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EP1637701B2 - Un corps monobloc pour un rotor d'un moteur à turbine à gaz - Google Patents

Un corps monobloc pour un rotor d'un moteur à turbine à gaz Download PDF

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Publication number
EP1637701B2
EP1637701B2 EP05108632.0A EP05108632A EP1637701B2 EP 1637701 B2 EP1637701 B2 EP 1637701B2 EP 05108632 A EP05108632 A EP 05108632A EP 1637701 B2 EP1637701 B2 EP 1637701B2
Authority
EP
European Patent Office
Prior art keywords
disk
monoblock body
adjacent
turbine
rotor
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
EP05108632.0A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1637701A1 (fr
EP1637701B1 (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
Original Assignee
Safran Aircraft Engines SAS
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
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP1637701A1 publication Critical patent/EP1637701A1/fr
Application granted granted Critical
Publication of EP1637701B1 publication Critical patent/EP1637701B1/fr
Publication of EP1637701B2 publication Critical patent/EP1637701B2/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
    • 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 is aimed in particular at a modular turbine element for such an engine comprising a one-piece turbine body.
  • a gas turbine engine comprises, in the direction of the gas flow, a means of compressing the air supplying the engine, a combustion chamber and at least one stage of a turbine driving the means of compressing the air.
  • the engine can cause a fan contributing to the thrust produced by the latter.
  • the air admitted to the engine inlet is then divided into a primary flow directed towards the combustion chamber and a concentric secondary flow to the first and supplying in engines with high dilution rate the major part of the thrust.
  • These latter motors include, for some, two bodies: a high pressure body and a low pressure body which are independent in rotation from one another.
  • the low pressure body drives the blower.
  • Each body comprises a turbine module driving the associated compression module.
  • the turbine rotor low pressure 9 consists of five discs 9A to 9E provided with blades on their periphery and bolted together. The five stages are separated by fixed flow distributors, 11A to 11 D, which each rectify the flow of gas from the upstream stage to the stage located immediately downstream.
  • the discs are each bordered laterally by a frustoconical part 10 provided with radial flanges, called “mustache” by which they are bolted to the neighboring disc.
  • the blades 12 are housed in axial cells with a dovetail profile, and retained against any axial displacement by a hook 12 'with which their foot is provided.
  • An annular ring 13 is engaged under each of the hooks and forms an axial locking of the blades.
  • the rod 13 itself is held in place and immobilized against any radial displacement which could release it from the hooks 12 'by inter-stage rings 14.
  • These rings 14 provided with wipers form a labyrinth seal with plates of abradable material mounted on along the inside edges of the dispensers. These rings also guide the cooling air from the inside of the rotor to the blade roots. Radial passages are provided for this purpose.
  • the Applicant has therefore set itself the objective of producing a turbine module, more particularly of a low pressure turbine module, the structure of which is simplified compared to the embodiment of the prior art.
  • EP patent 1,264,964 which relates to a turbomachine rotor arrangement comprising two discs with blades housed in axial cells.
  • the two discs are welded to form a one-piece body.
  • a spacer is provided between the two discs to form a labyrinth seal and guide the cooling air. It comprises in particular an annular part enveloping the surface of the rotor at a distance, in the form of a ferrule, between the two discs and tongues capable of sliding in the cells.
  • This one-piece body solution has a simplified structure compared to an assembly of two discs bolted together. In addition, there is a mass gain. However, this structure implies constraints on the arrangement of the blades which are not necessarily favorable aerodynamically.
  • the invention therefore aims to achieve a turbine module whose structure is simplified without having the drawbacks 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 part of the connecting members by bolting, and by reducing the adjacent discs by removing whiskers, and secondly to simplify the structure of the module.
  • the rotary assembly of the turbine module comprises inter-stage rings incorporating wipers for a labyrinth seal 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 the cooling air with the said inter-disc ferrules.
  • the module comprises one or more annular distributors made up of a plurality of elements in the form of a ring sector, a first part of which supports fixed vanes arranged radially towards the the axis of the turbine and a second part forms a sealing means with the tops of the moving blades.
  • said elements in the form of a ring sector are wedged inside the casing by hooking means.
  • said attachment means comprise an axial hook secured to the casing or said elements, cooperating with a pair of axial hooks secured respectively to said elements or to the casing.
  • the pair of hooks is arranged on the upstream part of said elements in the form of a ring sector.
  • the attachment means comprises an axial hook on the casing cooperating with a pair of axial hooks integral with said elements in the form of a ring sector, such that the downstream end of the sealing ring sectors of the rotor arranged upstream is held between the hooks.
  • the mounting of the turbine stages is improved in a simple and efficient manner without causing substantial modifications to the environment of this module in the engine.
  • the module according to the invention shown in section along the axis of the gas turbine engine, is arranged downstream of the combustion chamber not visible on the figure 2 . It receives the flow of engine gas through the distributor 105. It comprises a generally frustoconical casing 120 inside which are mounted the various stages of distributors interposed between the stages of rotor of turbines. As in the device of the prior art presented in relation to the figure 1 , the module here comprises five turbine stages 109A to 109E between which four distributor rings 111A to 111D are interposed.
