EP4166754A1 - 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
EP4166754A1
EP4166754A1 EP22200151.3A EP22200151A EP4166754A1 EP 4166754 A1 EP4166754 A1 EP 4166754A1 EP 22200151 A EP22200151 A EP 22200151A EP 4166754 A1 EP4166754 A1 EP 4166754A1
Authority
EP
European Patent Office
Prior art keywords
contact surface
rotor
gas turbine
radial direction
axial 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.)
Pending
Application number
EP22200151.3A
Other languages
German (de)
English (en)
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
Pending 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
    • F01D5/066—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

  • the present invention relates to a rotor arrangement for a gas turbine, in particular an aircraft gas turbine, with 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, with a rotor segment at the front in the axial direction having a first contact surface and a rotor segment at the rear in the axial direction having a second Having contact surface, wherein the first contact surface and the second contact surface are at least partially in contact with each other, and wherein the first contact surface and the second contact surface are essentially ring-shaped and extend in the radial direction and circumferential direction.
  • a rotor arrangement for a gas turbine in particular an aircraft gas turbine, with a plurality of rotor segments which are arranged one after the other in the axial direction and are connected to one another in the axial direction by at least one tie rod device; wherein an axially forward rotor segment has a first contact surface and an axially rearward rotor segment 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 essentially annular are formed and extend in the radial direction and circumferential direction.
  • first contact surface and/or the second contact surface runs at least partially inclined with respect to the radial direction, with an angle being formed between the first contact surface and the second contact surface with respect to a sectional plane that is spanned by the axial direction and the radial direction is.
  • Such a configuration of the contact surfaces of axially adjacent rotor segments makes it possible to avoid a ring-line-like contact or force-transmitting region, which is described above as being disadvantageous. As a result, the transmission of axial forces can be better distributed over the entire contact surface, so that no unwanted stress peaks arise.
  • the first contact surface may be substantially parallel to the radial direction and the second contact surface may be inclined to the radial direction.
  • the reverse configuration is also conceivable, according to which the second contact surface can be essentially parallel to the radial direction and the first contact surface can be inclined to the radial direction.
  • the front rotor segment may be a bladed 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 the angle can be selected as a function of the remaining geometry of the rotor segments lying against one another or their contact surfaces. It is also conceivable that along the radial direction between the two contact surfaces there are sections with different opening angles. For example, the opening angle can increase from radially inside to radially outside.
  • the front rotor segment and the rear rotor segment can only be clamped together via a single pair of contact surfaces consisting of the first annular contact surface and the second annular contact surface.
  • a single pair of contact surfaces consisting of the first annular contact surface and the second annular contact surface.
  • the first contact surface and the second contact surface can preferably each be designed as planar ring surfaces.
  • both the first contact surface and the second contact surface can be inclined by no more than 10°, preferably no more than 5°, particularly preferably no more than 2° with respect to the radial direction. This avoids the occurrence of excessive radial forces when the rotor segments are braced, which could contribute to the rotor drum bending open during operation.
  • first and second rotor segment does not describe the formation of pairs within the rotor arrangement.
  • a second rotor segment can also function as a first rotor segment if a further (total third) rotor segment is connected axially.
  • a gas turbine in particular an aircraft gas turbine, can have at least one rotor arrangement as described above.
  • the rotor arrangement in the gas turbine can be part of a low-pressure turbine or a medium-pressure turbine or a high-pressure turbine.
  • FIG. 1 shows a schematic and simplified view of an aircraft gas turbine 10, which is illustrated purely by way of example as a turbofan engine.
  • the gas turbine 10 includes a fan 12 surrounded by a jacket 14 that is indicated.
  • the fan 12 is followed by a compressor 16, which is accommodated in an indicated inner housing 18 and can be of single-stage or multi-stage design.
  • the compressor 16 is followed by the combustion chamber 20 .
  • 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 includes 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 inner 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 driven or rotated together.
  • a thrust nozzle 33 which is only indicated here, is connected to the turbine 22 .
  • a turbine center frame 34 is arranged between the high-pressure turbine 24 and the low-pressure turbine 26, which is arranged around the shafts 28, 30.
  • hot exhaust gases from the high-pressure turbine 24 flow through the turbine center frame 34 .
  • the hot exhaust gas then reaches 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 by way of example.
  • guide vane rings 31 that are usually present are shown as an example only for compressor 32 .
  • FIG. 2 shows a front rotor segment 40 and a rear rotor segment 42 of a rotor arrangement 100 in a simplified and schematic sectional view.
  • the front rotor segment 40 is a moving blade ring in this example.
  • the rear rotor segment 42 is in in this example a seal carrier element with a radially outwardly projecting sealing 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 .
  • the first rotor segment 40 has a first contact surface 40k.
  • the first contact surface 40k is an axially rear surface section, in particular in the form of an annular surface of the front rotor segment 40.
  • the second rotor segment 42 has a second contact surface 42k.
  • the second contact surface 42k is an axially front surface section, in particular in the form of an annular surface of the rear rotor segment 42.
  • the first contact surface 40k and the second contact surface 42k are arranged opposite one another in the axial direction AR.
  • the front rotor segment 40 and the rear rotor segment 42 are connected to one another or braced against one another in the axial direction by means of a tie rod device, not shown here. As a result, the first contact surface 40k and the second contact surface 42k come or are in contact with one another.
  • an intermediate space 46 is formed at least partially or in sections between the two contact surfaces 40k, 42k. This space has a small size of a few millimeters or fractions of a millimeter.
  • the second contact surface 42k of the rear rotor segment 42 is slightly inclined with respect to the radial direction RR.
  • a small or very acute angle ⁇ is thus formed between the first contact surface 40k and the second contact surface 42k.
  • the inclination of the second contact surface 42k is selected in such a way that the angle ⁇ is approximately 0.5° to 3°, in particular approximately 1°.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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 Pending EP4166754A1 (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 (1)

