EP4095357B1 - Berstschutz-vorrichtung für einen luftfahrtventilator -oder kompressor - Google Patents

Berstschutz-vorrichtung für einen luftfahrtventilator -oder kompressor

Info

Publication number
EP4095357B1
EP4095357B1 EP22172238.2A EP22172238A EP4095357B1 EP 4095357 B1 EP4095357 B1 EP 4095357B1 EP 22172238 A EP22172238 A EP 22172238A EP 4095357 B1 EP4095357 B1 EP 4095357B1
Authority
EP
European Patent Office
Prior art keywords
fan
compressor
casing
bosses
bladed wheel
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
EP22172238.2A
Other languages
English (en)
French (fr)
Other versions
EP4095357A1 (de
Inventor
Claude PENDARIES
François Gauharou
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 Ventilation Systems SAS
Original Assignee
Safran Ventilation Systems SAS
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 Safran Ventilation Systems SAS filed Critical Safran Ventilation Systems SAS
Publication of EP4095357A1 publication Critical patent/EP4095357A1/de
Application granted granted Critical
Publication of EP4095357B1 publication Critical patent/EP4095357B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips

Definitions

  • the technical background includes, in particular, documents US-A1-5,431,532 , US-A1-2011/0052383 , US-A1-4,902,201 , JP-2006177364A And US-A1-2019/0106996A1 .
  • FIG. 1 shows a device 10 of this type, the casing being designated by the reference 12 and the bladed wheel by the reference 14.
  • the present invention makes it possible to remedy this problem thanks to a simple, effective and economical solution.
  • the present invention also relates to a fan or compressor, in particular for an aeronautical application, comprising at least one device as described above.
  • the casing 12 has a generally tubular shape along the axis A. In the example shown, it has a straight shape but could alternatively have a bent shape.
  • the casing 12 comprises an internal annular surface 12a, here cylindrical, and an external annular surface 12b, here also cylindrical.
  • the bladed wheel 14 is schematically represented by a rectangle at the figure 2 .
  • This wheel 14 has an axial length or dimension noted L1.
  • Each of these bosses 22 has a generally square or rectangular axial section shape.
  • Each boss 22 has an axial length or dimension L2 and a thickness or radial dimension R2.
  • the two bosses 22 are identical here.
  • L2 preferably represents between 5 and 30% of L1.
  • Each boss 22 comprises an external cylindrical surface 22a and radial lateral surfaces 22b (cf. figure 6 ).
  • the bosses 22 define between them an annular space E which is empty in the example shown.
  • the bosses 22 are connected to each other by a tubular wall 12c of the casing 12 which has a constant thickness E3 over its entire axial extent.
  • the tubular wall 12a comprises free and bare internal 12ca and external 12cb cylindrical surfaces. In other words, this wall 12c is devoid of local excess thickness and in particular of stiffening ribs.
  • R2 preferably represents between 200% and 1000% of E3.
  • the retaining ring 20 extends around the bosses 22 and comprises an upstream edge 20a which covers the upstream boss 22 and in particular its surface 22a, and is fixed to this upstream boss.
  • the ring 20 comprises a downstream edge 20b which covers the downstream boss 22 and in particular its surface 22a, and is fixed to this downstream boss.
  • the ring 20 has a generally cylindrical and tubular shape and may have a constant thickness E4 over its entire axial dimension. This thickness E4 is for example between 1 and 5 mm.
  • the upstream and downstream edges 20a, 20b of the ring 20 can be glued to the bosses 22.
  • the retaining ring 20 may be continuous over 360° or may be formed by winding a strip of material whose circumferential ends 20a overlap. These ends may undergo a grooving operation.

Landscapes

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

Claims (10)

