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EP4166754B1 - Ensemble rotor pour turbine à gaz avec surfaces de contact axiales inclinées formées sur des segments de rotor, turbine à gaz et turbine à gaz d'avion - Google Patents

Ensemble rotor pour turbine à gaz avec surfaces de contact axiales inclinées formées sur des segments de rotor, turbine à gaz et turbine à gaz d'avion Download PDF

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Publication number
EP4166754B1
EP4166754B1 EP22200151.3A EP22200151A EP4166754B1 EP 4166754 B1 EP4166754 B1 EP 4166754B1 EP 22200151 A EP22200151 A EP 22200151A EP 4166754 B1 EP4166754 B1 EP 4166754B1
Authority
EP
European Patent Office
Prior art keywords
contact surface
rotor
gas turbine
turbine
radial direction
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
EP22200151.3A
Other languages
German (de)
English (en)
Other versions
EP4166754A1 (fr
Inventor
Daniel Theurich
Knut Werner
Hans-Peter Hackenberg
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 Aero Engines AG
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 Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP4166754A1 publication Critical patent/EP4166754A1/fr
Application granted granted Critical
Publication of EP4166754B1 publication Critical patent/EP4166754B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • US 20100290904 A1 discloses a rotor arrangement with wedge-shaped contact surfaces.
  • US 8 459 943 B2 discloses a rotor arrangement with wedge-shaped contact surfaces.
  • US 8794 923 B2 discloses a rotor arrangement with wedge-shaped contact surfaces.
  • US 2011/0219781 A1 and US 2020/0291781 A1 discloses a rotor arrangement with wedge-shaped contact surfaces.
  • US 2020/0291781 A1 discloses a rotor arrangement with wedge-shaped contact surfaces.
  • a rotor arrangement for a gas turbine in particular an aircraft gas turbine, comprising a plurality of rotor segments arranged one after the other in the axial direction and connected to one another in the axial direction by at least one tie rod device; wherein a rotor segment at the front in the axial direction has a first contact surface and a rotor segment at the rear in the axial direction has a second contact surface, wherein the first contact surface and the second contact surface are at least partially in contact with one another, and wherein the first contact surface and the second contact surface are substantially annular and extend in the radial direction and the circumferential direction.
  • first contact surface and/or the second contact surface extend at least partially inclined with respect to the radial direction, wherein an angle is formed between the first contact surface and the second contact surface with respect to a sectional plane spanned by the axial direction and the radial direction.
  • the first contact surface can be substantially parallel to the radial direction, and the second contact surface can be inclined to the radial direction.
  • the reverse configuration is also conceivable, whereby the second contact surface can be substantially parallel to the radial direction, and the first contact surface can be inclined to the radial direction.
  • the front rotor segment may be a rotor blade ring and the rear rotor segment may be a seal carrier.
  • the angle between the first contact surface and the second contact surface can be 0.5° to 3°, in particular 0.8° to 1.2°.
  • the inclination or angle can be selected depending on the remaining geometry of the adjacent rotor segments or their contact surfaces. It is also conceivable that sections with different opening angles may arise along the radial direction between the two contact surfaces. For example, the opening angle may increase from radially inward to radially outward.
  • the front rotor segment and the rear rotor segment are clamped together via a single contact surface pair consisting of the first annular contact surface and the second annular contact surface.
  • a single contact surface pair consisting of the first annular contact surface and the second annular contact surface.
  • the first contact surface and the second contact surface can each be designed as flat annular surfaces.
  • first and second rotor segments does not describe the formation of pairs within the rotor arrangement.
  • a second rotor segment can also function as the first rotor segment if another (total third) rotor segment is axially connected.
  • Fig. 1 shows a schematic and simplified illustration of an aircraft gas turbine 10, which is illustrated purely by way of example as a bypass engine.
  • the gas turbine 10 comprises a fan 12, which is surrounded by an indicated casing 14.
  • the fan 12 is followed by a compressor 16, which is accommodated in an indicated inner casing 18 and can be of single-stage or multi-stage design.
  • the combustion chamber 20 is connected to the compressor 16. Hot exhaust gas flowing out of the combustion chamber then flows through the adjoining turbine 22, which can be of single-stage or multi-stage design.
  • the turbine 22 comprises a high-pressure turbine 24 and a low-pressure turbine 26.
  • a hollow shaft 28 connects the high-pressure turbine 24 to the compressor 16, in particular a high-pressure compressor 29, so that they are driven or rotated together.
  • a further internal shaft 30 in the radial direction RR of the turbine connects the low-pressure turbine 26 to the fan 12 and to a low-pressure compressor 32, so that they are jointly driven and rotated.
  • a thrust nozzle 33, only indicated here, is connected to the turbine 22.
  • a turbine intermediate casing 34 is arranged between the high-pressure turbine 24 and the low-pressure turbine 26, said intermediate casing being arranged around the shafts 28, 30.
  • Hot exhaust gases from the high-pressure turbine 24 flow through the turbine intermediate casing 34 in its radially outer region 36.
  • the hot exhaust gases then enter an annular space 38 of the low-pressure turbine 26.
  • Rotor blade rings 27 of the compressors 28, 32 and the turbines 24, 26 are shown as examples.
  • conventionally present guide vane rings 31 are shown as examples only for the compressor 32.
  • Fig. 2 shows a simplified and schematic sectional view of a front rotor segment 40 and a rear rotor segment 42 of a rotor assembly 100.
  • the front rotor segment 40 is a rotor blade ring.
  • the rear rotor segment 42 is, in this example, a seal carrier element with a radially outwardly projecting seal section 44 of a labyrinth seal.
  • the first rotor segment 40 and the second rotor segment 42 can also be other rotating components of the turbine 22 of the gas turbine 10.

