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EP0422433A1 - Dispositif pour la fixation d'aubes de turbine - Google Patents

Dispositif pour la fixation d'aubes de turbine Download PDF

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Publication number
EP0422433A1
EP0422433A1 EP90118255A EP90118255A EP0422433A1 EP 0422433 A1 EP0422433 A1 EP 0422433A1 EP 90118255 A EP90118255 A EP 90118255A EP 90118255 A EP90118255 A EP 90118255A EP 0422433 A1 EP0422433 A1 EP 0422433A1
Authority
EP
European Patent Office
Prior art keywords
support
arrangement according
turbo blades
sections
arrangement
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.)
Withdrawn
Application number
EP90118255A
Other languages
German (de)
English (en)
Inventor
Uwe Schmidt-Eisenlohr
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 Motoren und Turbinen Union Muenchen 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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0422433A1 publication Critical patent/EP0422433A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference

Definitions

  • the invention relates to an arrangement for fastening turbo blades on the circumference of a rotor, in which an outwardly widening support strip is formed on the outer circumference of the rotor and is clasped on both sides by retaining flanges of the turbo blades.
  • the support strip consists of support sections of equal length, arranged alternately, with support beads formed on both sides and intermediate sections without support beads, and the holding flanges have the width of the support sections.
  • the arrangement has the advantage that with simultaneous quick assembly and hot gas shielding of the rotor, a rotationally symmetrical contour can be achieved, and thus no unfavorable stress concentrations occur at some points in the outer area of the rotor.
  • the overall construction can thus be designed to be tension-friendly and unnecessary, weight-increasing reinforcements can be avoided.
  • the holding flanges are preferably arranged radially under each turbo blade and have such a width and wall thickness that the centrifugal forces occurring during operation can be absorbed with the necessary certainty.
  • An advantageous development of the invention provides that at least at one point on the circumference a means for locking the turbo blades in the circumferential direction is attached.
  • This is preferably designed as an axially fixable locking filler fitted in at least one intermediate section.
  • Such means for locking can also be attached to several equally distributed locations on the circumference.
  • Filling pieces are advantageously used on both sides of the intermediate sections in order to achieve a favorable flow contour, and they do not have a supporting function.
  • Another advantageous embodiment of the invention provides that several, but at least two turbo blades with retaining flanges form an integral component. It is expedient to design the assignment of retaining flanges and turbo blades in the same way as for individual blades. This arrangement has the advantage that the assembly effort ver is reduced, and there is the possibility of support in the event of material failure in individual holding flanges. It is also advantageous that the holding flanges are connected to one another via connecting webs on both sides of the support strip. This enables the filler pieces, which are arranged in the intermediate sections, to be fixed. Furthermore, the locking filler piece can be axially fixed via these connecting webs.
  • FIG. 1 shows a partial axial section or cross section through a fastening arrangement, by means of which turbo blades 2 provided on the circumference of a rotor 1 are fastened.
  • the attachment takes place in that on the outer circumference of the rotor 1 a support strip 3 is formed which extends in the circumferential direction and which are clasped by retaining flanges 4a, b formed on the turbo blades 2.
  • the support strip 3 is shown in more detail in Figures 3 and 4.
  • the support strip 3 is constructed from support sections 5 of the same length, alternatingly arranged, and intermediate sections 6 arranged between them.
  • the support bar 3 is shown cut at the level of an intermediate section 6, and it can be seen that the support sections 5 consist of support beads 7 formed on both sides of the support bar 3.
  • FIG. 2 shows a top view of an integral component 8 consisting of two turbo blades 2, in which the two turbo blades 2, which are supported by holding flanges 4a, b, stand on a platform 9 which extends over two divisions of the blades.
  • the support bar 3 lying under the platform 9 is indicated by dashed lines.
  • FIG. 5 shows a cross section through the support strip 3, the outer contour of the platform 9 (FIG. 4) together with the turbo blades 2 being indicated.
  • the support bar 3 is surrounded by the holding flanges 4a, b, while in the area of the intermediate sections 6 locking filler pieces 10 are used which prevent displacement of the holding flanges 4a, b connected to the platform 9 in the circumferential direction.
  • These locking filler pieces 10 do not have to be attached in each intermediate section 6, it may be sufficient to arrange them only in a single intermediate section 6.
  • simple filler pieces 11 or molded elements 16 integrally connected to the platform are used at the outer ends of the components in order to achieve a favorable flow contour.
  • FIGS. 6a and 6b show two sections according to lines A-B from FIG.
  • These support strips 13, as shown in FIG. 6b, are integrally formed on the blade root region 14 of the turbo blades 2 pointing radially inwards and, in cooperation with the retaining tabs 12, serve to fix the locking filler pieces 10 and the simple filler pieces 11.
  • the support strip 13 is preferably radial in this case inner area with two adjacent retaining flanges 4a and 4b connected back-like.
  • FIGS. 7 and 8 show a further preferred embodiment of the invention, in which the two tangential outer ends of the platform 9 are formed diagonally opposite one another as extensions 15, 16 of the holding flanges 4a and 4b.
  • this extension is shown in section along the line VII of Figure 8, it can be seen that it has a cavity 17 for weight reduction.
  • FIG. 9 shows an alternative embodiment of the invention, which differs from the ones described above in the mushroom-shaped shape of the support strip 3a and in the formation of a merely thin wall 18 as a connection in the circumferential direction of adjacent holding flanges 4c.
  • a radially inserted pin 19 is provided in order to prevent the platform 9 from slipping in the circumferential direction with respect to the support bar 3a.
  • FIG. 10 The top view of this embodiment in FIG. 10 shows how the bolt 19 is inserted between two turbo blades 2. Furthermore, the connection of adjacent retaining flanges 4c can be seen through the relatively thin walls 18, as a result of which a smooth contour of the blade root is produced in the circumferential direction.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP90118255A 1989-10-13 1990-09-22 Dispositif pour la fixation d'aubes de turbine Withdrawn EP0422433A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19893934207 DE3934207A1 (de) 1989-10-13 1989-10-13 Anordnung zur befestigung von turboschaufeln
DE3934207 1989-10-13

