EP0602631A1 - Procédé pour la construction d'une rangée d'aubes statoriques, en particulier pour un compresseur axial - Google Patents

Procédé pour la construction d'une rangée d'aubes statoriques, en particulier pour un compresseur axial Download PDF

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Publication number
EP0602631A1
EP0602631A1 EP93120255A EP93120255A EP0602631A1 EP 0602631 A1 EP0602631 A1 EP 0602631A1 EP 93120255 A EP93120255 A EP 93120255A EP 93120255 A EP93120255 A EP 93120255A EP 0602631 A1 EP0602631 A1 EP 0602631A1
Authority
EP
European Patent Office
Prior art keywords
ring
end section
parts
blade
openings
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.)
Granted
Application number
EP93120255A
Other languages
German (de)
English (en)
Other versions
EP0602631B1 (fr
Inventor
Siegfried Sikorski
Michael Schober
Reinhold Schönacher
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 EP0602631A1 publication Critical patent/EP0602631A1/fr
Application granted granted Critical
Publication of EP0602631B1 publication Critical patent/EP0602631B1/fr
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
    • 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
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments

Definitions

  • the invention relates to a method according to the preamble of patent claim 1.
  • Modern axial compressors require aerodynamically optimized, extremely slim blade profiles; attempts are being made in particular to manufacture the guide vanes of the axial guide vanes from a fiber-reinforced plastic; in addition to a reduction in weight, this has the advantage that a blade breakage caused in extreme cases does not cause any appreciable damage to subsequent, e.g. metallic rotor blades caused by hitting fragments.
  • the steps are essentially as follows: wrapping an outer housing ring with a layer of fiber-reinforced adhesive tape; Contribution distributed over the scope Cutouts in the openings in the outer housing ring; Cutting out the tape at the recesses; Inserting the blades with foot-like end parts into the recesses; Securing the blades in the recesses of the outer housing ring; machine incorporation of a circumferential recess in each of the foot-like end parts; extensive further tape winding through the circumferential recesses in the end parts.
  • the tape wound in the manner of a ring can be connected to the outer housing ring and to the foot-like end parts by a synthetic resin adhesive.
  • a complete dissolution of the blade / ring assembly is generally also required in the prior art with plastic blades if a combination of a radially outer and radially inner housing ring is provided, and in the case of blade damage that with a radially inner and radially outer base profile blade anchored between ring segments must be removed.
  • the invention has for its object to provide a method of the type mentioned and at least one device for carrying out, with which the fiber-reinforced plastic blades on the outer and / or inner ring can be fixed in a relatively simple and reliable manner so that the Attachment does not cause any subsequent material and strength impairments of the blade material and ring structures; furthermore, damaged blades should be easily exchangeable locally without lattice dismantling.
  • the task is primarily according to the procedure according to claim 1 solved according to the invention.
  • This arrangement allows a metallic outer ring to be made on the material side (wall thickness) and relatively weak in terms of strength and light weight. This applies all the more in connection with an outer ring made of a fiber-reinforced composite material (e.g. GRP or CFRP).
  • a fiber-reinforced composite material e.g. GRP or CFRP
  • the relevant end section of the guide vane which is optionally also provided with a longitudinal slot, so that at least two parts of the end section can be bent towards one another in the opposite direction as "flaps", is part of the vane which is prefabricated in this way; it can be, for example, jacket parts of the airfoil which protrude radially from the openings and which is made from wound fiber composite layers;
  • the end section can be a square component, manufactured together with the rest of the blade and thickened with respect to the blade, for example with its entire length, with which the blade initially sits loosely at the opening on the ring before the bending and fastening takes place. Subsequent processing operations of the plastic blade are advantageously eliminated, as is a plastic housing ring (groove cutouts), which practically does not damage the composite structure (Fiber splicing) cannot be realized.
  • the invention can be used in a so-called “inner ringless” guide vane; with comparatively simple blade assembly or disassembly, use with a guide vane with an outer and inner ring is also possible and advantageous; the blades are first pushed through the openings of the outer ring, for example, so that they are anchored to the inner blade ends on the inner ring in the axial and circumferential directions; the inner leaf end can engage in prefabricated recesses or pockets of the inner ring; the inner end of the sheet can alternatively be prefabricated with at least one recess with which the end of the sheet engages in radially projecting projections, pins or knobs of the inner ring, so that the end of the sheet sits completely flush and tightly locally on the inner ring.
  • the heating, bending already explained can then be carried out thereon and fixing the blade with the remaining end portion on the outer ring.
