passed, clamped together are.
  • the problem is that the bolt holes in the Flange represent local stress risers causing notching and the limit cyclic life of the rotor.
  • a disc In a further known rotor, a disc has bores through which with adjacent discs, with cylindrical or conical shells with Have flanges, is connected by screwing.
  • the disk body limited the radial expansion of the joint due to centrifugal force.
  • the problem is that the holes in the highly loaded disk body represent life-limiting notch sites.
  • the invention has for its object to provide a rotor for a turbomachine to create the genus described above, in which the discs detachable with each other be connected without extreme voltage increases by notching occur in the disc.
  • the first flange extends axially spaced from the side surface of first disc to form a gap radially inward.
  • the first flange is designed as a disc ring, which has recesses along its inner end or peripheral edge.
  • the recesses are opened inwards, so that through the bolts generated centrifugal force can be absorbed by the edge surface of the recesses can.
  • the recesses are equidistant along the peripheral edge are arranged.
  • a slot or another recess can be provided.
  • a flange portion of an intermediate stage seal is between each the first and second flange clamped, wherein the flange portion of the Interstage seal preferred to the recesses of the first flange has aligned bores, which the bolts in the radial direction during assembly fix.
  • the bolts facing at their the first disc Ends a transverse section extending at right angles to its longitudinal axis have, with which they are supported on an inner side surface of the first flange.
  • the bolts are preferably T-head bolts.
  • the distance of the first flange to the side surface of the first disc as small as possible, but larger than the thickness of the transverse section of the bolt to to avoid a pressure point on the highly loaded, first disc.
  • the flange of an adjacent disc has at its radially inner end a substantially axially extending support portion on, on which the cross section of the bolt is supported, so as to prevent rotation to create a bolt.
  • the first disc on both side surfaces a first flange, so that in this way, the discs of rotors detachably connect with more than two levels.
  • Fig. 1 shows a longitudinal section of an embodiment of the invention Rotor for a turbomachine, which has three stages.
  • the steps are each with a blade 1, 2 and 3 and a first disc 4 and two adjacent Slices 5,6 provided.
  • the first disc 4 has at its two side surfaces 7,8 each have a flange 9 and 10, respectively.
  • the flanges 9,10 extend with a axial distance A from their inner side surfaces 11,12 to the side surfaces 7,8 the first disc 4. In this way, between the first disc 4 and the Flanges 9,10 a gap Z, which is open in the radial direction inwards.
  • the distance A is to be kept as small as possible, around the radial expansion of the flanges 9,10 and the flange to be limited by the body of the disc 4.
  • a transverse section 13 engages (Screw) bolt 14 in the space Z and rests on the Tensioning / bolting respectively to the inner side surface such as e.g. 12, the Flange 10 from.
  • the disks 5, 6 adjacent to the middle, first disk 4 each face each other extending substantially in the axial direction, cylindrical shells 16, which also may be formed cone-shaped.
  • the bowls 16 have on their to the Slices 5.6 distal ends each have a second flange 17, each with the Flanges 9,10 of the first disc 4 by (screw) bolt 14 or the like. tightly clamped becomes.
  • the second flanges 17 of the disks 5, 6 are each closed substantially in the axial direction extending support portion 18 at which the Transverse portions 13 of the bolts 14 can be supported, whereby a rotation of the bolt 14 is prevented. This ensures that when mounting or tightening the (screw) bolt 14 no pressure points on the highly loaded, first discs 4 occur.
  • each intermediate stage seal 19 with her Flange portion 20 clamped and releasably secured.
  • the intermediate stage seals Alternatively, 19 may also be integral with the discs 5, 6 or their shells 16 may be arranged.
  • Fig. 2 shows a cut and broken cross-sectional view along the line II-II of Fig. 1, in the upper partial section of the flange 9 shown in a plan view is.
  • the flange 9 is formed as a disc ring, on the inner Stir n-area or peripheral edge 21 in the radial direction inwardly open, slot-like Recesses 15 are provided.
  • a recess 15 is a (screw) bolt 14 used, the transverse section 13 is shown in dashed lines. After mo n-ting this is supported on the inner side surface 11 of the flange 9.
  • a bore 22 provided for relief, which the notch factor due to the recess 15th decreases.
  • the holes 22 as slots, more Au savings savings or the like. be educated.
  • Fig. 2 In the lower part of Fig. 2 is the disc-ring-shaped Flange portion 20 of the intermediate stage seal 19 shown, the holes 23rd having.
  • the holes 23 are aligned with the recesses 15 in the flanges 9,10 of the first disc 4 as well as corresponding holes 24 in the second Flanges 17 from the adjacent to the first disc 4 discs 5.6.
  • the holes 23 in the flange portion 20 of the interstage seal 19 radially inwardly open, with their opening size smaller than her Diameter is so as to a radial fixation of the (screw) bolt 14 in the To assure assembly.
  • the holes 23 as closed Be formed holes.
  • every second stage will have one less a flange 9 and 10 having the first disc 4 provided.
  • Fig. 3 shows a further embodiment of the rotor according to the invention, in the radius R at the transition between the inner side surface 8 of the first Slice 4 and the flange 10 and its inner side surface 12 of strength s-found is enlarged.
  • the distance A between the side surface 8 of the first disc 4 and the inner side surface 12 of the flange 10 is larger, has the (screw) bolt 14 a shear ring or collar 25, which on an outer Side surface 26 of the flange 10 rests and an axial displacement of the (Screw) bolt 14 prevents so that the transverse sections 13 during assembly not be pressed against the first disc 4 and e-hen their protection against Verdr to lose.