Landscapes

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

Claims (7)

  1. Système à rotor (100) pour une turbine à gaz (10), en particulier une turbine à gaz d'aéronef, comportant
    plusieurs segments de rotor (40, 42) disposés les uns après les autres dans la direction axiale (AR), lesquels sont reliés entre eux dans la direction axiale (AR) par au moins un dispositif formant tirant d'ancrage ;
    dans lequel un segment de rotor (40) avant dans la direction axiale (AR) présente une première surface de contact (40k) et un segment de rotor (42) arrière dans la direction axiale (AR) présente une seconde surface de contact (42k),
    dans lequel la première surface de contact (40k) et la seconde surface de contact (42k) entrent au moins partiellement en contact l'une avec l'autre,
    dans lequel la première surface de contact (40k) et la seconde surface de contact (42k) sont réalisées de manière sensiblement annulaire et s'étendent dans la direction radiale (RR) et dans la direction circonférentielle,
    caractérisé en ce que la première surface de contact (40k) et/ou la seconde surface de contact (42k) s'étendent au moins partiellement de manière inclinée par rapport à la direction radiale (RR), dans lequel un angle (α) est formé entre la première surface de contact (40k) et la seconde surface de contact (42k) par rapport à un plan de coupe défini par la direction axiale (AR) et la direction radiale (RR), dans lequel le segment de rotor avant et le segment de rotor arrière sont serrés l'un contre l'autre uniquement par l'intermédiaire d'une seule paire de surfaces de contact constituée de la première surface de contact annulaire et de la seconde surface de contact annulaire.
  2. Système à rotor (100) selon la revendication 1, caractérisé en ce que la première surface de contact (40k) est sensiblement parallèle à la direction radiale (RR) et en ce que la seconde surface de contact (42k) est inclinée par rapport à la direction radiale (RR).
  3. Système à rotor (100) selon la revendication 1 ou 2,
    caractérisé en ce que le segment de rotor (40) avant est une couronne d'aubes mobiles et en ce que le segment de rotor (42) arrière est un support à joint d'étanchéité.
  4. Système à rotor (100) selon l'une des revendications précédentes, caractérisé en ce que l'angle (α) entre la première surface de contact (40k) et la seconde surface de contact (42k) est compris entre 0,5° et 3°, en particulier entre 0,8° et 1,2°.
  5. Système à rotor (100) selon l'une des revendications précédentes, caractérisé en ce que tant la première surface de contact (40k) que la seconde surface de contact (42k) ne sont pas inclinées de plus de 10°, en particulier de plus de 5°, par rapport à la direction radiale.
  6. Turbine à gaz (10), en particulier turbine à gaz d'aéronef, comportant au moins un système à rotor (100) selon l'une des revendications précédentes.
  7. Turbine à gaz (10) selon la revendication 6, dans laquelle le système à rotor (100) fait partie d'une turbine basse pression (26) ou d'une turbine moyenne pression ou d'une turbine haute pression (24).
EP22200151.3A 2021-10-12 2022-10-06 Ensemble rotor pour turbine à gaz avec surfaces de contact axiales inclinées formées sur des segments de rotor, turbine à gaz et turbine à gaz d'avion Active EP4166754B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102021126427.8A DE102021126427A1 (de) 2021-10-12 2021-10-12 Rotoranordnung für eine Gasturbine mit an Rotorsegmenten ausgebildeten, geneigten axialen Kontaktflächen, Gasturbine und Fluggasturbine

