EP1111246B1 - Steifes Ringteil - Google Patents

Steifes Ringteil Download PDF

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Publication number
EP1111246B1
EP1111246B1 EP19990870274 EP99870274A EP1111246B1 EP 1111246 B1 EP1111246 B1 EP 1111246B1 EP 19990870274 EP19990870274 EP 19990870274 EP 99870274 A EP99870274 A EP 99870274A EP 1111246 B1 EP1111246 B1 EP 1111246B1
Authority
EP
European Patent Office
Prior art keywords
ferrule
barrel
rectifier
guide vane
stage
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
EP19990870274
Other languages
English (en)
French (fr)
Other versions
EP1111246A1 (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 DE69910408T priority Critical patent/DE69910408T2/de
Priority to EP19990870274 priority patent/EP1111246B1/de
Publication of EP1111246A1 publication Critical patent/EP1111246A1/de
Application granted granted Critical
Publication of EP1111246B1 publication Critical patent/EP1111246B1/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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like

Definitions

  • the present invention relates to a part of the shell provided with a device which allows the stiffen.
  • This ferrule can be the inner ferrule or the outer shell of a compressor, preferably a coaxial compressor.
  • Coaxial compressors are well known in itself, and are used in several types of application. In particular, they are used in double motors body, turbofans or turbojets. We also note their presence in power plants. These compressors low or high pressure basically consist of several stages of rotating blades separated by stages rectifiers which aim to reposition the vector speed of the fluid leaving the previous stage before send it to the next compartment. Such a compressor is for example known from patent application EP 0 277 884 A.
  • rectifier stages are made up essentially fixed vanes connecting an outer shell to an inner shell, both concentric.
  • the problem is that these rectifier stages are subject to relatively significant efforts due inter alia to vibrations which quickly cause wear and tear tired.
  • the present invention aims to provide a new solution that would stiffen the floor rectifier, and in particular the first floor of the compressor, which does not require the use of a surplus material and which therefore reduces the cost Manufacturing.
  • the present invention relates to a ferrule made of a sheet adhering to a part elastomer, characterized in that said elastomer part includes one or more independent metallic elements of the sheet metal of the shell which are at least partially embedded in said elastomeric part. These elements metallic stiffen said ferrule and are therefore called “stiffeners”.
  • the present invention also relates to a rectifier stage comprising two ferrules, a ferrule inner and outer ferrule, at least one of these ferrules being a ferrule according to the invention. These ferrules are connected to each other by a series of fixed vanes.
  • said ferrule is the inner ferrule which comprises at minus a metallic element, possibly totally submerged in said elastomeric part.
  • said ferrule is the outer ferrule which comprises at at least one metallic element partially embedded in said elastomeric part.
  • the present invention relates to the use of this rectifier stage as the first stage rectifier in a coaxial compressor, present for example in a turbofan.
  • Figure 1 shows a general view of the compression stage of a turbofan.
  • Figure 2 shows a detail of the figure 1 showing the stiffening device of the rectifiers at the inner shell.
  • FIG. 3 represents a device for stiffening of an inner ferrule of a rectifier according to a first preferred form of the invention.
  • FIG. 4 represents a device for stiffening of the outer shell of a rectifier according to another preferred form of the invention.
  • Figure 1 shows the compression stage of a turbofan.
  • This compression stage is composed of two types of parts: on the one hand, the moving parts which are essentially constituted by the rotor 1 provided with blades mobile 3, on the other hand the fixed parts constituting the rectifier stages 2 which are essentially constituted by an inner ferrule 4, an outer ferrule 5 and a series of fixed vanes 6 connecting said ferrules 4 and 5.
  • the outer shell 5 is common to several successive rectifier stages, while that the inner ferrules 4 and 4 'are specific to each rectifier stage 2, 2 ', ...
  • these interior ferrules 4 are in the form of shaped metal sheets rings, while the fixed blades 6 correspond to simple metal sheets radially connecting a ferrule inner 4 to an outer shroud 5.
  • a room elastomer 7 is present so as to secure the blade fixed 6 to the inner shell 4.
  • This elastomer part 7 also acts as a joint between two floors successive.
  • the gas first passes through the first stage rectifier 2 of the compressor where its speed vector is repositioned to be driven by the first floor rotating blades 3 before reaching the second stage rectifier 2 'to be repositioned again.
  • the gas thus undergoes a training cycle - repositioning at after which its kinetic energy decreases gradually as its pressure increases.
  • stairs 8 are machined in the sheet of the inner shell 4 to stiffen said ferrule, and in particular the first stage rectifier 2.
  • the alternative proposed by this invention consists in stiffening a ferrule by proposing to use a simple sheet for this one (therefore without bandage or stairs).
  • FIG 3 shows the principle of stiffening of an inner shell according to a first embodiment of the present invention.
  • an elastomer part 7 acting as a seal and support at fixed dawn 6 is conventionally arranged on said inner ferrule 4.
  • elastomer 7 acting as a seal and support at fixed dawn 6 is conventionally arranged on said inner ferrule 4.
  • metallic element 10 which thus indirectly stiffen said ferrule interior 4 and therefore the entire rectifier stage 2 in its together. Therefore, this metallic element is called more commonly stiffener.
  • this metal element 10 is independent of the sheet of the inner shell 4.
  • the elastomer part 7 which allows conventionally securing a fixed vane 6 of the rectifier to said inner ferrule 4 without direct contact is maintained. This avoids potential faults in the air flow from a weld or rivet.
  • the first important advantage of the device according to the invention resides in the machining of the ferrule itself, which is therefore particularly simplified. Indeed, it is no longer necessary to offer bandages or stairs. Because of this, the device is less expensive and safer than the solutions proposed according to the state of the art.
  • Another advantage of such a device is that it minimizes controls, in particular by compared to a solution requiring soldering.
  • Such a device using an element stiffener according to the present invention offers a large choice in the material that can be used.
  • the metal element 10 is completely embedded in the elastomer part 7 present under the sheet of the ferrule interior 4, but it may be only partially embedded in the elastomeric part.
  • FIG. 4 represents a device for stiffening of the outer shell 5 of a stage rectifier according to a second preferred embodiment according to the invention.
  • a piece in elastomer 17 playing the role of joint allows to join the fixed blade 6 at the outer shell 5 of the stage rectifier 2.
  • this elastomer part 17 is partially embedded at least one metallic element 12 which allows to indirectly stiffen this outer shell 5 and therefore the rectifier stage as a whole.
  • the element metallic 12 is independent of the sheet of the ferrule exterior 5.
  • the element metallic 12 is partially embedded in the room elastomer 17 under the sheet of the outer shell 5, but he could also be totally drowned.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Exhaust Gas After Treatment (AREA)

