EP3477047B1 - Liaisons structurelles segmentées pour accord de fréquence de disque et moteur à turbine à gaz associé ayant telles liaisons - Google Patents

Liaisons structurelles segmentées pour accord de fréquence de disque et moteur à turbine à gaz associé ayant telles liaisons Download PDF

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Publication number
EP3477047B1
EP3477047B1 EP18201780.6A EP18201780A EP3477047B1 EP 3477047 B1 EP3477047 B1 EP 3477047B1 EP 18201780 A EP18201780 A EP 18201780A EP 3477047 B1 EP3477047 B1 EP 3477047B1
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EP
European Patent Office
Prior art keywords
flange
fan
section
segmented structural
coupled
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EP18201780.6A
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German (de)
English (en)
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EP3477047A1 (fr
Inventor
Peter V. Tomeo
James H. MOFFITT
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RTX Corp
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Raytheon Technologies Corp
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    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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
    • F01D5/10—Anti- vibration means
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan 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
    • 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
    • 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 disclosure relates generally to fans and fan hubs of gas turbine engines.
  • Gas turbine engines typically include a fan section to drive inflowing air, a compressor section to pressurize inflowing air, a combustor section to burn a fuel in the presence of the pressurized air, and a turbine section to extract energy from the resulting combustion gases.
  • the fan section may include a plurality of fan blades coupled to a fan hub. The fan hub may experience vibrational modes in operation.
  • US 2016/298458 A1 discloses a rotor stage of a gas turbine engine comprising a circumferentially extending damper ring.
  • US 2017/211592 A1 discloses a rotor disc in an aircraft engine comprising a damping element.
  • US 2010/124495 A1 discloses an aft hub for a rotor stage of a gas turbine engine.
  • US 3056579 A discloses a disk-joining member for a turbine rotor of a gas turbine engine.
  • US 2016/298460 A1 discloses a rotor stage of a gas turbine engine comprising a circumferentially extending damper ring.
  • a fan section for a gas turbine engine as claimed in claim 1 is provided.
  • the tail portion comprises a first bend. In various embodiments, the tail portion further comprises a second bend. In various embodiments, the base portion further comprises at least one of a captured nut, a nut plate, or a self-clinching nut.
  • the first flange is one of a J-flange or a scalloped flange.
  • the blade ring pivots over the cone arm about the web in response to a rotation of the hub.
  • the first flange is coupled to the blade ring and, in response to the blade ring pivoting over the cone arm about the web, is driven toward the forward flange.
  • a gas turbine engine as claimed in claim 8 is provided.
  • the tail portion comprises a first bend.
  • a plurality of segmented structural links are distributed symmetrically about a circumference of the fan disk.
  • the segmented structural link extends around a portion of a circumference of the fan disk between a J-flange and a scalloped flange.
  • a method of tuning a vibrational response of a fan disk as claimed in claim 11 is provided.
  • Gas turbine engine 20 may be a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines may include, for example, an augmenter section among other systems or features.
  • fan section 22 can drive air along a bypass flow-path B while compressor section 24 can drive air for compression and communication into combustor section 26 then expansion through turbine section 28.
  • turbofan gas turbine engine 20 depicted as a turbofan gas turbine engine 20 herein, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures.
  • Gas turbine engine 20 may generally comprise a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A-A' relative to an engine static structure 36 via one or more bearing systems 38 (shown as bearing system 38-1 and bearing system 38-2). It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, including for example, bearing system 38, bearing system 38-1, and bearing system 38-2.
  • Low speed spool 30 may generally comprise an inner shaft 40 that interconnects a fan 42, a low pressure (or first) compressor section 44 (also referred to a low pressure compressor) and a low pressure (or first) turbine section 46.
  • Inner shaft 40 may be connected to fan 42 through a geared architecture 48 that can drive fan 42 at a lower speed than low speed spool 30.
  • Geared architecture 48 may comprise a gear assembly 60 enclosed within a gear housing 62.
  • Gear assembly 60 couples inner shaft 40 to a rotating fan structure.
  • High speed spool 32 may comprise an outer shaft 50 that interconnects a high pressure compressor (“HPC") 52 (e.g., a second compressor section) and high pressure (or second) turbine section 54.
  • HPC high pressure compressor
  • a combustor 56 may be located between HPC 52 and high pressure turbine 54.
  • a mid-turbine frame 57 of engine static structure 36 may be located generally between high pressure turbine 54 and low pressure turbine 46.