Publications (2)

Publication Number Publication Date
EP4166754A1 EP4166754A1 (fr) 2023-04-19
EP4166754B1 true EP4166754B1 (fr) 2025-07-02

Family

ID=83688752

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22200151.3A Active EP4166754B1 (fr) 2021-10-12 2022-10-06 Ensemble rotor pour turbine à gaz avec surfaces de contact axiales inclinées formées sur des segments de rotor, turbine à gaz et turbine à gaz d'avion

Country Status (3)

Country Link
US (1) US11795822B2 (fr)
EP (1) EP4166754B1 (fr)
DE (1) DE102021126427A1 (fr)

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT378575B (de) 1979-10-25 1985-08-26 Elin Union Ag Rotor fuer eine thermische turbomaschine
JPS5830405A (ja) * 1981-08-19 1983-02-22 Hitachi Ltd 軸流機械のロ−タ取付装置
DE4215050C2 (de) 1992-05-07 1997-07-17 Audi Ag Vorrichtung an zumindest zwei benachbart auf einer Achse oder Welle dreh- oder schwenkbar zu lagernden metallischen Bauteilen
US7510380B2 (en) * 2004-07-13 2009-03-31 Honeywell International Inc. Non-parallel spacer for improved rotor group balance
US8267649B2 (en) * 2009-05-15 2012-09-18 General Electric Company Coupling for rotary components
GB0919202D0 (en) 2009-11-03 2009-12-16 Rolls Royce Plc A male or female element for a conic coupling
US8459943B2 (en) 2010-03-10 2013-06-11 United Technologies Corporation Gas turbine engine rotor sections held together by tie shaft, and with blade rim undercut
US20110219781A1 (en) 2010-03-10 2011-09-15 Daniel Benjamin Gas turbine engine with tie shaft for axial high pressure compressor rotor
US8794923B2 (en) 2010-10-29 2014-08-05 United Technologies Corporation Gas turbine engine rotor tie shaft arrangement
US9200520B2 (en) * 2012-06-22 2015-12-01 General Electric Company Gas turbine conical flange bolted joint
US20140064946A1 (en) * 2012-09-06 2014-03-06 Solar Turbines Incorporated Gas turbine engine compressor undercut spacer
US20140099210A1 (en) * 2012-10-09 2014-04-10 General Electric Company System for gas turbine rotor and section coupling
CA2930561A1 (fr) * 2013-11-26 2015-06-04 General Electric Company Ressort de support de boulon de liaison radial
US10125785B2 (en) * 2015-10-16 2018-11-13 Pratt & Whitney Reduced stress rotor interface
GB201602857D0 (en) * 2016-02-18 2016-04-06 Rolls Royce Plc Connection of rotatable parts
US20180058219A1 (en) * 2016-08-30 2018-03-01 Siemens Aktiengesellschaft Rotor disk having serrations and rotor
US11131195B2 (en) 2019-03-14 2021-09-28 Raytheon Technologies Corporation Tie shaft assembly for a gas turbine engine

Also Published As

Publication number Publication date
EP4166754A1 (fr) 2023-04-19
US11795822B2 (en) 2023-10-24
US20230111341A1 (en) 2023-04-13
DE102021126427A1 (de) 2023-04-13

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