  1. Lüfter oder Verdichter, insbesondere für die Luftfahrtindustrie, wobei dieser Lüfter oder Verdichter eine Vorrichtung aufweist, umfassend:
    - ein ringförmiges Gehäuse (12), das eine Hauptachse (A) aufweist und einen inneren Zirkulationskanal für einen Gasstrom entlang dieser Achse definiert,
    - ein beschaufeltes Rad (14), das im Inneren des Gehäuses (12) montiert ist und eine Drehachse aufweist, die mit der Achse (A) des Gehäuses zusammenfällt,
    wobei der Lüfter oder Verdichter weiter ein System (18) zum Zurückhalten von Trümmern im Falle eines Bruchs des beschaufelten Rades (14) umfasst, wobei dieses System einen Haltering (20) aufweist, der um das Gehäuse (12) herum montiert ist, wobei das Gehäuse (12) zwei ringförmige, radial nach außen vorstehende Ausbuchtungen (22) aufweist, die jeweils stromaufwärts und stromabwärts des beschaufelten Rades (14) angeordnet sind und an denen stromaufwärtige und stromabwärtige Ränder (20a, 20b) des Rückhaltesystems (20) angebracht und befestigt sind,
    und dadurch gekennzeichnet, dass die stromaufwärtigen (20a) und stromabwärtigen (20b) Ränder des Halteringes (20) Öffnungen umfassen, die mit Gewindebohrungen (24) der Ausbuchtungen (22) zur Montage von Befestigungselementen (26), wie Schrauben oder Nieten, ausgerichtet sind.
  2. Lüfter oder Verdichter nach Anspruch 1, wobei das Gehäuse (12) zwischen den beiden Ausbuchtungen (22) und um das beschaufelte Rad (14) herum eine rohrförmige Wand (12c) umfasst, die eine konstante radiale Dicke (E3) aufweist.
  3. Lüfter oder Verdichter nach Anspruch 2, wobei die rohrförmige Wand (12c) freie und blanke zylindrische innere (12ca) und äußere (12cb) Oberflächen umfasst.
  4. Lüfter oder Verdichter nach einem der vorstehenden Ansprüche, wobei das Gehäuse (12) aus Metall oder Verbundwerkstoff ausgeführt ist und/oder der Haltering (20) aus Metall oder Verbundwerkstoff ausgeführt ist.
  5. Lüfter oder Verdichter nach einem der Ansprüche 1 bis 4, wobei die stromaufwärtigen (20a) und stromabwärtigen (20b) Ränder des Halteringes (20) weiter an den Ausbuchtungen (22) geklebt sind.
  6. Lüfter oder Verdichter nach einem der vorstehenden Ansprüche, wobei der Haltering (20) über 360° durchgehend ist oder durch Umwickeln eines Materialstreifens gebildet ist, dessen Umfangsenden sich überlappen.
  7. Lüfter oder Verdichter nach einem der vorstehenden Ansprüche, wobei das beschaufelte Rad einen Außendurchmesser von weniger als oder gleich 1 Meter aufweist.
  8. Lüfter oder Verdichter nach einem der vorstehenden Ansprüche, wobei die Ausbuchtungen (22) jeweils eine axiale Abmessung (L2) aufweisen, die zwischen 5 und 30 % einer maximalen axialen Abmessung (L1) des beschaufelten Rades (14) darstellt.
  9. Lüfter oder Verdichter nach einem der vorstehenden Ansprüche, wobei die Ausbuchtungen (22) jeweils eine radiale Abmessung (R2) aufweisen, die zwischen 200 % und 1000 % einer radialen Dicke (E3) des Gehäuses (14) zwischen den Ausbuchtungen (22) darstellt.
  10. Lüfter oder Verdichter nach einem der vorstehenden Ansprüche, wobei der Haltering eine radiale Dicke zwischen 1 und 5 mm aufweist.
EP22172238.2A 2021-05-11 2022-05-09 Berstschutz-vorrichtung für einen luftfahrtventilator -oder kompressor Active EP4095357B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR2104986A FR3122900A1 (fr) 2021-05-11 2021-05-11 Dispositif pour la realisation d’un ventilateur ou compresseur pour l’industrie aeronautique

Publications (2)

Publication Number Publication Date
EP4095357A1 EP4095357A1 (de) 2022-11-30
EP4095357B1 true EP4095357B1 (de) 2025-08-13

Family

ID=76284028

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22172238.2A Active EP4095357B1 (de) 2021-05-11 2022-05-09 Berstschutz-vorrichtung für einen luftfahrtventilator -oder kompressor

Country Status (3)

Country Link
US (1) US11879344B2 (de)
EP (1) EP4095357B1 (de)
FR (1) FR3122900A1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3767081A1 (de) * 2019-07-15 2021-01-20 ABB Schweiz AG Turbinengehäuse mit einem spannungsarmen verbindungsflansch und abgasturbine mit einem solchen turbinengehäuse
FR3149053A1 (fr) 2023-05-24 2024-11-29 Safran Ventilation Systems Dispositif de ventilation ou de compression pour l’industrie aeronautique

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3814954A1 (de) * 1988-05-03 1989-11-16 Mtu Muenchen Gmbh Berstschutzring fuer ein triebwerksgehaeuse
US5431532A (en) * 1994-05-20 1995-07-11 General Electric Company Blade containment system
US7246990B2 (en) * 2004-12-23 2007-07-24 General Electric Company Composite fan containment case for turbine engines
US8757958B2 (en) * 2009-08-31 2014-06-24 United Technologies Corporation Composite fan containment case
US20120195746A1 (en) * 2011-01-27 2012-08-02 General Electric Company Turbomachine service assembly
US10167727B2 (en) * 2014-08-13 2019-01-01 United Technologies Corporation Gas turbine engine blade containment system
FR3031469B1 (fr) * 2015-01-14 2017-09-22 Snecma Carter en materiau composite a matrice organique auto-raidi
GB201813081D0 (en) * 2018-08-10 2018-09-26 Rolls Royce Plc Efficient gas turbine engine
EP3767081A1 (de) * 2019-07-15 2021-01-20 ABB Schweiz AG Turbinengehäuse mit einem spannungsarmen verbindungsflansch und abgasturbine mit einem solchen turbinengehäuse

Also Published As

Publication number Publication date
EP4095357A1 (de) 2022-11-30
US20220364479A1 (en) 2022-11-17
FR3122900A1 (fr) 2022-11-18
US11879344B2 (en) 2024-01-23

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