Claims (6)

  1. Ring (4, 5), bestehend aus einem Blech, an dem ein Elastomerteil (7, 17) haftet, dadurch gekennzeichnet, dass dieses Elastomerteil (7, 17) ein oder mehrere Metallteile (10, 12) enthält, die vom Blech des Rings (4, 5) unabhängig sind und die zumindest teilweise in das besagte Elastomerteil (7, 17) eingebettet sind und die die Versteifung des besagten Rings ermöglichen.
  2. Leitapparat (2), der zwei Ringe umfasst, einen Innenring (4) und einen Außenring (5), die durch eine Leitschaufel (6) miteinander verbunden sind, dadurch gekennzeichnet, dass wenigstens einer dieser Ringe ein Ring nach Anspruch 1 ist.
  3. Leitapparat nach Anspruch 2, dadurch gekennzeichnet, dass der besagte Ring der Innenring (4) ist.
  4. Leitapparat nach Anspruch 2, dadurch gekennzeichnet, dass der besagte Ring der Außenring (5) ist.
  5. Leitapparat nach Anspruch 2, dadurch gekennzeichnet, dass beide Ringe Ringe gemäß Anspruch 1 sind.
  6. Verwendung des Leitapparats nach einem der Ansprüche 2 bis 5 als Leitapparat in einem koaxialen Verdichter, der sich vorzugsweise in einem Turboventilator befindet.
EP19990870274 1999-12-21 1999-12-21 Steifes Ringteil Expired - Lifetime EP1111246B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE69910408T DE69910408T2 (de) 1999-12-21 1999-12-21 Steifes Ringteil
EP19990870274 EP1111246B1 (de) 1999-12-21 1999-12-21 Steifes Ringteil

