EP1213484B1 - Statorstufe eines Verdichters - Google Patents

Statorstufe eines Verdichters Download PDF

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Publication number
EP1213484B1
EP1213484B1 EP00870292A EP00870292A EP1213484B1 EP 1213484 B1 EP1213484 B1 EP 1213484B1 EP 00870292 A EP00870292 A EP 00870292A EP 00870292 A EP00870292 A EP 00870292A EP 1213484 B1 EP1213484 B1 EP 1213484B1
Authority
EP
European Patent Office
Prior art keywords
vanes
blades
ferrule
ferrules
series
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
EP00870292A
Other languages
English (en)
French (fr)
Other versions
EP1213484A1 (de
Inventor
Mathieu Bos
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 DE60026687T priority Critical patent/DE60026687T2/de
Priority to EP00870292A priority patent/EP1213484B1/de
Priority to US10/000,830 priority patent/US6595747B2/en
Publication of EP1213484A1 publication Critical patent/EP1213484A1/de
Application granted granted Critical
Publication of EP1213484B1 publication Critical patent/EP1213484B1/de
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
    • 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
    • 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

Definitions

  • the present invention relates to a rectifier stage of a compressor comprising a succession of rectifier or stator stages separated by rotor blade stages of rotor blades, each rectifier stage consisting of fixed vanes connecting an inner ferrule to an outer ferrule.
  • Coaxial compressors are well known per se, and are used in several types of applications. In particular, they are used in dual-body engines, turbofans or turbojet engines. We also note their presence in power plants. These low or high pressure compressors consist essentially of several stages of rotating vanes or rotor stages separated by stator stages or rectifiers which are intended to reposition (straighten) the velocity vector of the fluid leaving the preceding stage before the send to the next compartment.
  • Each of these rectifier stages consists essentially of fixed vanes connecting an outer ferrule to an inner ferrule, both concentric.
  • a major problem in the case of the rectifier stages of a compressor is that it is necessary to particularly effectively bond said blades to ferrules. Indeed, this bonding of the blades to the ferrules must be optimal so as to be able to cope with accidents such as breaking a blade or ingestion of a foreign body such as a bird in said turbojet engine.
  • the blades are joined to the ferrules, both inside and out, by rivets, bolts or welds. Nevertheless, the use of these fastening means has the major disadvantage of disturbing the flow and generating a pressure drop in the aerodynamic vein.
  • US-A-2 812 159 features a blade assembly device comprising a series of U-shaped pieces, each blade being provided with a perforation in the bottom of the U in which the end is fitted free blades, this assembly being secured by fastening means comprising among others screws and which are adapted to prevent lateral and axial movements of the blades.
  • this assembly device does not solve the problem of the flow disturbance in the turbojet associated with the use of screws and other similar fastening means.
  • Document FR-A-1252179 relates to an assembly of fixed blades to the ferrules, wherein the vanes are temporarily attached to each other by their root T-shaped by means of a band which fits above said feet.
  • said assembly always uses screws to attach the blades to the ferrules, with the same disadvantage as mentioned above.
  • US-A-5 569 019 discloses an assembly of a turbine stator comprising an inner shell and an outer shell provided with openings through which blades pass, said blades being radially retained to the inner and outer ferrules by means of seals.
  • Each dawn consists essentially of two parts, a part exposed to the flow of air and a foot.
  • the vanes preferably comprise a non-metallic composite material consisting of a series of fibers including para-aramid fibers, which are continuous from the portion exposed to the airflow to the root of the vanes, but are discontinuous at the junction between said part exposed to the flow and the foot.
  • US-A-2,812,158 discloses a vane / ferrule assembly for a turbocharger, comprising an outer ferrule, an inner ferrule and sets of vanes, wherein the outer end of each fixed blade enters an opening at the outer shell and protrudes out of said outer shell.
  • two sets of vanes are held in position by means of a band subjected to tensile stresses, which surrounds the outer shell while being differentiated and which comes into contact with the surfaces of the outer ends of the vanes. .
  • the present invention aims to propose a solution that makes it possible to simplify the assembly of the blades to both the inner ferrule and the outer ferrule.
  • the present invention aims to provide a solution that offers great simplicity of assembly and does not require additional assembly operations.
  • the present invention also aims at providing a solution that allows the aerodynamic stream of the flow is not impaired by the presence of welds or rivets at the ferrule.
  • the present invention also aims to allow a low cost solution.
  • the present invention relates to a rectifier stage of a compressor comprising two ferrules, an inner ferrule and an outer ferrule, both concentric and preferably circular and connected one to the other. to the other by a series of blades. At least one of the ferrules, and preferably the two inner and outer ferrules, are provided with lights which allow the passage of said blades in these lumens to allow their attachment to the ferrules.
  • the blades also have at least one and preferably at both ends, an opening for allowing the passage of a locking element.
  • This locking element advantageously allows the joining of the blades to at least one and preferably to the two ferrules on the non-functional side, that is to say on the side of the inner face for the inner ferrule and the side of the face. external for the outer shell.
  • the joining of the blades to the ferrule or to the ferrules is effected by the passage of a strip in one or more pieces, which passes successively through all the openings of the blades of the same rectifier stage, and this non-functional side of the ferrules.
  • This strip has an elastic function and will be embedded in an elastomeric element that protects the various parts, and in particular the locking elements.
  • Figure 1 shows a general view of the compression stage of a turbofan.
  • FIG. 2 represents the solution implemented by the present invention for securing fixed blades to both outer and inner rings.
  • each ferrule, both the inner ferrule 4 and the outer ferrule 5 is provided with a series of lumens or openings (respectively the series 14 and 15) which allow the passage of the blades 60,61,62,63 , ... by one of their ends to the corresponding ferrule.
  • a portion 16 and 17 of said vanes 60,61,62,63, ... exceeds ferrules 4 and 5.
  • the different portions 16 or 17 each also have an opening 20,21,22,23, ... and 30,31,32, ... which allows the introduction of a locking element (respectively 40 and 50).
  • Said locking element here takes the form of a strip which, crossing simultaneously all openings 20,21,22, ..., or all openings 30,31,32, ... vanes fixed 60,61 , 62,63, ..., secures said vanes to the inner and outer ferrules 4 and 5. This occurs on the non-functional face of said ferrule, that is to say on the inner face of the inner ferrule 4 and on the outer face of the outer shell 5.
  • this strip has an elastic function and consists of a single piece.
  • the banner may comprise several pieces.
  • the blades are secured to the two ferrules in this way, on the one hand to the inner ferrule 4 and on the other hand to the outer ferrule 5, by through two locking elements 40 and 50.
  • the vanes are fixed and only one of the two rings.
  • the ends 16 or 17 of the blades 60,61,62,63, ... at which passes the locking element 40 or 50 are embedded in an elastomeric element 18 or 19.
  • Such a securing device has several advantages. Firstly, it does not cause any defects in the aerodynamic flow stream, which greatly reduces the pressure drops in it.
  • Another advantage is that it allows to assemble and secure two types of parts without mechanical connection, the blades and the ferrule, without changing the functional aspect of these two types of parts.