  • Mid-turbine frame 57 may support one or more bearing systems 38 in turbine section 28.
  • Inner shaft 40 and outer shaft 50 may be concentric and rotate via bearing systems 38 about the engine central longitudinal axis A-A', which is collinear with their longitudinal axes.
  • a "high pressure" compressor or turbine experiences a higher pressure than a corresponding "low pressure” compressor or turbine.
  • the core airflow C may be compressed by low pressure compressor 44 then HPC 52, mixed and burned with fuel in combustor 56, then expanded over high pressure turbine 54 and low pressure turbine 46.
  • Mid-turbine frame 57 includes airfoils 59 which are in the core airflow path.
  • Low pressure turbine 46, and high pressure turbine 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
  • Gas turbine engine 20 may be, for example, a high-bypass geared aircraft engine. In various embodiments, the bypass ratio of gas turbine engine 20 may be greater than about six (6). In various embodiments, the bypass ratio of gas turbine engine 20 may be greater than ten (10).
  • geared architecture 48 may be an epicyclic gear train, such as a star gear system (sun gear in meshing engagement with a plurality of star gears supported by a carrier and in meshing engagement with a ring gear) or other gear system. Geared architecture 48 may have a gear reduction ratio of greater than about 2.3 and low pressure turbine 46 may have a pressure ratio that is greater than about five (5). In various embodiments, the bypass ratio of gas turbine engine 20 is greater than about ten (10:1).
  • the diameter of fan 42 may be significantly larger than that of the low pressure compressor 44, and the low pressure turbine 46 may have a pressure ratio that is greater than about (5:1). Low pressure turbine 46 pressure ratio may be measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of low pressure turbine 46 prior to an exhaust nozzle. It should be understood, however, that the above parameters are exemplary of various embodiments of a suitable geared architecture engine and that the present disclosure contemplates other gas turbine engines including direct drive turbofans.
  • the next generation of turbofan engines may be designed for higher efficiency which is associated with higher pressure ratios and higher temperatures in the HPC 52. These higher operating temperatures and pressure ratios may create operating environments that may cause thermal loads that are higher than the thermal loads encountered in conventional turbofan engines, which may shorten the operational life of current components.
  • HPC 52 may comprise alternating rows of rotating rotors and stationary stators.
  • Stators may have a cantilevered configuration or a shrouded configuration.
  • a stator may comprise a stator vane, a casing support and a hub support.
  • a stator vane may be supported along an outer diameter by a casing support and along an inner diameter by a hub support.
  • a cantilevered stator may comprise a stator vane that is only retained and/or supported at the casing (e.g., along an outer diameter).
  • rotors may be configured to compress and spin a fluid flow.
  • Stators may be configured to receive and straighten the fluid flow.
  • the fluid flow discharged from the trailing edge of stators may be straightened (e.g., the flow may be directed in a substantially parallel path to the centerline of the engine and/or HPC) to increase and/or improve the efficiency of the engine and, more specifically, to achieve enhanced compression and efficiency when the straightened air is compressed and spun by rotor 64.
  • a fan section 200 having a segmented structural link comprises blade 206 coupled at blade root 207 to a fan disk 208 and compressor inlet cone 204.
  • Fan 202 may be coupled to a shaft, such as inner shaft 40, where inner shaft 40 may be in mechanical communication with geared architecture 48.
  • Tip 205 of blade 206 lies proximate rub strip 214 which forms a part of the inner aerodynamic surface 216 of fan case 210.
  • a segmented structural link 302 lies radially inward of blade 206 aft of compressor inlet cone 204 at the forward face of fan disk 208.
  • a plurality of segmented structural links may be coupled circumferentially about the forward face of the disk.
  • segmented structural link 302 may be coupled proximate and radially outward of a shaft, such as inner shaft 40.
  • Fan case 210 may be coupled at an aft end to pylon 218 which may be coupled to compressor case 220.
  • gas 222 such as, for example air
  • Rotating fan 202 tends to conduct gas 222 along inner aerodynamic surface 215 toward pylon 218 passing between inner aerodynamic surface 215 and compressor case 220 as fan exhaust 224.
  • a segmented structural link 302 is shown coupled to a fan disk 300.
  • FIG 3A illustrates fan disk 300 in a section through the x-y plane and
  • FIG 3B illustrates a perspective view of the fan disk 300 from the forward face looking aft.
  • Segmented structural link 302 comprises a base portion 304 and a tail 306 extending at an angle ⁇ relative to the plane of the forward face 305 of base portion 304.
  • Tail 306 extends radially inward (along the x and y-axis) from the base portion toward a distal end 308 and may comprise one or more bends.
  • tail 306 may have a distal taper (along the y-axis) from base portion 304 toward distal end 308.
  • Segmented structural link 302 is coupled at the base portion 304 to J-flange 312, with forward face 305 in contact with an aft face of J-flange 312.