  • the distributor 111A is generally annular in shape, being subdivided into sectors.
  • the sectors include from one to ten fixed blades, for example five or six. There can be, for example, 8 sectors forming the distribution ring.
  • For each sector of the 111A distributor a distinction is made, 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 axis of the engine and an outer platform 113A opposite.
  • the distributors 111B to 111D are preferably formed in the same way.
  • Rotary assembly 109 consists here of five discs, 109B3 to 109E3 on which the movable blades are mounted.
  • Each blade comprises a bulbous-shaped foot housed in a cell of complementary shape, with a dovetail profile for example, machined axially in the rim of the discs.
  • the movable blades and their mounting on a disc 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, they are not linked by mechanical means such as bolts and are not normally removable. They are preferably welded.
  • the two discs 109B3 and 109C3 are interconnected by a ferrule 109BC. We can see the welding zones between the ferrule and the rims of the discs.
  • This ferrule has two wipers 109BC1, oriented transversely relative to the axis of the engine and formed by machining on its surface facing the distributor 111B.
  • the disc 109B3 is integral with a lateral ferrule inter disc 109BA.
  • 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 ferrule 109CD with a radial flange 109CD1 by which it is bolted (at B) to the disc 109D3.
  • the disc 109E3 has a ferrule 109ED with a radial flange by which it is bolted to the disc 109D3.
  • a 109D4 cone is integral with the 109D3 disc for mounting the rotary assembly on a bearing not shown.
  • the ring 131 comprises a frustoconical portion 131A of diameter slightly greater than that of the ferrule 109BA to form with the latter an air passage. It has on each side a veil, 131B and 131C respectively, frustoconical which bears against the disc, 109A3 and 109B3 respectively, at the level of the cells. It thus forms both a means for guiding the air in the latter and an axial stop for the blade roots which are housed there.
  • Air is admitted from inside the rotor through passages formed between the radial flange 109BA1 and the disc 109A3; it flows between the two ferrules 109BA and 131A to be evacuated by the cells of the two discs 109A3 and 109B3 in the direction of the gas stream.
  • the ferrule 132 likewise comprises a central frustoconical part 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 the ferrules 132A and 109CD from where it is guided to pass through the cells of the discs 109C3 and 109D3 then in the gas stream.
  • the outer platform 113A is part of an element 114A in the form of a ring sector, 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 interior platform 112A, the element 114A and the blades have come from a single piece of casting.
  • the second part 113'A comprises an abradable material 115A with regard to the wipers formed on the top of the blades of the corresponding movable stage.
  • the external 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 part 113'A comprises a radial bearing surface 113'A4, and a radial lug 113'A5 forming an axial stop. There is also a finger axially oriented 113'A6 which engages between two sectors of the downstream distributor 113B and forms an anti-rotation locking means.
  • the housing 120 comprises on its internal face hooks distributed along the axis of the motor by which the stators are fixed.
  • an axial hook 121A comprising 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 in axial abutment against the hook 121B of the housing.
  • the pair of hooks 113A1 and 113A2 of the stator surrounds the hook 121A of the casing and the downstream end of the sealing sector 105 'which is arranged immediately upstream of the distributor stage 111A.
  • the pair of hooks encloses the assembly constituted by the corresponding hook 121, the downstream end of the ring sector 113'A and the plate 115A of abradable material.
  • the housing also includes stops forming radial support surfaces 122 between two consecutive hooks 121A and 121B. They serve as radial support for the bearing surfaces 113A3.
  • the blades 109B1 of stage 109B are terminated by a heel 109B2 which is provided with wipers or radial blades cooperating with the plate made of abradable material 115A. They thus form a labyrinth seal against gas leaks 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 distributor 111A is placed sector by sector by sliding the hooks 113A1 and 113A2 onto the downstream part of the assembly formed by the ring 105 'and the first hook 121A of the casing.
  • 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 is in abutment against the latter.
  • the inter-stage ring 131 is slid inside the ring 111A until it comes into abutment against the rotor 109A, thus axially blocking the blade roots in their cell; hooks formed on the foot of the blades and bearing against the rim ensure immobilization against any 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 disc 109A3. It is observed that the blades of the stage 109B come to bear against the web 131C of the inter-stage ring 131.
  • the hooks on the blade feet are located on the upstream side in abutment against the rim of the disc; in this way the feet are locked against any axial displacement.
  • Distributor 111B is set up sector by sector. We first introduce the foot of each sector between the two discs 109B and 109C, then we switch the latter until it hooks onto the second hook 121B of the casing 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 disc 109C3.
  • the hook forming an axial stop is located on the downstream side of the disc 109C3, preventing any axial displacement upstream.
  • the distributor 111C is put in place so that it is positioned in the casing like the previous distributors.
  • the inter-stage ring 132 is slid into the central passage formed by the distributor 111C. It bears against the disc 109C3, locking the vanes.
  • the complete rotor 109D is bolted to the flange 109CD1 of the monoblock 109 '.
  • Distributor 111D is mounted
  • the complete 109 E rotor is bolted to the 109D3 disc.
  • the description relates to a module comprising five stages.
  • the invention covers modules preferably comprising from four to six stages.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05108632.0A 2004-09-21 2005-09-19 Un corps monobloc pour un rotor d'un moteur à turbine à gaz Expired - Lifetime EP1637701B2 (fr)