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19990870274 EP1111246B1 (de) 1999-12-21 1999-12-21 Steifes Ringteil

Publications (2)

Publication Number Publication Date
EP1111246A1 EP1111246A1 (de) 2001-06-27
EP1111246B1 true EP1111246B1 (de) 2003-08-13

Family

ID=8243946

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19990870274 Expired - Lifetime EP1111246B1 (de) 1999-12-21 1999-12-21 Steifes Ringteil

Country Status (2)

Country Link
EP (1) EP1111246B1 (de)
DE (1) DE69910408T2 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2400160A1 (de) 2010-06-23 2011-12-28 Techspace Aero S.A. Leichterer Rotor für Axialkompressor
RU2584365C2 (ru) * 2013-05-13 2016-05-20 Текспейс Аеро С.А. Система отбора воздуха для осевой турбомашины

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6425736B1 (en) * 1999-08-09 2002-07-30 United Technologies Corporation Stator assembly for a rotary machine and method for making the stator assembly
EP1293645A1 (de) * 2001-09-14 2003-03-19 Techspace Aero S.A. Axialverdichter einer Turbomaschine mit Vorrichtung zur Strömungsteilung, sowie Zusammenbauverfahren für diese Vorrichtung
DE60231219D1 (de) * 2002-12-03 2009-04-02 Techspace Aero Sa Innerer Mantelring eines axialen Kompressors sowie dessen Verwendung
GB0618991D0 (en) 2006-09-27 2006-11-08 Rolls Royce Plc A component for a gas turbine engine
EP2194230A1 (de) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Leitschaufelanordnung für eine Axialturbomaschine
DE102009034025A1 (de) * 2009-07-21 2011-01-27 Mtu Aero Engines Gmbh Einlaufbelag zur Anordnung an einem Gasturbinenbauteil
BE1023134B1 (fr) * 2015-05-27 2016-11-29 Techspace Aero S.A. Aube et virole a fourreau de compresseur de turbomachine axiale

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB991357A (en) * 1963-12-04 1965-05-05 Rolls Royce Axial fluid flow machine such as a compressor or turbine
GB994568A (en) * 1964-05-07 1965-06-10 Rolls Royce Bladed structure
DE1626031A1 (de) * 1967-08-31 1971-01-14 Daimler Benz Ag Gehaeuse fuer ein Gasturbinentriebwerk
DE2706110C3 (de) * 1977-02-14 1981-07-09 Aktiengesellschaft Kühnle, Kopp & Kausch, 6710 Frankenthal Verdichtergehäuse vorzugsweise für Abgasturbolader
FR2610673B1 (fr) * 1987-02-05 1991-03-15 Snecma Turboreacteur multiflux a couronne externe de redresseur de soufflante frettee sur le carter

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2400160A1 (de) 2010-06-23 2011-12-28 Techspace Aero S.A. Leichterer Rotor für Axialkompressor
RU2584365C2 (ru) * 2013-05-13 2016-05-20 Текспейс Аеро С.А. Система отбора воздуха для осевой турбомашины

Also Published As

Publication number Publication date
DE69910408T2 (de) 2004-06-24
EP1111246A1 (de) 2001-06-27
DE69910408D1 (de) 2003-09-18

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