EP3433469B1 - Plattform, fananordnung und fan - Google Patents

Plattform, fananordnung und fan Download PDF

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Publication number
EP3433469B1
EP3433469B1 EP17716956.2A EP17716956A EP3433469B1 EP 3433469 B1 EP3433469 B1 EP 3433469B1 EP 17716956 A EP17716956 A EP 17716956A EP 3433469 B1 EP3433469 B1 EP 3433469B1
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EP
European Patent Office
Prior art keywords
platform
disk
fan
upstream
bottom wall
Prior art date
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Active
Application number
EP17716956.2A
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English (en)
French (fr)
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EP3433469A1 (de
Inventor
Thomas Alain DE GAILLARD
Alexandre Bernard Marie BOISSON
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
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Safran Aircraft Engines SAS
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Publication of EP3433469A1 publication Critical patent/EP3433469A1/de
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the present invention relates to the general field of aeronautical turbomachines, and more specifically to the field of blade and disk platforms of the fan of an aeronautical turbomachine, an assembly comprising the platforms and the disk, and a fan comprising this assembly.
  • the fan blade platforms In a turbomachine, the fan blade platforms must fulfill several functions. From an aerodynamic point of view, these platforms have the primary function of defining the air flow path. In addition, they must also be capable of withstanding high forces while deforming as little as possible and remaining integral with the disk which carries them.
  • the platforms have a first part making it possible to define the air flow path and to ensure the retention of the platform when the motor is rotating, and a second part making it possible to limit the deformations of the first part under the effects of centrifugal forces and to maintain the platform in position when the engine is stopped.
  • the platform can take the form of a box with a two-dimensional vein wall retained downstream by a drum and upstream by a shroud, the upstream retention by the shroud being carried out above the fan disc tooth (a flange of the shroud blocking the platform axially and radially upstream).
  • the document US 2016/0069355 A1 discloses an example of a turbomachine comprising blade platforms and a fan disk.
  • Such upstream retention carried out above the tooth of the disc with a ferrule has the disadvantage of imposing a high hub ratio, the hub ratio being the ratio of the radius taken between the axis of rotation and the point of the edge leading edge of the blade flush with the surface of the platform, on the radius taken between the axis of rotation and the outermost point of the leading edge.
  • this upstream retention is liable to generate over-stresses on the tooth and in the socket of the disc, at the level of the connection between the ferrule and the disc.
  • Axial means the direction of the greatest length of the platform, and “radial” means the direction perpendicular to the axial direction and to the main surface of the bottom wall.
  • Upstream means upstream with respect to the direction of air flow, when the platform rests on a fan disc.
  • the platform can take the form of a box formed by assembling the vein wall and the bottom wall.
  • the duct wall makes it possible to delimit the flow duct of the air entering the fan.
  • the bottom wall makes it possible to hold the vein wall in position, and also to limit its deformations under the effect of centrifugal forces.
  • the bottom wall also comprises a main surface which can be supported on a fan disk.
  • the axial and radial retention surfaces arranged on two axial ends of the platform, make it possible to retain and maintain the platform in position relative to the disc on which it rests, when the disc is in motion.
  • the radial retention surface arranged on the upstream axial end of the platform is offset radially with respect to a main surface of the bottom wall.
  • “Radially offset” means offset in the direction in which the bottom wall bears on the disc.
  • the radial retention surface and the main surface of the bottom wall can be substantially parallel with respect to each other.
  • This offset of the radial retention surface makes it possible to modify the shape of the upstream axial end of the stream wall, and therefore of the platform, with respect to known platforms.
  • the platform can take the form of a plunging box, that is to say the upstream axial end of which is offset radially with respect to the main surface of the bottom wall.
  • This modification of the shape of the platform thus makes it possible to modify the air flow path when the platform is placed in a fan, is therefore to reduce the hub ratio in order to improve the performance of the fan, and therefore to the turbomachine in which the fan is mounted.
  • the bottom wall has a surface inclined with respect to the main surface of the bottom wall, continuously connecting the main surface of the bottom wall and the radial retention surface disposed on the upstream axial end of the platform.