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)

Publication Number Publication Date
EP1637701A1 EP1637701A1 (fr) 2006-03-22
EP1637701B1 EP1637701B1 (fr) 2017-01-04
EP1637701B2 true EP1637701B2 (fr) 2019-12-25

Family

ID=34949270

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05108632.0A Expired - Lifetime EP1637701B2 (fr) 2004-09-21 2005-09-19 Un corps monobloc pour un rotor d'un moteur à turbine à gaz

Country Status (6)

Country Link
US (1) US7507072B2 (ru)
EP (1) EP1637701B2 (ru)
JP (1) JP5072207B2 (ru)
CA (1) CA2520069C (ru)
FR (1) FR2875534B1 (ru)
RU (1) RU2377417C2 (ru)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2875535B1 (fr) 2004-09-21 2009-10-30 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
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
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 (fr) * 2013-05-13 2019-12-04 Safran Aero Boosters SA Système de prélèvement d'air de turbomachine axiale
FR3040734B1 (fr) * 2015-09-09 2017-09-22 Snecma Turbine de turbomachine comprenant un etage distributeur en materiau composite a matrice ceramique
FR3126022B1 (fr) 2021-08-05 2025-04-18 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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3644057A (en) † 1970-09-21 1972-02-22 Gen Motors Corp Locking device
US5232339A (en) † 1992-01-28 1993-08-03 General Electric Company Finned structural disk spacer arm
US20020187046A1 (en) † 2001-06-07 2002-12-12 Snecma Moteurs Turbomachine rotor assembly with two bladed-discs separated by a spacer
US20030133803A1 (en) † 2002-01-17 2003-07-17 Snecma Moteurs Turbomachine rotor arrangement
US20050111970A1 (en) † 2003-11-26 2005-05-26 Gabriel Suciu Turbine durm rotor for a turbine engine