  • base portion 304 further comprises a captured nut 321 and segmented structural link 302 that may be coupled at the base portion 304 via first fastener 310 extending through J-flange 312 and base portion 304 to engage captured nut 321.
  • Distal end 308 is coupled at aft face 309 to forward flange 316 of hub 322.
  • hub 322 engages a shaft, such as inner shaft 40, at splines 324 and in response to rotation of the shaft transmits torque from the shaft via cone arm 326 and web 328 to blade ring 330 causing blade ring 330 to rotate about the axis of the shaft.
  • Blade ring 330 comprises channels 334 configured to receive a blade at a blade root, such as, for example, receiving blade 206 at blade root 207, and in this regard a fan, such as fan 202, may be caused to rotate about the shaft.
  • vibrations may be induced in the structure of the fan manifesting as a vibrational bending mode such as, for example, a first bending mode, a second bending mode, or a third bending mode.
  • Blade ring 330 is coupled to J-flange 312 and, in response to a bending mode, tends to pivot over cone arm 326 about web 328 tending to induce a torque 332 which tends to cause a downward (relative to the y-axis) deflection of J-flange 312 which is in turn transmitted as a downward (relative to the y-axis) load "F" at J-flange 312.
  • segmented structural link 302 may be said to increase the stiffness of a fan disk, such as fan disk 208, by resisting vibrationally induced bending loads.
  • a segmented structural link 402 is shown coupled to a fan disk 400, which may comprise features, geometries, construction, manufacturing techniques, and/or internal components similar to fan disk 300 of FIGS. 3A and 3B .
  • FIG 4A illustrates fan disk 400 in a section through the x-y plane and
  • FIG 4B illustrates a perspective view of the fan disk 400 from the forward face looking aft.
  • Segmented structural link 402 comprises a base portion 404 and tail portion 408 having a first bend 406 proximate base portion 404, a second bend 410 proximate a distal end 412, and extending at an angle ⁇ relative to the plane of the aft face 434 of the base portion 404.
  • Segmented structural link 402 extends in a continuous arc segment over a portion of the circumference of fan disk 400 and base portion 404 is coupled to J-flange 418 with aft face 434 of base portion 404 in contact with a forward face of J-flange 418 and coupled to scalloped flange 419 with aft face 434 of base portion 404 in contact with a forward face of scalloped flange 419.
  • Distal end 412 is coupled at aft face 434 to forward flange 416 of hub 422.
  • blade ring 430 tends to pivot over cone arm 426 about web 428 tending to induce a torque 432 which tends to cause a downward (relative to the y-axis) deflection of J-flange 418 and scalloped flange 419 which is in turn transmitted as a downward (relative to the y-axis) load "F" at J-flange 418 and scalloped flange 419.
  • segmented structural link 402 Downward load “F” is transmitted through segmented structural link 402 into forward flange 416 and is resisted by upward (relative to the y-axis) load “C” at forward flange 416 tending thereby to place segmented structural link 402 in compression.
  • segmented structural link 402 may be said to increase the stiffness of a fan disk, such as fan disk 208, by resisting vibrationally induced bending loads.
  • a blade ring such as, for example, blade ring 330, may comprise one or more flanges or J-flanges, such as J-flange 312 or scalloped flange 313.
  • one or more segmented structural links such as, for example, segmented structural link 302 or segmented structural link 402, may be located circumferentially around the forward end of a fan disk, such as fan disk 300, and coupled between one or more flanges or J-flanges, such as J-flange 312 or scalloped flange 313, and a forward flange such as, for example forward flange 316 of a hub, such as hub 322, to resist vibrationally induced bending loads.
  • segmented structural link 402 extends around a portion of the circumference of a fan disk, such as, for example, fan disk 400 between a J-flange and a scalloped flange or may extend around the entire circumference of a fan disk.
  • a fastener such as fastener 314 or fastener 421, may comprise a threaded stud coupled to a forward flange, such as forward flange 316.
  • a captured nut such as captured nut 321 or captured nut 420, may comprise a self-clinching nut, a nut plate, or any other captured fastener know to those skilled in the art.
  • a segmented structural link is one of a metal, an alloy, a steel, a titanium, a titanium alloy, a nickel, or a nickel alloy.
  • angle ⁇ is between ten degrees (10°) and fifty degrees (50°). In various embodiments, angle ⁇ is between twenty-five degrees (25°) and forty-five degrees (45°).
  • a method 500 of tuning the vibrational response of a fan disk comprises calculating the vibrational mode shapes of a fan disk (502); determining a point of maximum relative downward deflection of a blade ring (504) of the fan disk; coupling a segmented structural link to the fan disk (506) at the point of maximum relative downward deflection between a first flange, such as, for example J-flange 312 of FIG 3A , and a second flange, such as, for example, forward flange 316 of FIG 3A .
  • references to "one embodiment”, “an embodiment”, “an example embodiment”, etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the present invention in alternative embodiments.
  • the terms “comprises”, “comprising”, or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