  • the invention for example according to FIGS. 1 to 3, can be used in the case of an axially flowable guide vane containing only one outer ring 1 or in the case of an axially flowable guide vane of an compressor stage of a gas turbine engine containing an outer and inner ring 1.10 (FIGS. 6 and 7) .
  • Outer and / or inner ring 1 or 10 can be held in a manner not shown axially and radially supported on outer or inner housing or stator structures;
  • the outer ring can also be part of the compressor housing.
  • the outer ring 1 (FIGS.
  • the end section 3 is prefabricated with a longitudinal slot 6 extending approximately in the longitudinal direction of the profile, through which the end section 3 is divided into at least two parts 4, 5 or "tabs"; Plates 8 can be integrated into the end section 3 produced during blade manufacture (FIG. 1), which support the deforming bend in the direction of arrow B by means of a deformation tool W which grips radially on the outside, centrally between the plates 8, or damage to the two parts 4, 5 should prevent.
  • the initially radially protruding parts 4, 5 of the end section 3 are heated and then — or thereafter — bent according to arrows B into the contour shown in dashed lines against the surface of the outer ring 1.
  • the parts 4, 5 can be bent around beads 9 or bead-like thickenings, each prefabricated along the openings 7 on the outer ring 1; these beads 9 enable a softly rounded bending of the parts 4, 5 and create relatively large seating and adhesive surfaces even with small blade spacings.
  • a self-adhesive connection of the parts 4,5 bent against the outer ring 1 can be produced by local heat supply.
  • a suitable adhesive can be used as a connecting means, e.g. a metal-containing plastic cement adhesive can be used.
  • a fastening of the bent parts 4, 5 with the outer ring 1 or with one another and with the outer ring 1 can be provided along the lines L1, L2 by riveting or screwing or the like.
  • the end section 3 embodies a schematically and perspectively represented fastening concept using an end section 3 of a guide vane 2 which is thickened in each case compared to the other airfoil profiling;
  • the end section 3 can have a square or rectangular cross section along its length; there is a straight extension of the end section 3 and the longitudinal slot 6 relative to the blade curvature and relative to the opening 7; in the starting contour shown with solid lines, the end section is at least partially seated at the opening 7 on the outer ring 1;
  • the end section 3 (FIG. 3) advantageously defines an exactly pre-positioned installation position of the guide vane 2.
  • FIG. 4 embodies a mutual overlap of the parts 4, 5 or bent in opposite directions from the longitudinal slot 6 per blade 2 from the longitudinal slot 6, which is possible over a relatively large area around the circumference of the ring, as shown in FIG. 3 "Rag".
  • each guide vane 2 is precisely pre-positioned on both sides before the deforming bending process of the parts 4, 5 of the end section 3.
  • the guide blade 2 can have a recess 13 on the side of its leaf profile facing away from the opening 7 (FIG. 6) in the outer ring 1, with which the blade 2 can be inserted into a corresponding projection 14 or pin or web or the like engages, which is arranged on the inner ring 10 radially projecting.
  • Fig. 6 more clearly compared to Fig. 1, the radially outer tool W with its two wedge surfaces W1, W2, the common tip for the bend in direction B increasingly deeper (arrow R) into the gap between the two sheet metal plates 8 can be inserted.
  • the first tool W can be replaced by a tool that actually works for the local attachment to the ring 1 required contouring is more clearly coordinated.
  • the supply of heat required for the bending of the parts 4, 5 and / or their fixing gluing can be generated, for example, by induction coils or electrical resistance heating spirals; in such or a comparable manner, however, the tool W itself and / or the plates 8 can also be heated or designed as a radiator.
  • the required local heating of components 4, 5 and / or 1 can also be generated by hair dryer-type hot air generators, with which e.g. at the same time differently directed hot air flows are caused.
  • the component heating required for the deforming bend and / or for the gluing can take place in a chamber in a vacuum or under pressure.
  • a chamber could consist of two shell-like or box-like complementary half-parts, which, with a portion of the outer ring 1 and the end portions 4, 5, are slipped over the ring portion on both sides and then hermetically sealed along their outer edges.
  • FIG. 6 that is to say in the case of an axial guide vane with an outer and inner ring 1, 10, it would be conceivable to equip the inner ring 10 with the blade filling openings 7 and the guide blades 2, in the sense of FIGS. 1 to 6, on the outside
  • the remaining fastening alternatives 11, 12 (FIG. 6) or 13, 14 (FIG. 7) then being applicable analogously with respect to the outer ring 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP93120255A 1992-12-18 1993-12-16 Procédé pour la construction d'une rangée d'aubes statoriques, en particulier pour un compresseur axial Expired - Lifetime EP0602631B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4242851 1992-12-18
DE4242851A DE4242851A1 (de) 1992-12-18 1992-12-18 Verfahren zur Herstellung eines Leitgitters für Turbomaschinen, insbesondere für Axialverdichter

Publications (2)

Publication Number Publication Date
EP0602631A1 true EP0602631A1 (fr) 1994-06-22
EP0602631B1 EP0602631B1 (fr) 1996-05-01