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GB1047281A (ru) * 1964-01-23
US3963368A (en) 1967-12-19 1976-06-15 General Motors Corporation Turbine cooling
US4248569A (en) 1978-11-13 1981-02-03 General Motors Corporation Stator mounting
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
FR2600377B1 (fr) * 1986-06-18 1988-09-02 Snecma Dispositif de controle des debits d'air de refroidissement d'une turbine de moteur
FR2607866B1 (fr) * 1986-12-03 1991-04-12 Snecma Axes de fixation de rotors de turbomachine, procede de montage et rotors ainsi montes
US5131811A (en) 1990-09-12 1992-07-21 United Technologies Corporation Fastener mounting for multi-stage compressor
US5211541A (en) * 1991-12-23 1993-05-18 General Electric Company Turbine support assembly including turbine heat shield and bolt retainer assembly
US5271711A (en) * 1992-05-11 1993-12-21 General Electric Company Compressor bore cooling manifold
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US5320487A (en) * 1993-01-19 1994-06-14 General Electric Company Spring clip made of a directionally solidified material for use in a gas turbine engine
DE4319727C2 (de) * 1993-06-15 1996-08-29 Mtu Muenchen Gmbh Verfahren zur Herstellung eines Schaufelringes für einen trommelartig aufgebauten Rotor, insbesondere Verdichterrotor einer Turbomaschine
US5350278A (en) * 1993-06-28 1994-09-27 The United States Of America As Represented By The Secretary Of The Air Force Joining means for rotor discs
FR2711730B1 (fr) 1993-10-27 1995-12-01 Snecma Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator.
US5503528A (en) 1993-12-27 1996-04-02 Solar Turbines Incorporated Rim seal for turbine wheel
GB2313161B (en) 1996-05-14 2000-05-31 Rolls Royce Plc Gas turbine engine casing
RU2211337C1 (ru) * 2002-01-11 2003-08-27 Открытое акционерное общество "Авиадвигатель" Ротор многоступенчатой турбины газотурбинного двигателя
GB2388161A (en) 2002-05-02 2003-11-05 Rolls Royce Plc Gas turbine engine compressor casing
DE10223655B3 (de) 2002-05-28 2004-02-12 Mtu Aero Engines Gmbh Anordnung zum axialen und radialen Fixieren der Leitschaufeln eines Leitschaufelkranzes einer Gasturbine
FR2857419B1 (fr) * 2003-07-11 2005-09-23 Snecma Moteurs Liaison amelioree entre disques aubages sur la ligne rotor d'un compresseur
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

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3644057A (en) † 1970-09-21 1972-02-22 Gen Motors Corp Locking device
US5232339A (en) † 1992-01-28 1993-08-03 General Electric Company Finned structural disk spacer arm
US20020187046A1 (en) † 2001-06-07 2002-12-12 Snecma Moteurs Turbomachine rotor assembly with two bladed-discs separated by a spacer
US20030133803A1 (en) † 2002-01-17 2003-07-17 Snecma Moteurs Turbomachine rotor arrangement
US20050111970A1 (en) † 2003-11-26 2005-05-26 Gabriel Suciu Turbine durm rotor for a turbine engine

Also Published As

Publication number Publication date
JP2006090320A (ja) 2006-04-06
FR2875534A1 (fr) 2006-03-24
RU2377417C2 (ru) 2009-12-27
FR2875534B1 (fr) 2006-12-22
CA2520069C (fr) 2013-03-12
EP1637701A1 (fr) 2006-03-22
CA2520069A1 (fr) 2006-03-21
US20060251520A1 (en) 2006-11-09
EP1637701B1 (fr) 2017-01-04
US7507072B2 (en) 2009-03-24
JP5072207B2 (ja) 2012-11-14
RU2005129353A (ru) 2007-03-27

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