  • the radial retention surface arranged on the upstream axial end of the platform being offset radially with respect to the main surface of the bottom wall, the inclined surface corresponds to the zone of the bottom wall making it possible to compensate for the offset between the surface radial retention and the main surface of the bottom wall. It is therefore understood that the inclined surface rests on the disc.
  • the radial retention surface disposed on the upstream axial end of the platform, the inclined surface and the main surface of the bottom wall can be in one piece constituting the bottom wall.
  • the inclined surface is a straight wall portion.
  • the rectilinear wall portion linearly connects the radial retention surface with the main surface of the bottom wall, thus modifying the shape of the upstream axial end of the platform in order to reduce the hub ratio.
  • This rectilinear wall portion has the advantage of having a simple shape that is easy to produce, for example by machining.
  • the inclined surface is a curvilinear wall portion.
  • curvilinear wall portion progressively connects the radial retention surface with the main surface of the bottom wall, thus modifying the shape of the upstream axial end of the platform in order to reduce the hub ratio.
  • This portion of curvilinear wall has the advantage of softening the change in slope from the main surface of the bottom wall, avoiding the presence of a break at the junction between the inclined surface and the main surface, unlike the straight wall portion, and thus reduce the stresses at this junction.
  • the inclined surface and the vein wall are substantially parallel.
  • the upstream axial end of the platform has a plunging shape, the inclined surface and the section of the stream being inclined radially in the same way in the direction in which the platform bears on the disc.
  • This shape of the upstream axial end of the platform makes it possible to reduce the hub ratio.
  • upstream face is understood to mean upstream with respect to the direction in which the air flows, when the disc is placed in a fan.
  • Axial projections are understood to mean axial in the direction of air flow, when the disk is placed in a fan.
  • Randomly offset means offset towards the inside of the disc, that is to say towards the axis of rotation of the disc.
  • the disk can comprise as many axial projections as there are teeth.
  • the axial projections may each include a hole allowing the axial projections to be fixed to a fan platform retention flange, using a screw or a bolt, for example.
  • this fixing zone being offset radially with respect to the teeth of the disc, this has the advantage of freeing up space at the level of the upstream axial end of the tooth of the disc, making it possible, for example, to machine the tooth of the disc.
  • the axial projections are studs machined on the upstream face of the disc.
  • the fixing holes can make it possible to fix an element external to the disc, for example a retaining flange or a ferrule, using a screw or a bolt, for example.
  • Axial projections can also have an insertion hole machined radially on an outer face of the projections. The insertion holes may permit the insertion of fasteners, through which an outer member may be attached to the disc.
  • An upstream axial end of the disk teeth has a beveled surface.
  • the beveled surface may be in the form of an inclined surface, with respect to a main surface of the tooth of the disc, towards the inside of the disc.
  • the beveled surface can be produced by machining the upstream axial end of the tooth of the disc, for example. This machining is possible thanks to the space freed up by the radial offset of the axial projections on the upstream face of the disc.
  • the presence of this beveled surface has the advantage of being able to adapt the shape of the tooth of the disc to the shape of a platform bearing on the tooth, and thus of reducing the hub ratio to improve the performance of the fan.
  • the interface between the flange and the disc is offset radially towards the inside of the disc, with respect to the tooth of the disc, compared to known systems in which this interface is located at the level of the tooth of the disc.
  • This offset makes it possible to limit the stresses at the level of the upstream axial end of the teeth and of the grooves of the disc.
  • the offset of this interface makes it possible to free up space at the level of the upstream axial end of the tooth of the disc, offering more possibility of machining the tooth and therefore of modifying the shape of the platform and thus, reduction of the hub ratio.
  • the inclined surface of the bottom wall is in contact with the beveled surface of the tooth of the disc.
  • the inclined surface and the beveled surface can be parallel.
  • the disc tooth can be machined more freely.
  • the upstream axial end of the tooth may have a bevel to adapt to the shape of the platform, the beveled surface being parallel to the inclined surface of the platform.
  • the upstream retention flange is a ferrule.
  • This presentation also relates to a turbomachine fan comprising an assembly according to any one of the embodiments described in this presentation, and a plurality of vanes mounted in the grooves of the disk.