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

Claims (13)

  1. Rotor pour une turbomachine, comprenant au moins deux étages équipés de pales, turbomachine dont les disques (4, 5, 6) sont reliés entre eux de façon amovible, où un premier disque (4) comprend, au moins au niveau d'une surface latérale (7, 8), une première bride (9, 10) comprenant sa surface latérale intérieure (11, 12) dont le disque est espacé le moins possible, laquelle bride est reliée à une seconde bride (17) d'un disque voisin (5, 6), par des boulons (14) présentant à chaque fois une Section transversale (13), où les sections transversales (13), après le montage, sont en appui sur la surface latérale intérieure (11, 12) de la première bride (9, 10), et où la première bride (9, 10) du premier disque (4) est conformée comma un anneau de disque qui comprend, le long de son bord périphérique intérieur (21), des évidements ouverts (15) vers l'intérieur, dans le sens radial,
    caractérisé en ce que la seconde bride (17) comprend, sur le disque voisin (5, 6), un segment support (18) s'étendant pratiquement en direction axiale, segment support sur lequel sont en appui les sections transversales (13) des boulons (14).
  2. Rotor selon la revendication 1, caractérisé en ce que la première bride (9, 10) s'étend vers l'intérieur, dans le sens radial, en comportant un espacement axial (A) par rapport à la surface latérale (7, 8) du premier disque (4).
  3. Rotor selon la revendication 1 ou 2, caractérisé en ce que les évidements (15) sont disposés de façon équidistante.
  4. Rotor selon l'une quelconque ou plusieurs des revendications précédentes, caractérisé en ce que l'anneau de disque (9, 10) comprend à chaque fois, entre les évidements (15), un perçage ou un évidement (22).
  5. Rotor selon l'une quelconque ou plusieurs des revendications précédentes, caractérisé en ce que la seconde bride (17) d'un disque voisin (5, 6) comprend des perçages alignés (24) par rapport aux évidements (15) d'une première bride (9, 10).
  6. Rotor selon l'une quelconque ou plusieurs des revendications précédentes, caractérisé en ce qu'un segment de bride (20) d'une garniture d'étanchéité d'étage intermédiaire (19) est serré à chaque fois entre la première bride et la seconde bride (9, 10 et 17).
  7. Rotor selon la revendication 6, caractérisé en ce que le segment de bride (20) de la garniture d'étanchéité d'étage intermédiaire (19) comprend des perçages alignés (23) par rapport aux évidements (15) de la première bride (9, 10).
  8. Rotor selon la revendication 7, caractérisé en ce que les perçages (23) fixent les boulons (14) en direction radiale.
  9. Rotor selon l'une quelconque ou plusieurs des revendications précédentes, caractérisé en ce que les boulons (14) comprennent, au niveau de leurs extrémités tournées vers le premier disque (4), une section transversale (13) s'étendant perpendiculairement à leur axe longitudinal.
  10. Rotor selon l'une quelconque ou plusieurs des revendications précédentes, caractérisé en ce que les boulons (14) sont des boulons à tête en T.
  11. Rotor selon l'une quelconque ou plusieurs des revendications précédentes, caractérisé en ce que l'espacement (A) de la première bride (9, 10), par rapport à la surface latérale (7, 8) du premier disque (4), est plus important que l'épaisseur de la section transversale (13).
  12. Rotor selon l'une quelconque ou plusieurs des revendications précédentes, caractérisé en ce que le boulon (14) comprend un épaulement (25) qui est en appui sur une surface latérale extérieure (26) de la première bride (9, 10).
  13. Rotor selon l'une quelconque ou plusieurs des revendications précédentes, caractérisé en ce que le premier disque (4) comprend une première bride (9, 10) sur les deux surfaces latérales (7, 8).
EP99939943A 1998-06-27 1999-06-24 Rotor pour turbomachine Expired - Lifetime EP1092081B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19828817 1998-06-27
DE19828817A DE19828817C2 (de) 1998-06-27 1998-06-27 Rotor für eine Turbomaschine
PCT/DE1999/001840 WO2000000719A1 (fr) 1998-06-27 1999-06-24 Rotor pour turbomachine

Publications (2)

Publication Number Publication Date
EP1092081A1 EP1092081A1 (fr) 2001-04-18
EP1092081B1 true EP1092081B1 (fr) 2003-07-30

Family

ID=7872288

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99939943A Expired - Lifetime EP1092081B1 (fr) 1998-06-27 1999-06-24 Rotor pour turbomachine

Country Status (6)

Country Link
US (1) US6499957B1 (fr)
EP (1) EP1092081B1 (fr)
JP (1) JP2002519564A (fr)
CA (1) CA2335964A1 (fr)
DE (2) DE19828817C2 (fr)
WO (1) WO2000000719A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10837284B2 (en) 2017-08-11 2020-11-17 MTU Aero Engines AG Rotor for a turbomachine

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20011961A1 (it) * 2001-09-20 2003-03-20 Nuovo Pignone Spa Flangia migliorata di accoppiamento tra compressore assiale e gruppo di dischi rotorici di alta pressione in una turbina a gas
RU2224892C2 (ru) * 2002-05-06 2004-02-27 Открытое акционерное общество "Авиадвигатель" Газотурбинный двигатель с двухступенчатой газовой турбиной
FR2857419B1 (fr) * 2003-07-11 2005-09-23 Snecma Moteurs Liaison amelioree entre disques aubages sur la ligne rotor d'un compresseur
DE102004016244B4 (de) 2004-04-02 2007-08-23 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
FR2868814B1 (fr) * 2004-04-09 2009-12-18 Snecma Moteurs Dispositif d'assemblage de brides annulaires, en particulier dans une turbomachine
FR2931873B1 (fr) * 2008-05-29 2010-08-20 Snecma Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier,circuit de refroidissement d'un disque de turbine d'un tel ensemble.
US8043062B2 (en) * 2008-09-04 2011-10-25 Mitsubishi Heavy Industries, Ltd. Turbine rotor and turbine having the same
DE102008048006B4 (de) 2008-09-19 2019-02-21 MTU Aero Engines AG Wellenleistungstriebwerk, insbesondere für ein Luftfahrzeug, mit einem Kühlgasführungssystem im Bereich der Befestigungsflansche der Rotorscheiben
FR2961249B1 (fr) * 2010-06-10 2014-05-02 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine
US9004871B2 (en) * 2012-08-17 2015-04-14 General Electric Company Stacked wheel assembly for a turbine system and method of assembling
US9279325B2 (en) * 2012-11-08 2016-03-08 General Electric Company Turbomachine wheel assembly having slotted flanges
US11073044B2 (en) * 2013-01-21 2021-07-27 Raytheon Technologies Corporation Adjustable floating oil channel for gas turbine engine gear drive
US10465519B2 (en) * 2013-10-17 2019-11-05 Pratt & Whitney Canada Corp. Fastening system for rotor hubs
US10502059B2 (en) * 2015-02-02 2019-12-10 United Technologies Corporation Alignment tie rod device and method of utilization
US10316681B2 (en) * 2016-05-31 2019-06-11 General Electric Company System and method for domestic bleed circuit seals within a turbine
FR3062415B1 (fr) * 2017-02-02 2019-06-07 Safran Aircraft Engines Rotor de turbine de turbomachine a ventilation par lamage
US11428124B2 (en) 2018-11-21 2022-08-30 Raytheon Technologies Corporation Flange stress-reduction features
CN112360886B (zh) * 2020-10-28 2022-03-25 中国航发湖南动力机械研究所 盘轴连接结构
CN115614324B (zh) * 2022-11-22 2023-05-05 中国航发四川燃气涡轮研究院 基于变截面螺栓连接的压气机转子多级轮盘连接结构
EP4575190A3 (fr) * 2023-12-22 2025-10-29 Rohr, Inc. Ensemble de fixation pour un corps central de moteur à turbine à gaz et procédé de fixation d'un corps central
CN119084084B (zh) * 2024-09-09 2025-11-21 中国航发沈阳发动机研究所 一种航空发动机高压涡轮盘与轴连接结构

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2614796A (en) * 1950-03-30 1952-10-21 Westinghouse Electric Corp Rotor construction
US3688371A (en) * 1970-04-30 1972-09-05 Gen Electric The method of manufacturing compositely formed rotors
FR2552159B1 (fr) * 1983-09-21 1987-07-10 Snecma Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
CA1209482A (fr) * 1983-12-22 1986-08-12 Douglas L. Kisling Rotor bi-etage a circulation amelioree du fluide caloporteur
FR2607866B1 (fr) * 1986-12-03 1991-04-12 Snecma Axes de fixation de rotors de turbomachine, procede de montage et rotors ainsi montes
US5052891A (en) * 1990-03-12 1991-10-01 General Motors Corporation Connection for gas turbine engine rotor elements
US5350278A (en) * 1993-06-28 1994-09-27 The United States Of America As Represented By The Secretary Of The Air Force Joining means for rotor discs
US5388963A (en) * 1993-07-02 1995-02-14 United Technologies Corporation Flange for high speed rotors
GB2303188B (en) * 1995-07-13 1999-04-28 Bmw Rolls Royce Gmbh An assembly of two turbine rotor discs

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10837284B2 (en) 2017-08-11 2020-11-17 MTU Aero Engines AG Rotor for a turbomachine

Also Published As

Publication number Publication date
CA2335964A1 (fr) 2000-01-06
DE59906444D1 (de) 2003-09-04
WO2000000719A1 (fr) 2000-01-06
JP2002519564A (ja) 2002-07-02
DE19828817A1 (de) 1999-12-30
US6499957B1 (en) 2002-12-31
EP1092081A1 (fr) 2001-04-18
DE19828817C2 (de) 2000-07-13

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