EP1637702B1 - Module de turbine pour moteur à turbine à gaz - Google Patents

Module de turbine pour moteur à turbine à gaz Download PDF

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Publication number
EP1637702B1
EP1637702B1 EP05108736.9A EP05108736A EP1637702B1 EP 1637702 B1 EP1637702 B1 EP 1637702B1 EP 05108736 A EP05108736 A EP 05108736A EP 1637702 B1 EP1637702 B1 EP 1637702B1
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EP
European Patent Office
Prior art keywords
sector
annular
turbine
shaped element
module 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.)
Active
Application number
EP05108736.9A
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German (de)
English (en)
French (fr)
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EP1637702A1 (fr
Inventor
Jacques René Bart
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 Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP1637702A1 publication Critical patent/EP1637702A1/fr
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • 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

Definitions

  • the present invention relates to the field of gas turbine engines and aims in particular a modular turbine element for such a motor.
  • 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.
  • rings 13A to 13E are arranged concentrically to the vanes of each stage.
  • the rings 13A to 13E consist of sheet metal sectors comprising sealing segments 14, of abradable type material, which cooperate with the end of the rotor blades, here a bead provided with radial blades, so as to form labyrinth seals.
  • the outer casing comprises annular axially oriented hooks 15 forming bearing and hooking surfaces for both the distributors 11 and the rings 13.
  • Each fin or nozzle sector includes corresponding means on its head portion. It is a pair of axial hooks 11 'facing upstream and radially spaced from each other, and downstream axial hooks 11'.
  • the hooks 15 cooperate with the stator hooks for supporting the distributors and the sealing rings together
  • Metal elements forming springs are associated with anti-rotation plates and ensure the clamping of the parts together and the maintenance of the assembly.
  • Labyrinth seals also provide sealing between the rotor and stator members at the other end of the stator vanes.
  • rings said inter-stages, on which radial blades are machined, are mounted between two discs and bolted with them. These inter-stage rings cooperate with pads of abradable material soldered to the inner platforms of the dispenser.
  • the interstage rings form a channel for guiding the cooling air between an internal supply source and the blade roots housed in the cells, especially at the dovetail, on the rim at the periphery of the disks.
  • 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.
  • a turbine module for a gas turbine engine comprising at least two consecutive stages of rotor of turbine separated by a distributor grid inside a housing, the annular distributors having a plurality of ring sector-shaped elements, a first portion of which supports fixed blades arranged radially towards the axis of the turbine and a second part forms a sealing means with the tops of the vanes of the turbine rotor, characterized in that said elements in the form of ring sector are wedged inside the casing by attachment means each comprising a axial hook integral with the casing, cooperating with a pair of axial hooks integral with the upstream portion of said ring-shaped element in such a way that the downstream end of a ring sealing sector of the rotor disposed upstream is held between said axial hooks secured to the upstream portion of said element with said axial hook integral with the housing.
  • the patent US 3644057 discloses ring-shaped elements having a first portion supporting fixed blades and a second portion forming a sealing means with the tips of the rotor blades. However, all the distributors and the housing do not form a module.
  • the module of the invention preferably comprises from three to six consecutive turbine rotor stages separated by distributors.
  • At least two of said turbine rotors form a one-piece assembly.
  • platelets of abradable material are fixed on said second part of the element.
  • 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 crankcase 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 above, the module here comprises five turbine stages 109A to 109E between which are interposed four distributor rings 111A to 111D.
  • the distributor grid 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 are 111A1 blades or 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.
  • 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 turbine sealing sector 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 second hook 121B of the housing.
  • the pair of stator hooks 113A1 and 113A2 encloses the first housing 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 constituted by the corresponding second hook 121B, the downstream end of the ring sector 113'A and the sector-shaped wafer 115A of abradable material.
  • the housing also comprises stops forming radial bearing surfaces 122 between the two hooks 121A and 121B consecutive. 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 engine gas leakage between the two sides of the turbine stage.
  • the rotary assembly 109 consists here of five disks, 109B3 to 109E3 on which the vanes are mounted. Each blade comprises a bulb-shaped foot housed in an axial cavity of complementary shape, with a dovetail profile for example, machined 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.
  • two discs together form a single block 109 '. They are monoblock, that is to say that they are not linked by mechanical means such as bolts and are not normally removable.
  • the two disks 109B3 and 109C3 are interconnected by a ferrule 109BC.
  • This ferrule has two wipers 109BC1 circumferential, transverse to the axis of the motor, formed by machining on its surface facing the distributor 111B.
  • the disc 109B3 is secured to a ferrule lateral 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 disc 109C3 also includes a 109CD ferrule with a radial flange 109CD1 by which it is bolted to the disc 109D3.
  • the disk 109 E3 comprises a ferrule 109ED with a radial flange through which it is bolted to the disk 109D 3.
  • a cone 109D4 is integral with the disk 109D 3 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, 109A 3 and 109B 8, 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 passages between the cell bottom and the blade root of the two disks 109A3 and 109B3 and be introduced into the gas vein.
  • 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 circulates between the ferrules 132A and 109CD from which it is guided to pass through the passages between the cell bottom and the blade root of the discs. 109C3 and 109D3 then in the gas vein.
  • 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05108736.9A 2004-09-21 2005-09-21 Module de turbine pour moteur à turbine à gaz Active EP1637702B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0452103A FR2875535B1 (fr) 2004-09-21 2004-09-21 Module de turbine pour moteur a turbine a gaz