Family

ID=6475683

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93120255A Expired - Lifetime EP0602631B1 (fr) 1992-12-18 1993-12-16 Procédé pour la construction d'une rangée d'aubes statoriques, en particulier pour un compresseur axial

Country Status (2)

Country Link
EP (1) EP0602631B1 (fr)
DE (2) DE4242851A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1302629A1 (fr) * 2001-10-12 2003-04-16 Techspace Aero S.A. Etage redresseur d'un compresseur comprenant des aubes fixes et procédé de montage des aubes fixes
EP1531234A1 (fr) * 2003-11-17 2005-05-18 Rolls-Royce Deutschland Ltd & Co KG Virole interne pour les aubes statoriques d'un compresseur de turbine à gaz
EP2075416A1 (fr) * 2007-12-27 2009-07-01 Techspace aero Procédé de fabrication d'un élément de turbomachine et dispositif ainsi obtenu
EP1746252A3 (fr) * 2005-07-20 2010-03-17 United Technologies Corporation Elément structurel pour une combinaison montant - virole
FR2943942A1 (fr) * 2009-04-06 2010-10-08 Snecma Procede de fabrication d'une aube de turbomachine en materiau composite
EP2264284A1 (fr) 2009-06-18 2010-12-22 Techspace Aero S.A. Procédé de fabrication d'aubes integrées dans une virole et redresseur obtenu selon le procédé
US20240191627A1 (en) * 2022-12-09 2024-06-13 Lilium Eaircraft Gmbh Rotor for a ducted fan engine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR336322A (fr) * 1903-07-20 1904-03-05 Postel Vinay Ets Perfectionnements apportés à la construction des aubes de turbines
US3393436A (en) * 1965-09-16 1968-07-23 Rolls Royce Method of securing a blade assembly in a casing, e. g., a gas turbine engine rotor casing
GB2260580A (en) * 1991-10-16 1993-04-21 Rolls Royce Plc Gas turbine engine aerofoil structure

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3731360A (en) * 1971-04-07 1973-05-08 United Aircraft Corp Method of making a composite blade with an integrally attached root thereon

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR336322A (fr) * 1903-07-20 1904-03-05 Postel Vinay Ets Perfectionnements apportés à la construction des aubes de turbines
US3393436A (en) * 1965-09-16 1968-07-23 Rolls Royce Method of securing a blade assembly in a casing, e. g., a gas turbine engine rotor casing
GB2260580A (en) * 1991-10-16 1993-04-21 Rolls Royce Plc Gas turbine engine aerofoil structure

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1302629A1 (fr) * 2001-10-12 2003-04-16 Techspace Aero S.A. Etage redresseur d'un compresseur comprenant des aubes fixes et procédé de montage des aubes fixes
EP1531234A1 (fr) * 2003-11-17 2005-05-18 Rolls-Royce Deutschland Ltd & Co KG Virole interne pour les aubes statoriques d'un compresseur de turbine à gaz
US7287957B2 (en) 2003-11-17 2007-10-30 Rolls-Royce Deutschland Ltd & Co Kg Inner shroud for the stator blades of the compressor of a gas turbine
EP1746252A3 (fr) * 2005-07-20 2010-03-17 United Technologies Corporation Elément structurel pour une combinaison montant - virole
US8192150B2 (en) 2007-12-27 2012-06-05 Techspace Aero Method of manufacturing a turbomachine element and device obtained in this way
EP2075416A1 (fr) * 2007-12-27 2009-07-01 Techspace aero Procédé de fabrication d'un élément de turbomachine et dispositif ainsi obtenu
FR2943942A1 (fr) * 2009-04-06 2010-10-08 Snecma Procede de fabrication d'une aube de turbomachine en materiau composite
WO2010116066A1 (fr) * 2009-04-06 2010-10-14 Snecma Procede de fabrication d'une aube de turbomachine en materiau composite
CN102387908A (zh) * 2009-04-06 2012-03-21 斯奈克玛 一种用复合材料制成的涡轮机叶片的制造方法
US8607454B2 (en) 2009-04-06 2013-12-17 Snecma Method for producing a turbomachine blade made from a composite material
EP2264284A1 (fr) 2009-06-18 2010-12-22 Techspace Aero S.A. Procédé de fabrication d'aubes integrées dans une virole et redresseur obtenu selon le procédé
US8414259B2 (en) 2009-06-18 2013-04-09 Techspace Aero S.A. Method for manufacturing vanes integrated into a ring and rectifier obtained by the method
US20240191627A1 (en) * 2022-12-09 2024-06-13 Lilium Eaircraft Gmbh Rotor for a ducted fan engine

Also Published As

Publication number Publication date
DE4242851A1 (de) 1994-06-23
EP0602631B1 (fr) 1996-05-01
DE59302445D1 (de) 1996-06-05

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