EP1637701B1 - Integriertes Rotorelement für den Rotor einer Gasturbine - Google Patents

Integriertes Rotorelement für den Rotor einer Gasturbine Download PDF

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Publication number
EP1637701B1
EP1637701B1 EP05108632.0A EP05108632A EP1637701B1 EP 1637701 B1 EP1637701 B1 EP 1637701B1 EP 05108632 A EP05108632 A EP 05108632A EP 1637701 B1 EP1637701 B1 EP 1637701B1
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EP
European Patent Office
Prior art keywords
turbine
blades
disks
axial
ring
Prior art date
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Application number
EP05108632.0A
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English (en)
French (fr)
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EP1637701A1 (de
EP1637701B2 (de
Inventor
Jacques René Bart
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
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    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/063—Welded rotors
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the present invention relates to the field of gas turbine engines and aims in particular a modular turbine element for such a motor having a one-piece turbine body.
  • a gas turbine engine comprises, in the direction of flow of the gases, means for compressing the air supplying the engine, a combustion chamber and at least one turbine stage for driving the compression means of the engine. air.
  • the engine can drive a blower contributing to the thrust produced by the latter.
  • the air admitted to the engine inlet is then divided into a primary flow directed to the combustion chamber and a secondary flow concentric to the first and providing in engines with high dilution rate most of the thrust.
  • These latter motors for some two bodies include: a high pressure body and a low pressure body independent in rotation from one another.
  • the low pressure body drives the blower.
  • Each body includes a turbine module driving the associated compression module.
  • the turbine rotor low pressure 9 consists of five disks 9A to 9E provided with blades on their periphery and bolted together. The five stages are separated by fixed flow distributors, 11A to 11D, which each straighten the flow of gas from the upstream stage to the stage immediately downstream.
  • the discs are each laterally bordered by a frustoconical portion 10 provided with radial flanges, called “mustaches” by which they are bolted to the neighboring disc.
  • the vanes 12 are housed in axial cells with a dovetail profile, and retained against any axial displacement by a hook 12 'whose foot is provided.
  • An annular ring 13 is engaged under each of the hooks and forms an axial locking of the blades.
  • the ring 13 itself is maintained in placed and immobilized against any radial displacement that could disengage the hooks 12 'by interstage rings 14.
  • These rings 14 provided with wipers form a labyrinth seal with plates of abradable material mounted along the inner edges of the distributors. These rings also guide the cooling air from inside the rotor to the blade roots. Radial passages are provided for this purpose.
  • the applicant has therefore set itself the goal of producing a turbine module, more particularly a low pressure turbine module, the structure of which is simplified with respect to the production of the prior art.
  • EP Patent 1,264,964 which relates to a turbomachine rotor arrangement comprising two disks with blades housed in axial cavities. Both discs are welded to form a one-piece body. A spacer is provided between the two disks to form a labyrinth seal and guide the cooling air. It comprises in particular an annular part enveloping at a distance the surface of the rotor, in the form of a ferrule, between the two disks and tongues able to slide in the cavities.
  • This monoblock body solution is of simplified structure compared to an assembly of two disks bolted together. In addition one benefits from a gain of mass. However, this structure implies constraints on the arrangement of blades that are not necessarily aerodynamically favorable.
  • the invention therefore aims to provide a turbine module whose structure is simplified without the disadvantages of the solutions presented in the prior art.
  • the structure according to the invention makes it possible on the one hand to reduce the mass of the rotary assembly, in particular by eliminating a part of the connecting members by bolting, and by lightening the adjacent disks by removing whiskers, and secondly to simplify the structure of the module.
  • the rotatable assembly of the turbine module includes inter-stage rings incorporating labyrinth seal wipers between each of said adjacent disks and the one-piece body.
  • Said rings also form an axial locking means for the blades and / or a passage for cooling air with said inter-disk ferrules.
  • the module comprises one or more annular distributors consisting of a plurality of elements in the form of a ring sector, a first portion of which supports vanes arranged radially towards the outside. turbine axis and a second part forms a sealing means with the tops of the blades.
  • said ring sector-shaped elements are wedged inside the housing by hooking means.
  • said hooking means comprise an axial hook integral with the housing or said elements, cooperating with a pair of axial hooks integral respectively said elements or the housing.
  • the pair of hooks is disposed on the upstream portion of said ring sector elements.
  • the attachment means comprises an axial hook on the casing cooperating with a pair of axial hooks integral with said ring-sector shaped elements, such that the downstream end of the rotor sealing ring sectors. placed upstream is maintained between the brackets.
  • the module according to the invention shown in section along the axis of the gas turbine engine is disposed downstream of the combustion chamber not visible on the figure 2 . It receives the flow of engine gas from the distributor 105. It comprises a housing of frustoconical general shape 120 inside which are mounted the different distributor stages interposed between the turbine rotor stages. As in the device of the prior art presented in connection with the figure 1 , the module here comprises five turbine stages 109A to 109E between which are intercalated four distributor rings 111A to 111D.
  • the distributor 111A is of generally annular shape being subdivided into sectors.
  • the sectors comprise from one to ten fixed vanes, for example five or six. There may be for example 8 sectors forming the distribution ring.
  • For each sector of the distributor 111A there is a distinction, see in more detail also the figure 3 , or the blades 111A1, arranged radially across the gas stream between an inner platform 112A located on the side of the motor axis and an outer platform 113A to the opposite.
  • Distributors 111B to 111D are preferably the same.
  • the rotating assembly 109 consists here of five disks, 109B3 to 109E3 on which are mounted the blades.
  • Each blade comprises a bulb-shaped foot housed in a cell of complementary shape, dovetail profile for example, machined axially in the rim of the discs.
  • Mobile blades and their mounting on a disk are known to those skilled in the art and do not form part of the invention.
  • the feet include an axial retaining hook as is also known.
  • two rotor discs together form a single block 109 '. They form a one-piece body, that is to say that they are not linked by mechanical means such as bolts and are not normally removable. They are preferably welded.
  • the two disks 109B3 and 109C3 are interconnected by a ferrule 109BC. We see the welding zones between the ferrule and rims of the discs.
  • This ferrule has two wipers 109BC1, oriented transversely to the axis of the motor and formed by machining on its surface facing the distributor 111B.
  • the disk 109B3 is secured to a side ferrule inter disk 109BA.
  • This comprises a radial flange 109BA1 through which the rotor is bolted to the adjacent disc 109A3.
  • a bolt B is shown.
  • the holes for the passage of the bolts are drilled in the plane of the disc near the rim.
  • the disk 109C3 also comprises a 109CD ring with a radial flange 109CD1 by which it is bolted (in B) to the disk 109D3.
  • the disk 109E3 has a 109ED ferrule with a radial flange through which it is bolted to the disk 109D3.
  • a cone 109D4 is secured to the disk 109D3 for mounting the rotary assembly on a bearing not shown.
  • the ring 131 has a frustoconical portion 131A of diameter slightly greater than that of the shell 109BA to form with the latter an air passage. It comprises on each side a respectively frustoconical web 131B and 131C which bears against the disk, 109A3 and 109B3 respectively, at the level of the cells. It thus forms both a means of guiding the air in the latter and an axial stop for the blade roots that are housed therein.
  • the air is admitted from inside the rotor by passages formed between the radial flange 109BA1 and the disc 109A3; it circulates between the two rings 109BA and 131A to be evacuated by the cells of the two disks 109A3 and 109B3 in the direction of the gas stream.
  • the ferrule 132 similarly comprises a central frustoconical portion 132A bordered by two sails 132B and 132C.
  • the cooling air is admitted through passages formed between the flange 109CD1 and the disc 109D3; it circulates between ferrules 132A and 109CD from where it is guided to pass through the cells of disks 109C3 and 109D3 and then into the gas vein.
  • the outer platform 113A is part of a ring-shaped element 114A in two parts arranged axially one after the other. Said platform is the first part 113A and a sealing sector of turbine cooperating with the top of the blades of the downstream turbine stage is the second part 113'A.
  • the inner platform 112A, the element 114A and the blades have come from a single casting.
  • the second portion 113'A comprises an abradable material 115A with regard to wipers formed on the top of the blades of the corresponding mobile stage.
  • the outer platform 113A comprises upstream a pair of axial hooks 113A1 and 113A2 spaced radially from one another. It also comprises downstream a radial bearing surface 113A3. Downstream, the second portion 113'A comprises a radial bearing surface 113'A4, and a radial lug 113'A5 forming axial stop. There is also an axially oriented finger 113'A6 which engages between two sectors of the downstream distributor 113B and forms an anti-rotation locking means.
  • the casing 120 comprises on its inner face hooks distributed along the axis of the motor by which the stators are fixed.
  • an axial hook 121A having an outer radial bearing surface and an inner radial bearing surface.
  • the spacing between two consecutive hooks 121a and 121B corresponds to the spacing between the hook 113A1 and the radial bearing surface 113'A4 of the same element 114.
  • the lug 113'A5 winds axially against the hook 121B crankcase.
  • the pair of stator hooks 113A1 and 113A2 enclose the crank hook 121A and the downstream end of the sealing sector 105 'which is disposed immediately upstream of the distributor stage 111A.
  • the pair of hooks encloses the assembly consisting of the corresponding hook 121, the downstream end of the ring sector 113'A and the plate 115A of abradable material.
  • the casing also comprises abutments forming radial bearing surfaces 122 between two consecutive hooks 121A and 121B. They serve as radial support to the bearing surfaces 113A3.