  • the term “longitudinal” and its derivatives are defined with respect to the main direction of the platform considered; the terms “radial”, “inner”, “outer” and their derivatives are defined with respect to the main axis of the turbomachine; finally, the terms “upstream” and “downstream” are defined with respect to the direction of flow of the fluid passing through the turbomachine. Also, unless otherwise indicated, the same reference signs in different figures designate the same characteristics.
  • FIG. 1 shows a schematic view in longitudinal section of a turbofan engine 1 centered on the axis A according to the invention. It comprises, from upstream to downstream: a fan 2, a low compressor pressure 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7.
  • FIG 2 shows a schematic view of the fan 2 of the figure 1 according to direction II.
  • the fan 2 comprises a fan disc 40 in which a plurality of grooves 42 are made at its outer periphery. These grooves 42 are rectilinear and extend axially from upstream to downstream all along the disc 40. They are also regularly distributed all around the axis A of the disc 40. In this way, each groove 42 defines with its neighbor a tooth 44 which also extends axially from upstream to downstream all along the disc 40. Equivalently, a groove 42 is delimited between two neighboring teeth 44.
  • the fan 2 further comprises a plurality of blades 20 of curvilinear profile (only four blades 20 have been shown on the figure 2 ).
  • Each blade 20 has a root 20a which is mounted in a respective groove 42 of the fan disk 40.
  • the root 20a of a blade 20 can have a fir tree or dovetail shape adapted to the geometry of the grooves 42.
  • the fan 2 comprises a plurality of added platforms 30, each platform 30 being mounted in the interval between two neighboring fan blades 20, in the vicinity of the feet 20a thereof, in order to delimit, on the interior side, a vein annular air inlet into the fan 2, the vein being delimited on the outside by a fan casing.
  • THE figures 1 and 2 also show an internal radius RI and an external radius RE.
  • the internal radius RI corresponds to the radius taken between the axis of rotation A and the point of the leading edge of a blade 20 flush with the surface of a platform 30.
  • the external radius RE corresponds to the radius taken between the axis of rotation A and the outermost point of the leading edge of a blade 20.
  • These two radii RI, RE are those used in the calculation of the hub ratio RI/RE that the assembly according to the invention proposes to reduce (in particular by reducing the internal radius RI). In other words, the reduction in the hub ratio, by acting in particular on the internal radius RI, amounts to bringing the aerodynamic air inlet vein closer to the fan disc.
  • the figures 3A and 3B show views in longitudinal section of the platform 30.
  • the platform 30, object of the present invention comprises a vein wall 34, a bottom wall 36, and radial and axial retention surfaces 38 and 39 arranged at the two axial ends of the platform 30.
  • the assembly formed by the vein wall 34 and the wall 36 forms a box 32, constituting the platform 30.
  • the bottom wall consists of a main surface 36a and an inclined surface 36b.
  • the inclined surface 36b continuously connects the main surface 36a and the retention surface 38, such that the retention surface 38, located at the upstream axial end of the platform, is offset radially with respect to the main surface 36a.
  • the inclined surface 36b is a straight wall portion.
  • the inclined surface 36b is a curvilinear wall portion.
  • FIG 4 shows a perspective view of a fan disk having an outer surface 40a and an upstream face 40b.
  • the outer surface 40a has a succession of grooves 42 in which a foot 20a of the fan blade 20 can be housed, and of teeth 44 interposed between the grooves 42, which can support the platforms 30 of the fan.
  • Each tooth 44 may have a major tooth surface 44a, and has a beveled surface 44b.
  • the beveled surface 44b is produced, for example by machining the upstream axial end of the tooth 44, so that the shape of the beveled surface 44b is identical to the shape of the inclined surface 36b of the platform 30.
  • the disc 40 comprises, on its upstream face 40b, a plurality of axial projections 46, which may have a cubic shape and be arranged circumferentially, at regular intervals, around the axis A.
  • the number of axial projections 46 may be equal to the number of teeth 44, each projection 46 being aligned radially with the corresponding tooth 44.
  • each axial projection 46 is offset radially towards the inside of the disc, that is to say towards the axis A, with respect to the corresponding tooth 44. For example, a distance between the A axis and a face external 46a of a projection 46 perhaps smaller than the distance between the axis A and a groove 42.
  • