EP4144957A1 - Disque de rotor pourvu de bras incurvé de rotor pour une turbine à gaz d'avion - Google Patents

Disque de rotor pourvu de bras incurvé de rotor pour une turbine à gaz d'avion Download PDF

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Publication number
EP4144957A1
EP4144957A1 EP22192078.8A EP22192078A EP4144957A1 EP 4144957 A1 EP4144957 A1 EP 4144957A1 EP 22192078 A EP22192078 A EP 22192078A EP 4144957 A1 EP4144957 A1 EP 4144957A1
Authority
EP
European Patent Office
Prior art keywords
rotor
gas turbine
disk
compressor
main body
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.)
Withdrawn
Application number
EP22192078.8A
Other languages
German (de)
English (en)
Inventor
Thomas Binsteiner
Knut Werner
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 EP4144957A1 publication Critical patent/EP4144957A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • 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
    • F01D5/027—Arrangements for balancing
    • 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
    • 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
    • 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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F01D5/026—Shaft to shaft connections
    • 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
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F05D2220/3217—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the first stage of a compressor or a low pressure compressor
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F05D2220/3218—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for an intermediate stage of a compressor
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F05D2220/3219—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the last stage of a compressor or a high pressure compressor
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the present invention relates to a rotor disk for a compressor of a gas turbine, in particular an aircraft gas turbine, with a main body, at least one rotor arm protruding from the main body in the axial direction, the rotor arm having, based on a sectional view in the sectional plane spanned by the axial direction and the radial direction: the initial portion merging the main body; an end portion remote from the main body forming a kind of free end in the axial direction, the beginning portion and the end portion being connected to each other by means of an intermediate portion.
  • the invention also relates to a rotor blade disk with such a rotor disk, a compressor with such a rotor blade disk and a gas turbine with such a compressor.
  • a compressor in particular a high-pressure compressor, of an (aircraft) gas turbine
  • axial tension forces are transmitted by means of the rotor arm of one rotor disk to an axially adjacent rotor disk, so that the multiple rotor disks braced against one another due to axial tensile forces can be stabilized.
  • the problem arises that in the case of axially adjacent rotor disks, which have a significantly different diameter, a relatively large radial distance must be bridged by means of the rotor arm in order to be able to support the acting distortion forces.
  • Previous rotor arms therefore have at least one kink along the axial direction and possibly also changes in material thickness, which, however, leads to undesired stresses in the rotor arm.
  • the object on which the invention is based is seen as specifying a rotor disk in which the axial power transmission is made possible with reduced stresses.
  • the intermediate section is curved with at least one radius of curvature.
  • the leading portion, the trailing portion and the intermediate portion may have substantially the same rotor arm thickness.
  • the two essentially straight beginning and end sections together with the curved intermediate section form a rotor arm which is essentially of the same thickness over its axial length.
  • the thickness of the rotor arm can be about 0.3 cm to 1.3 cm.
  • At least one sealing fin pointing radially outwards can be arranged on the rotor arm.
  • the at least one sealing fin is radially opposite to a sealing element attached to a stator or a guide vane ring, which usually has a honeycomb structure and into which the sealing fin can run in certain operating states of the gas turbine in order to enable sealing.
  • the radius of curvature of the intermediate section can be from about 2 cm to 6 cm, in particular about 2.5 cm to 5.1 cm.
  • a rotor blade disk for a compressor of a gas turbine, in particular an aircraft gas turbine can have a rotor disk as described above, the rotor blade disk having a plurality of rotor blades arranged next to one another in the circumferential direction and connected to the rotor disk.
  • the rotor disk and the moving blades can be designed in one piece with one another in the case of the rotating blade disk, in particular can be designed as a blisk.
  • a compressor in particular a high-pressure compressor, for a gas turbine, in particular an aircraft gas turbine, can have at least one rotor disk described above or at least one rotor blade disk described above.
  • An aircraft gas turbine can be equipped with such a compressor, in particular a high-pressure compressor.
  • 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. 1 shows a rotor disk 40 having a main body 42 and a rotor arm 44.
  • the rotor arm 44 is connected to the main body 42.
  • FIG. A further rotor disk 40a is arranged in front of the rotor disk 40 in relation to a flow direction of air LR, which flows through an annular space 46 indicated schematically by means of short dashed lines.
  • the two rotor disks 40, 40a are braced against one another in the axial direction AR, although this is not shown in the illustration.
  • the rotor arm 44 of the rotor disk 40 is supported in the axial direction AR and radial direction RR on the rotor disk 40a, so that acting forces of the axial tension can be transmitted.
  • a moving blade 48 is connected to the rotor disk 40 .
  • a rotor blade 48a is also attached to the rotor disk 40a.
  • the moving blades 48 or 48a it is pointed out that these can be designed in one piece with the respective rotor blade 40 or 40a, in particular can be designed as a so-called blisk.
  • openings to be provided in the rotor disks 40 or 40a can be in which rotor blade roots of rotor blades can be positively accommodated.
  • the rotor arm 44 can be divided into a beginning section 44a, an end section 44e and an intermediate section 44z.
  • the starting portion 44a is connected to the main body 42 and extends obliquely to the axial direction AR and the radial direction RR.
  • the starting section 44a is essentially straight.
  • the end portion 44e abuts the axially forward rotor disk 40a.
  • the end section 44e runs essentially parallel to the axial direction AR and essentially orthogonally to the radial direction RR. Acting axial forces can be optimally transmitted or supported by the end section 44e running essentially parallel to the axial direction AR.
  • the power flow along the axial direction AR in the rotor arm 44 and the rotor discs 40, 40a is in the Figures 2 and 3 illustrated in a simplified way by the dotted line KF.
  • the intermediate section 44z which extends between the beginning section 44a and the end section 44e, is curved or bent.
  • the intermediate section 44z has an inner radius Ri and an outer radius Ra in relation to a center point MP.
  • the two radii Ri and Ra are selected in such a way that the intermediate section 44z has a rotor arm thickness RD that remains essentially the same.
  • the beginning portion 44a and the ending portion 44e also have a rotor arm thickness RD that is substantially the same.
  • the entire rotor arm 44 has a continuous thickness RD that is kept substantially constant.
  • the radius of curvature Ri or Ra of the intermediate section 44z has a length of approximately 2 cm to 6 cm, in particular approximately 2.5 cm to 5.1 cm.
  • the substantially constant thickness RD of the rotor arm 44 is approximately 0.3 cm to 1.3 cm.
  • At least one sealing fin 50 can be provided on the rotor arm 44, which is arranged opposite a sealing inlet element of a stator or guide vane ring in an assembled state of a compressor.
  • FIG. 2 and 3 described rotor disk 40 with the curved rotor arm 44 can, for example, in an in 1 shown high-pressure compressor 29 of an aircraft gas turbine 10 may be arranged.
  • the in the Figures 2 and 3 described moving blades 48 or 48a can be parts of an in 1 indicated blade ring 27 to be.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Aviation & Aerospace Engineering (AREA)
EP22192078.8A 2021-09-07 2022-08-25 Disque de rotor pourvu de bras incurvé de rotor pour une turbine à gaz d'avion Withdrawn EP4144957A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102021123173.6A DE102021123173A1 (de) 2021-09-07 2021-09-07 Rotorscheibe mit gekrümmtem Rotorarm für eine Fluggasturbine

Publications (1)

Publication Number Publication Date
EP4144957A1 true EP4144957A1 (fr) 2023-03-08

Family

ID=83081623

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22192078.8A Withdrawn EP4144957A1 (fr) 2021-09-07 2022-08-25 Disque de rotor pourvu de bras incurvé de rotor pour une turbine à gaz d'avion

Country Status (3)

Country Link
US (1) US20230160395A1 (fr)
EP (1) EP4144957A1 (fr)
DE (1) DE102021123173A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060099070A1 (en) * 2004-11-10 2006-05-11 United Technologies Corporation Turbine engine disk spacers
EP1905952A2 (fr) * 2006-09-12 2008-04-02 United Technologies Corporation Aube statorique de compresseur et entretoise d'un moteur à turbine
US20140017087A1 (en) * 2012-07-10 2014-01-16 Pratt & Whitney Dynamic Stability and Mid Axial Preload Control for a Tie Shaft Coupled Axial High Pressure Rotor
EP3012411A1 (fr) * 2014-10-23 2016-04-27 United Technologies Corporation Rotor à aubage intégral ayant un bras axial et une poche
EP3091177A1 (fr) * 2015-05-07 2016-11-09 MTU Aero Engines GmbH Rotor pour une turbomachine et compresseur
EP3192966A1 (fr) * 2016-01-14 2017-07-19 MTU Aero Engines GmbH Rotor pour une turbomachine axiale comprenant une bride d'equilibrage orientee axialement et compresseur
FR3094398A1 (fr) * 2019-03-29 2020-10-02 Safran Aircraft Engines Ensemble pour un rotor de turbomachine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3710480B2 (ja) * 1994-08-24 2005-10-26 ユナイテッド テクノロジーズ コーポレイション 回転機械用回転可能なシール素子
US6267553B1 (en) * 1999-06-01 2001-07-31 Joseph C. Burge Gas turbine compressor spool with structural and thermal upgrades
US7059831B2 (en) * 2004-04-15 2006-06-13 United Technologies Corporation Turbine engine disk spacers
US9938840B2 (en) * 2015-02-10 2018-04-10 United Technologies Corporation Stator vane with platform having sloped face
EP3091178A1 (fr) * 2015-05-07 2016-11-09 MTU Aero Engines GmbH Tambour-rotor pour une turbomachine et compresseur

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060099070A1 (en) * 2004-11-10 2006-05-11 United Technologies Corporation Turbine engine disk spacers
EP1905952A2 (fr) * 2006-09-12 2008-04-02 United Technologies Corporation Aube statorique de compresseur et entretoise d'un moteur à turbine
US20140017087A1 (en) * 2012-07-10 2014-01-16 Pratt & Whitney Dynamic Stability and Mid Axial Preload Control for a Tie Shaft Coupled Axial High Pressure Rotor
EP3012411A1 (fr) * 2014-10-23 2016-04-27 United Technologies Corporation Rotor à aubage intégral ayant un bras axial et une poche
EP3091177A1 (fr) * 2015-05-07 2016-11-09 MTU Aero Engines GmbH Rotor pour une turbomachine et compresseur
EP3192966A1 (fr) * 2016-01-14 2017-07-19 MTU Aero Engines GmbH Rotor pour une turbomachine axiale comprenant une bride d'equilibrage orientee axialement et compresseur
FR3094398A1 (fr) * 2019-03-29 2020-10-02 Safran Aircraft Engines Ensemble pour un rotor de turbomachine

Also Published As

Publication number Publication date
US20230160395A1 (en) 2023-05-25
DE102021123173A1 (de) 2023-03-09

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