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Claims (11)

  1. Section de soufflante (200) pour un moteur à turbine à gaz, la section de soufflante (200) comprenant :
    un disque de soufflante (300 ; 400) comprenant un moyeu (322 ; 422) ; et
    une liaison structurelle segmentée (302 ; 402) couplée au disque de soufflante (300 ; 400), la liaison structurelle segmentée (302 ; 402) comprenant :
    une partie de base (304 ; 404) présentant une première face (305 ; 434) ;
    une partie de queue (306 ; 408) se prolongeant selon un angle (Θ) par rapport à la première face ; et
    une extrémité distale (308 ; 412) présentant une seconde face (309), dans laquelle l'extrémité distale (308 ; 412) est couplée au niveau de la seconde face à une bride avant du moyeu (322 ; 422) ;
    caractérisée en ce que :
    le moyeu (322 ; 422) comprend un bras conique (326 ; 426) couplé à un anneau d'aubes (330 ; 430) au niveau d'une âme (328 ; 428) ;
    la partie de base (304 ; 404) est couplée au niveau de la première face à une première bride du disque de soufflante (300 ; 400) ;
    la liaison structurelle segmentée (302 ; 402) est comprimée en réponse à l'entraînement de la première bride vers la bride avant ; et
    l'angle (Θ) est compris entre 10 et 50 degrés.
  2. Section de soufflante (200) selon la revendication 1, dans laquelle la partie de queue (408) comprend un premier coude (406) .
  3. Section de soufflante (200) selon la revendication 2, dans laquelle la partie de queue (408) comprend en outre un second coude (410).
  4. Section de soufflante (200) selon la revendication 1, 2 ou 3, dans laquelle la partie de base (304 ; 404) comprend en outre au moins l'un d'un écrou capturé (321 ; 420), d'une plaque d'écrou ou d'un écrou auto-serrant.
  5. Section de soufflante (200) selon une quelconque revendication précédente, dans laquelle la première bride est l'une parmi une bride en J (312 ; 418) ou une bride festonnée (319 ; 419).
  6. Section de soufflante (200) selon une quelconque revendication précédente, dans laquelle l'anneau d'aubes (330 ; 430) pivote au-dessus du bras conique (326 ; 426) autour de l'âme (328 ; 428) en réponse à une rotation du moyeu (322 ; 422).
  7. Section de soufflante (200) selon la revendication 6, dans laquelle la première bride est couplée à l'anneau d'aubes (330 ; 430) et, en réponse au pivotement de l'anneau d'aubes (330 ; 430) au-dessus du bras conique (326 ; 436) autour de l'âme (328 ; 428), est configurée pour être entraînée vers la bride avant.
  8. Moteur à turbine à gaz (20) comprenant :
    la section de soufflante (200) selon une quelconque revendication précédente ;
    une section de compresseur (24) configurée pour comprimer un gaz (222) ;
    une section de chambre de combustion (26) à l'arrière de la section de compresseur (24) et configurée pour brûler le gaz (222) ; et
    une section de turbine (28) à l'arrière de la section de chambre de combustion (26) configurée pour extraire de l'énergie à partir du gaz (222).
  9. Moteur à turbine à gaz (20) selon la revendication 8, dans lequel une pluralité de liaisons structurelles segmentées (302 ; 402) sont réparties symétriquement autour d'une circonférence du disque de soufflante (300 ; 400).
  10. Moteur à turbine à gaz (20) selon la revendication 8 ou 9, dans lequel la liaison structurelle segmentée (302 ; 402) se prolonge autour d'une partie d'une circonférence du disque de soufflante (300 ; 400) entre une bride en J (312 ; 418) et une bride festonnée (319 ; 419).
  11. Procédé (500) de réglage d'une réponse vibratoire d'un disque de soufflante (300 ; 400) selon la revendication 1, caractérisé en ce que le procédé comprend :
    le calcul d'une forme de mode vibratoire du disque de soufflante (300 ; 400) ;
    la détermination d'un point de déviation relative maximale vers le bas de l'anneau d'aubes (330 ; 430) du disque de soufflante (300 ; 400) ; et
    le couplage de la liaison structurelle segmentée (302 ; 402) au disque de soufflante (300 ; 400) au niveau du point de déviation relative maximale vers le bas entre la première bride et la bride avant.
EP18201780.6A 2017-10-25 2018-10-22 Liaisons structurelles segmentées pour accord de fréquence de disque et moteur à turbine à gaz associé ayant telles liaisons Active EP3477047B1 (fr)

