EP1426560B1 - Dichtung für den Niederdruckverdichter eines Flugtriebwerks - Google Patents

Dichtung für den Niederdruckverdichter eines Flugtriebwerks Download PDF

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Publication number
EP1426560B1
EP1426560B1 EP20020447237 EP02447237A EP1426560B1 EP 1426560 B1 EP1426560 B1 EP 1426560B1 EP 20020447237 EP20020447237 EP 20020447237 EP 02447237 A EP02447237 A EP 02447237A EP 1426560 B1 EP1426560 B1 EP 1426560B1
Authority
EP
European Patent Office
Prior art keywords
gasket
drum
housing
seal
chamber according
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
EP20020447237
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English (en)
French (fr)
Other versions
EP1426560A1 (de
Inventor
André Lhoest
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 Aero Boosters SA
Original Assignee
Techspace Aero SA
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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to DE2002613621 priority Critical patent/DE60213621T2/de
Priority to EP20020447237 priority patent/EP1426560B1/de
Publication of EP1426560A1 publication Critical patent/EP1426560A1/de
Application granted granted Critical
Publication of EP1426560B1 publication Critical patent/EP1426560B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • the present invention relates to a new seal for sealing a chamber in the booster or low-pressure compressor of a turbofan engine type single or double flow.
  • the invention applies whenever a seal is required in the chambers of a turbomachine, in particular at a fan disk.
  • the mounting of the seal is provided by bolting a piece of metal gasket 5 to a specific flange 4 associated with the drum 2.
  • the deformations to which such a flange is subjected in operation involve a requirement of great flexibility for it. Also it is usually done "lace".
  • the realization of this flange involves machining on massive piece with additional material and therefore also extra cost.
  • the bolted connection involves the making of holes in the joint, usually made of aluminum and in the flange, which reduces the life of these parts.
  • a first solution for producing drum / blower seals has been proposed in European Patent Application No. 01870116 (unpublished).
  • a prestressed seal located between the integral flange of the drum and the rotating disc supporting the rotating blades of the fan is held in place, without mechanical attachment, on the one hand with a heel extending the flange and on the other hand by contact with said disk.
  • the tightening of the support face of the seal on the heel is thus achieved by the elasticity of the seal.
  • the present invention aims to provide a solution that is both free from the disadvantages of the state of the art and alternative to the solution already proposed by the Applicant.
  • the present invention relates to a sealing device for a pressurized chamber of a low-pressure compressor belonging to a turbomachine engine, preferably a turbojet or turbofan, comprising a seal ensuring a sealing contact between the inner part of the drum supporting the blades of the engines. compression stages of the primary flow and the rotating disk supporting the rotating vanes of the fan, at a first end of the seal, characterized in that said seal is held at the drum in a housing thereof, an element elastomer being molded on a second end of the seal to fit the shape of said housing.
  • the elastomer element is symmetrical in revolution and concentric with the housing made in the drum.
  • the elastomeric element is made so that it can be compressed by mounting in said housing.
  • the seal is thereby centered without being subjected to constraints.
  • the housing is made in a flange integral with the drum.
  • the elastomer element is a silicone element.
  • the seal may consist of a metal or a light metal alloy, preferably aluminum.
  • Figure 1 shows an axial sectional view for one embodiment of a sealing device according to the state of the art.
  • FIG. 2 represents a perspective view for one embodiment of a sealing device according to the invention.
  • FIG. 3 represents an axial sectional view corresponding to the sealing device of FIG. 2.
  • the idea underlying the present invention is to provide a seal which does not play the role of resilient element and which is therefore not the seat of significant constraints.
  • the new seal device is shown in Figures 2 and 3.
  • the drum 2 comprises a first seal portion 15 shown in Figure 2, which is notched and has notches 8 for exceeding the blades of the fan at their level. heels 10.
  • the support of the drum 2 on the fan disk 1 is at the level of the protuberances 9 and a second seal portion 5.
  • the second seal portion 5 is metal, for example aluminum. It is held in place by its position sandwiched between the fan disc 1, at its curved end 6 and the drum 2 without a flange but in which a housing 7 has been machined to accommodate the other end 6 'of the seal 5.
  • the metal part 5 of the seal at this end is then trapped in an elastomer such as silicone filling the housing 7.
  • the elastomer is molded in the housing of the drum 2, around the end 6 'of the metal gasket 5 and constitutes the first part of the gasket 15.
  • An advantage of the present invention lies in the fact that, given the abandonment of the effect "spring", the metal part of the seal undergoes almost no stress and can be made of a common metal such as aluminum.

Landscapes

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

Claims (5)

  1. Druckraum eines Niederdruckverdichters, der zum Antrieb eines Turbotriebwerks, vorzugsweise eines Turbinenluftstrahltriebwerks oder Turbogebläses gehört, und eine Dichtungsvorrichtung umfasst, bestehend aus einer Dichtung (5), die einen dichten Kontakt zwischen dem inneren Teil der Trommel (2), die die Laufschaufeln der Verdichtungsstufen des Primärstroms trägt, und dem Läufer (1), der die Laufschaufeln des Gebläses trägt, an einem ersten Ende (6) der Dichtung (5) sicherstellt, wobei die besagte Dichtung (5) bei der Trommel (2) in einer Aufnahme (7) derselben gehalten wird, dadurch gekennzeichnet, dass ein Elastomerteil (15) auf ein zweites Ende (6') der Dichtung (5) aufgebracht ist, um sich an die Form der besagten Aufnahme (7) anzupassen.
  2. Druckraum nach Anspruch 1, dadurch gekennzeichnet, dass das Elastomerteil drehsymmetrisch und zur Aufnahme (7) in der Trommel konzentrisch ist, wobei das besagte Elastomerteil (15) so ausgeführt wird, dass es durch den Einbau in die Aufnahme (7) komprimiert werden kann; die Dichtung (5) wird dadurch zentriert, ohne dass sie Spannungen ausgesetzt wird.
  3. Druckraum nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Aufnahme (7) in einem mit der Trommel (2) verbundenen Flansch ausgeführt wird.
  4. Druckraum nach irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Elastomerteil (15) aus Silikon besteht.
  5. Druckraum nach irgendeinem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Dichtung (5) aus Metall oder Leichtmetall, vorzugsweise Aluminium besteht.
EP20020447237 2002-12-03 2002-12-03 Dichtung für den Niederdruckverdichter eines Flugtriebwerks Expired - Lifetime EP1426560B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE2002613621 DE60213621T2 (de) 2002-12-03 2002-12-03 Dichtung für den Niederdruckverdichter eines Flugtriebwerks
EP20020447237 EP1426560B1 (de) 2002-12-03 2002-12-03 Dichtung für den Niederdruckverdichter eines Flugtriebwerks

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20020447237 EP1426560B1 (de) 2002-12-03 2002-12-03 Dichtung für den Niederdruckverdichter eines Flugtriebwerks

Publications (2)

Publication Number Publication Date
EP1426560A1 EP1426560A1 (de) 2004-06-09
EP1426560B1 true EP1426560B1 (de) 2006-08-02

Family

ID=32309545

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20020447237 Expired - Lifetime EP1426560B1 (de) 2002-12-03 2002-12-03 Dichtung für den Niederdruckverdichter eines Flugtriebwerks

Country Status (2)

Country Link
EP (1) EP1426560B1 (de)
DE (1) DE60213621T2 (de)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3708949A1 (de) * 1986-03-21 1987-09-24 Rolls Royce Plc Haltering zur lagesicherung eines bauteils
US4968854A (en) * 1988-11-10 1990-11-06 Vanguard Products Corporation Dual elastomer gasket shield for electronic equipment
CH681043A5 (en) * 1989-07-13 1992-12-31 Balzers Hochvakuum Sealing element with light metal support - has elastomer sealing body forming compound unit with support.
US4982889A (en) * 1989-08-09 1991-01-08 Union Carbide Corporation Floating dual direction seal assembly
FR2695164B1 (fr) * 1992-08-26 1994-11-04 Snecma Turbomachine munie d'un dispositif empêchant une circulation longitudinale de gaz autour des étages d'aubes de redressement.
FR2722240B1 (fr) * 1994-07-06 1996-08-14 Snecma Joint metallique a levre et turbomachine equipee de ce joint
DE60102217T2 (de) * 2001-05-30 2005-01-13 Techspace Aero, Milmort Dichtende Verbindungsplatte

Also Published As

Publication number Publication date
DE60213621T2 (de) 2007-03-08
DE60213621D1 (de) 2006-09-14
EP1426560A1 (de) 2004-06-09

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