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

Claims (3)

  1. Leitapparat (2) eines Verdichters (1), der einen Außenring (5) und einen Innenring (4) umfasst, die beide konzentrisch und vorzugsweise kreisförmig sind und die durch eine Reihe Leitschaufeln (60, 61, 62, 63...) miteinander verbunden sind, dadurch gekennzeichnet, dass wenigstens einer der Ringe mit einer Reihe von Schlitzen oder Ausschnitten (Reihen 14 oder 15) versehen ist, die es ermöglichen, dass die besagten Leitschaufeln (60, 61, 62, 63...) durch diese Schlitze oder Ausschnitte geführt werden, wobei die Leitschaufeln (60, 61, 62, 63...) an wenigstens einem Ende (16 oder 17) einen Ausschnitt (20, 21, 22,... oder 30, 31, 32...) aufweisen, der zur Durchführung von wenigstens einem Verriegelungselement (40 oder 50) dient, mit dem gleichzeitig alle Schaufeln (60, 61, 62, 63...) des Leitapparats (2) auf der nicht funktionalen Seite des Rings miteinander verbunden werden können, und dadurch, dass das Ende (16 oder 17) der Leitschaufeln (60, 61, 62, 63...), an dem das Verriegelungselement (40 oder 50) angeordnet ist, in ein Elastomerteil (18 oder 19) eingebettet ist.
  2. Leitapparat nach Anspruch 1, dadurch gekennzeichnet, dass das Verriegelungselement (40 oder 50) die Form eines Bandes hat, das alle Ausschnitte (20, 21, 22,... oder 30, 31, 32...) der aufeinanderfolgenden Schaufeln (60, 61, 62, 63...) nacheinander durchquert.
  3. Leitapparat nach Anspruch 2, dadurch gekennzeichnet, dass das Band aus einem oder mehreren Teilen besteht, die eine Federfunktion aufweisen.
EP00870292A 2000-12-06 2000-12-06 Statorstufe eines Verdichters Expired - Lifetime EP1213484B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE60026687T DE60026687T2 (de) 2000-12-06 2000-12-06 Statorstufe eines Verdichters
EP00870292A EP1213484B1 (de) 2000-12-06 2000-12-06 Statorstufe eines Verdichters
US10/000,830 US6595747B2 (en) 2000-12-06 2001-11-30 Guide vane stage of a compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00870292A EP1213484B1 (de) 2000-12-06 2000-12-06 Statorstufe eines Verdichters

Publications (2)

Publication Number Publication Date
EP1213484A1 EP1213484A1 (de) 2002-06-12
EP1213484B1 true EP1213484B1 (de) 2006-03-15

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP00870292A Expired - Lifetime EP1213484B1 (de) 2000-12-06 2000-12-06 Statorstufe eines Verdichters

Country Status (3)

Country Link
US (1) US6595747B2 (de)
EP (1) EP1213484B1 (de)
DE (1) DE60026687T2 (de)

Cited By (1)

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EP2204546A1 (de) 2008-12-24 2010-07-07 Techspace Aero SA Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe

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Publication number Priority date Publication date Assignee Title
EP2204546A1 (de) 2008-12-24 2010-07-07 Techspace Aero SA Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe

Also Published As

Publication number Publication date
DE60026687T2 (de) 2006-11-09
EP1213484A1 (de) 2002-06-12
US6595747B2 (en) 2003-07-22
US20020085916A1 (en) 2002-07-04
DE60026687D1 (de) 2006-05-11

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