Publication Number Publication Date
EP4166754A1 true EP4166754A1 (fr) 2023-04-19

Family

ID=83688752

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22200151.3A Pending EP4166754A1 (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) EP4166754A1 (fr)
DE (1) DE102021126427A1 (fr)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070009360A1 (en) * 2004-07-13 2007-01-11 Honeywell International, Inc. Non-parallel spacer for improved rotor group balance
US20100290904A1 (en) * 2009-05-15 2010-11-18 General Electric Company Coupling for rotary components
US20110219781A1 (en) 2010-03-10 2011-09-15 Daniel Benjamin Gas turbine engine with tie shaft for axial high pressure compressor rotor
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
EP2677120A1 (fr) * 2012-06-22 2013-12-25 General Electric Company Joint boulonné à bord conique de turbine à gaz
WO2014039826A1 (fr) * 2012-09-06 2014-03-13 Solar Turbines Incorporated Entretoise à dégagement de compresseur de moteur de turbine à gaz
US8794923B2 (en) 2010-10-29 2014-08-05 United Technologies Corporation Gas turbine engine rotor tie shaft arrangement
US20200291781A1 (en) 2019-03-14 2020-09-17 United Technologies Corporation Tie shaft assembly for a gas turbine engine

Family Cites Families (9)

* 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
GB0919202D0 (en) 2009-11-03 2009-12-16 Rolls Royce Plc A male or female element for a conic coupling
US20140099210A1 (en) * 2012-10-09 2014-04-10 General Electric Company System for gas turbine rotor and section coupling
WO2015081037A1 (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

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070009360A1 (en) * 2004-07-13 2007-01-11 Honeywell International, Inc. Non-parallel spacer for improved rotor group balance
US20100290904A1 (en) * 2009-05-15 2010-11-18 General Electric Company Coupling for rotary components
US20110219781A1 (en) 2010-03-10 2011-09-15 Daniel Benjamin Gas turbine engine with tie shaft for axial high pressure compressor rotor
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
US8794923B2 (en) 2010-10-29 2014-08-05 United Technologies Corporation Gas turbine engine rotor tie shaft arrangement
EP2677120A1 (fr) * 2012-06-22 2013-12-25 General Electric Company Joint boulonné à bord conique de turbine à gaz
WO2014039826A1 (fr) * 2012-09-06 2014-03-13 Solar Turbines Incorporated Entretoise à dégagement de compresseur de moteur de turbine à gaz
US20200291781A1 (en) 2019-03-14 2020-09-17 United Technologies Corporation Tie shaft assembly for a gas turbine engine

Also Published As

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

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