Publications (2)

Publication Number Publication Date
EP1637702A1 EP1637702A1 (fr) 2006-03-22
EP1637702B1 true EP1637702B1 (fr) 2016-11-16

Family

ID=34949271

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05108736.9A Active EP1637702B1 (fr) 2004-09-21 2005-09-21 Module de turbine pour moteur à turbine à gaz

Country Status (6)

Country Link
US (1) US7828521B2 (ru)
EP (1) EP1637702B1 (ru)
JP (1) JP5005901B2 (ru)
CA (1) CA2520282C (ru)
FR (1) FR2875535B1 (ru)
RU (1) RU2377421C2 (ru)

Families Citing this family (17)

* 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
US8979491B2 (en) 2009-05-15 2015-03-17 Pratt & Whitney Canada Corp. Turbofan mounting arrangement
FR2960590B1 (fr) * 2010-05-25 2014-04-11 Snecma Distributeur de turbine pour une turbomachine
FR2966529B1 (fr) * 2010-10-21 2014-04-25 Turbomeca Procede d’attache de couvercle de compresseur centrifuge de turbomachine, couvercle de compresseur de mise en oeuvre et assemblage de compresseur muni d’un tel couvercle
FR2968030B1 (fr) * 2010-11-30 2013-01-11 Snecma Turbine basse-pression de turbomachine d'aeronef, comprenant un distributeur sectorise
FR2971004B1 (fr) * 2011-02-01 2013-02-15 Snecma Procede d'assemblage d'une turbine basse-pression de turboreacteur a double corps
JP6364415B2 (ja) 2012-10-08 2018-07-25 ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ 比較的軽量のプロパルサーモジュールを有するギア式タービンエンジン
EP2803822B1 (fr) * 2013-05-13 2019-12-04 Safran Aero Boosters SA Système de prélèvement d'air de turbomachine axiale
US9957826B2 (en) 2014-06-09 2018-05-01 United Technologies Corporation Stiffness controlled abradeable seal system with max phase materials and methods of making same
CA2966126C (fr) * 2014-10-15 2023-02-28 Safran Aircraft Engines Ensemble rotatif pour turbomachine comprenant une virole de rotor auto-portee
DE102016203567A1 (de) 2016-03-04 2017-09-07 Siemens Aktiengesellschaft Strömungsmaschine mit mehreren Leitschaufelstufen und Verfahren zur teilweisen Demontage einer solchen Strömungsmaschine
CN107060896B (zh) * 2017-05-08 2019-03-29 中国航发湖南动力机械研究所 涡轮导向器连接结构及具有其的燃气涡轮发动机
FR3069671A1 (fr) 2017-07-25 2019-02-01 Stmicroelectronics (Rousset) Sas Protection d'un calcul iteratif contre des attaques horizontales
CN109723507B (zh) * 2018-12-28 2023-09-12 中国船舶重工集团公司第七0三研究所 一种堆氦气涡轮机构
CN109404049B (zh) * 2018-12-28 2024-04-09 中国船舶重工集团公司第七0三研究所 一种可快速拆装的氦气涡轮连接结构
FR3104194B1 (fr) * 2019-12-10 2021-11-12 Safran Aircraft Engines Roue de rotor de turbine pour une turbomachine d’aeronef
US11549373B2 (en) 2020-12-16 2023-01-10 Raytheon Technologies Corporation Reduced deflection turbine rotor

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US3295751A (en) * 1965-04-21 1967-01-03 United Aircraft Corp Compressor stator shroud arrangement
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield

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FR2825748B1 (fr) * 2001-06-07 2003-11-07 Snecma Moteurs Agencement de rotor de turbomachine a deux disques aubages separes par une entretoise
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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

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3295751A (en) * 1965-04-21 1967-01-03 United Aircraft Corp Compressor stator shroud arrangement
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield

Also Published As

Publication number Publication date
JP2006090322A (ja) 2006-04-06
RU2005129351A (ru) 2007-03-27
CA2520282A1 (fr) 2006-03-21
FR2875535B1 (fr) 2009-10-30
FR2875535A1 (fr) 2006-03-24
US20070231133A1 (en) 2007-10-04
JP5005901B2 (ja) 2012-08-22
CA2520282C (fr) 2013-03-12
EP1637702A1 (fr) 2006-03-22
RU2377421C2 (ru) 2009-12-27
US7828521B2 (en) 2010-11-09

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