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US15/793,838 US20190120255A1 (en) 2017-10-25 2017-10-25 Segmented structural links for coupled disk frequency tuning

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EP3477047B1 true EP3477047B1 (fr) 2023-10-04

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Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2571176B (en) * 2017-12-14 2022-07-20 Safran Aircraft Engines Damping device
US11021962B2 (en) * 2018-08-22 2021-06-01 Raytheon Technologies Corporation Turbulent air reducer for a gas turbine engine
US11686415B2 (en) 2019-04-01 2023-06-27 Inogen, Inc. Compact portable oxygen concentrator
US11686202B1 (en) 2021-12-20 2023-06-27 Rolls-Royce North American Technologies Inc. Rotor damper with contact biasing feature for turbine engines

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160298460A1 (en) * 2015-04-13 2016-10-13 Rolls-Royce Plc Rotor damper

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3056579A (en) * 1959-04-13 1962-10-02 Gen Electric Rotor construction
US6375428B1 (en) * 2000-08-10 2002-04-23 The Boeing Company Turbine blisk rim friction finger damper
US6666017B2 (en) * 2002-05-24 2003-12-23 General Electric Company Counterrotatable booster compressor assembly for a gas turbine engine
US8287242B2 (en) * 2008-11-17 2012-10-16 United Technologies Corporation Turbine engine rotor hub
US8459954B2 (en) * 2010-01-19 2013-06-11 United Technologies Corporation Torsional flexing energy absorbing blade lock
DE102016101427A1 (de) * 2016-01-27 2017-07-27 Rolls-Royce Deutschland Ltd & Co Kg Rotor in BLISK- oder BLING-Bauweise eines Flugtriebwerks

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160298460A1 (en) * 2015-04-13 2016-10-13 Rolls-Royce Plc Rotor damper

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