  • the blades 109B1 of the stage 109B are terminated by a heel 109B2 which is provided with wipers or radial blades cooperating with the wafer of abradable material 115A. They thus form a labyrinth seal against gas leakage between the two sides of the turbine rotor.
  • the assembly of the various components of the module is carried out as follows.
  • the casing is possibly already in place on the engine with the ring 105 '.
  • the pieces are then placed in the following order.
  • the complete rotor 109A whose blades are already mounted on the disk 109A3, is set up and wedged by means of appropriate tools.
  • the distributor 111A is placed sector by sector by sliding the hooks 113A1 and 113A2 on the downstream part of the assembly formed by the ring 105 'and the first hook 121A of the housing.
  • the surface 113A3 abuts against the first stop 122, and the surface 113'A4 abuts against the inner radial surface of the second hook 121B.
  • the finger 113'A5 abuts against the latter.
  • the interstage ring 131 is slid inside the ring 111A until it abuts against the rotor 109A, thus axially locking the blade roots in their cell; hooks formed on the blade root and bearing against the rim ensure immobilization against axial displacement in one direction.
  • the ring provides axial locking in the opposite direction.
  • the one-piece body 109 'with only the blades of the stage 109B is put in place and bolted directly to the disk 109A3. It is observed that the blades of the stage 109B bear against the veil 131C of the inter-stage ring 131. The hooks on the blade roots are located on the upstream side bearing against the rim of the disc; in this way the feet are locked against axial displacement.
  • the distributor 111B is set up sector by sector. First introduced the foot of each sector between the two disks 109B and 109C, then tilts it until it clings to the second hook 121B of the housing by enclosing the downstream end of the ring 113'A together with its abradable material. It is positioned on the housing in the same way as the previous distributor. The downstream radial finger comes into axial abutment against the third hook 121C.
  • the blades of the stage 109C are introduced into their housing on the disk 109C3.
  • the axial stop hook is located on the downstream side of the disc 109C3, preventing axial displacement upstream.
  • the distributor 111C is set up so that it is positioned in the housing as the previous distributors.
  • the interstage ring 132 is slid into the central passage formed by the distributor 111C. It comes to bear against the disk 109C3, locking the blades.
  • the complete rotor 109D is bolted to the flange 109CD1 of the monoblock 109 '.
  • the 111D distributor is mounted
  • the complete rotor 109 E is bolted to the disk 109D3.
  • the invention covers modules comprising from four to six stages preferably.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. Modul einer Turbine für ein Gasturbinentriebwerk mit einem Turbinenrotor (109), der aus mindestens vier Scheiben besteht, die Schaufeln an ihrem Umfang tragen, wobei zwei der Scheiben einen einteiligen Körper bilden, wobei der einteilige Körper (109') zwei seitliche Rohrabschnitte zwischen Scheiben (109BA, 109CD) aufweist, dadurch gekennzeichnet, dass die Rohrabschnitte an den Scheiben (109A3, 109D3) der zwei Rotoren, die an den einteiligen Block angrenzen, durch die Öffnungen verbolzt sind, die in den Ebenen der Scheiben (109A3, 109D3) vorgesehen sind, wobei ein Ring zwischen Stufen (131, 132), der sich von dem einteiligen Körper (109') unterscheidet, sich zwischen jeder der benachbarten Scheiben (109A3, 109D3) und dem einteiligen Körper (109') befindet, wobei der Ring einen axialen Stopper für den Fuß der mobilen Schaufeln und einen Luftdurchlass zur Kühlung des Fußes der Schaufeln mit den seitlichen Rohrabschnitten zwischen Scheiben (109BA, 109CD) bildet.
  2. Modul einer Turbine nach Anspruch 1, das mindestens ringförmige Verteiler zwischen den Turbinenstufen umfasst, wobei die Verteiler mehrere Elemente (114A bzw. 114D) in Form eines Ringsektors umfassen, von dem ein erster Teil (113A bzw. 113D) feststehende Schaufeln trägt, die radial zu der Achse der Turbine angeordnet sind, und ein zweiter Teil (113'A bzw. 113'D) ein Dichtungsmittel mit den Spitzen der Schaufeln des Turbinenrotors bildet, wobei die Elemente (114A bzw. 114D) in Form von Ringsektoren im Inneren des Gehäuses (120) durch Befestigungsmittel verkeilt sind.
  3. Modul nach dem vorhergehenden Anspruch, wobei die Befestigungsmittel einen axialen Haken (121A bzw. 121D) umfassen, der mit dem Gehäuse (120) oder dem Element (114A bzw. 114D) einstückig ist, der mit einem Paar axialer Haken (113A1-113A2 bzw. 113D1-113D2) kooperiert, die einstückig mit dem Element (114A bzw. 114D) bzw. dem Gehäuse (120) sind.
  4. Modul nach einem der Ansprüche 2 und 3, das Befestigungsmittel (113A1-113A2 bzw. 113D1-113D2) an dem stromaufwärts gelegenen Teil des Elements (114A bzw. 114D) in Form von einem Ringsektor umfasst.
  5. Modul nach Anspruch 4, wobei die Befestigungsmittel einen axialen Haken (121A bzw. 121D) an dem Gehäuse umfassen, der mit einem Paar axialen Haken 113A1-113A2 bzw. 113D1-113D2) kooperiert, die einstückig mit dem Element (114A bzw. 114D) in Form eines Ringsektors sind, so dass das stromabwärts gelegene Ende eines Ringsektors (105' 113A' bzw. 113'C) zur Abdichtung des Rotors, der stromaufwärts gelegen ist, zwischen den Haken gehalten wird.
  6. Gasturbinentriebwerk, das ein Modul einer Turbine nach einem der Ansprüche 1 bis 5 umfasst.
EP05108632.0A 2004-09-21 2005-09-19 Integriertes Rotorelement für den Rotor einer Gasturbine Active EP1637701B2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0452102A FR2875534B1 (fr) 2004-09-21 2004-09-21 Module de turbine pour moteur a turbine a gaz avec rotor comportant un corps monobloc