Publications (1)

Publication Number Publication Date
EP0422433A1 true EP0422433A1 (fr) 1991-04-17

Family

ID=6391402

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90118255A Withdrawn EP0422433A1 (fr) 1989-10-13 1990-09-22 Dispositif pour la fixation d'aubes de turbine

Country Status (2)

Country Link
EP (1) EP0422433A1 (fr)
DE (1) DE3934207A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5638411A (en) * 1991-05-23 1997-06-10 Mitsubishi Denki Kabushiki Kaisha Stuff bit synchronization system
DE19904027A1 (de) * 1999-02-02 2000-08-03 Abb Research Ltd Verdichterrad
EP2762681A1 (fr) * 2013-02-04 2014-08-06 Techspace Aero S.A. Tambour de rotor de turbomachine axiale et turbomachine associée
EP3862571A1 (fr) * 2020-02-06 2021-08-11 ABB Schweiz AG Ventilateur, machine synchrone et procédé de fabrication d'un ventilateur

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1891948A (en) * 1931-10-02 1932-12-27 Gen Electric Elastic fluid turbine
US2157827A (en) * 1937-05-12 1939-05-09 Gen Electric Turbine rotor
US2221685A (en) * 1939-01-18 1940-11-12 Gen Electric Elastic fluid turbine bucket unit
US3826592A (en) * 1971-06-02 1974-07-30 Gen Electric Split locking piece for circumferential dovetail on turbine wheel

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1019318B (de) * 1954-04-28 1957-11-14 Siemens Ag Deckbandbefestigung an Turbinenschaufeln mittels Bajonettverschlusses
GB1069024A (en) * 1964-08-25 1967-05-17 Mitsubishi Heavy Ind Ltd Turbine rotor
DE1957614C3 (de) * 1969-11-15 1974-03-14 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Laufschaufelkranz für Gasturbinentriebwerke mit hoher DrehzahL
GB1479332A (en) * 1974-11-06 1977-07-13 Rolls Royce Means for retaining blades to a disc or like structure
GB2001398A (en) * 1977-07-22 1979-01-31 Rolls Royce Bladed Rotor for Gas Turbine Engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1891948A (en) * 1931-10-02 1932-12-27 Gen Electric Elastic fluid turbine
US2157827A (en) * 1937-05-12 1939-05-09 Gen Electric Turbine rotor
US2221685A (en) * 1939-01-18 1940-11-12 Gen Electric Elastic fluid turbine bucket unit
US3826592A (en) * 1971-06-02 1974-07-30 Gen Electric Split locking piece for circumferential dovetail on turbine wheel

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5638411A (en) * 1991-05-23 1997-06-10 Mitsubishi Denki Kabushiki Kaisha Stuff bit synchronization system
DE19904027A1 (de) * 1999-02-02 2000-08-03 Abb Research Ltd Verdichterrad
EP2762681A1 (fr) * 2013-02-04 2014-08-06 Techspace Aero S.A. Tambour de rotor de turbomachine axiale et turbomachine associée
CN103967840A (zh) * 2013-02-04 2014-08-06 航空技术空间股份有限公司 将轴流涡轮压缩机的叶片连接至压缩机鼓
US20140219803A1 (en) * 2013-02-04 2014-08-07 Techspace Aero S.A. Attaching the Blades of an Axial Turbocompressor to the Compressor Drum
US9739150B2 (en) 2013-02-04 2017-08-22 Safran Aero Boosters Sa Attaching the blades of an axial turbocompressor to the compressor drum
RU2651697C2 (ru) * 2013-02-04 2018-04-23 Сафран Аэро Бустерс Са Барабан ротора осевой турбомашины и турбомашина
CN103967840B (zh) * 2013-02-04 2018-12-18 赛峰航空助推器股份有限公司 将轴流涡轮压缩机的叶片连接至压缩机鼓
EP3862571A1 (fr) * 2020-02-06 2021-08-11 ABB Schweiz AG Ventilateur, machine synchrone et procédé de fabrication d'un ventilateur
WO2021155966A1 (fr) * 2020-02-06 2021-08-12 Abb Schweiz Ag Ventilateur, machine synchrone et procédé de production d'un ventilateur
CN114901952A (zh) * 2020-02-06 2022-08-12 Abb瑞士股份有限公司 风扇、同步电机和生产风扇的方法

Also Published As

Publication number Publication date
DE3934207C2 (fr) 1992-07-16
DE3934207A1 (de) 1991-04-25

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