Publications (3)

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EP1637701A1 EP1637701A1 (de) 2006-03-22
EP1637701B1 true EP1637701B1 (de) 2017-01-04
EP1637701B2 EP1637701B2 (de) 2019-12-25

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EP05108632.0A Active EP1637701B2 (de) 2004-09-21 2005-09-19 Integriertes Rotorelement für den Rotor einer Gasturbine

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US (1) US7507072B2 (de)
EP (1) EP1637701B2 (de)
JP (1) JP5072207B2 (de)
CA (1) CA2520069C (de)
FR (1) FR2875534B1 (de)
RU (1) RU2377417C2 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2875534B1 (fr) 2004-09-21 2006-12-22 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz avec rotor comportant un corps monobloc
FR2875535B1 (fr) 2004-09-21 2009-10-30 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
JP2009236038A (ja) * 2008-03-27 2009-10-15 Toshiba Corp 蒸気タービン
FR2961848B1 (fr) 2010-06-29 2012-07-13 Snecma Etage de turbine
IT1403415B1 (it) * 2010-12-21 2013-10-17 Avio Spa Turbina a gas per motori aeronautici
FR2971004B1 (fr) * 2011-02-01 2013-02-15 Snecma Procede d'assemblage d'une turbine basse-pression de turboreacteur a double corps
FR2983518B1 (fr) * 2011-12-06 2014-02-07 Snecma Dispositif deverrouillable d'arret axial d'une couronne d'etancheite contactee par une roue mobile de module de turbomachine d'aeronef
EP2803822B1 (de) * 2013-05-13 2019-12-04 Safran Aero Boosters SA Luftentnahmesystem aus einer axialen Turbomaschine
FR3040734B1 (fr) * 2015-09-09 2017-09-22 Snecma Turbine de turbomachine comprenant un etage distributeur en materiau composite a matrice ceramique
FR3126022A1 (fr) 2021-08-05 2023-02-10 Safran Aircraft Engines Ensemble pour turbomachine d’aeronef comprenant une anneau de recouvrement pour l’isolement d’organes de fixation mecanique vis-a-vis d’un flux d’air

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FR2690954A1 (fr) * 1992-05-11 1993-11-12 Gen Electric Distributeur-collecteur pour le refroidissement du passage central d'un compresseur.

Also Published As

Publication number Publication date
JP2006090320A (ja) 2006-04-06
US7507072B2 (en) 2009-03-24
CA2520069C (fr) 2013-03-12
EP1637701A1 (de) 2006-03-22
FR2875534A1 (fr) 2006-03-24
RU2005129353A (ru) 2007-03-27
EP1637701B2 (de) 2019-12-25
RU2377417C2 (ru) 2009-12-27
FR2875534B1 (fr) 2006-12-22
JP5072207B2 (ja) 2012-11-14
US20060251520A1 (en) 2006-11-09
CA2520069A1 (fr) 2006-03-21

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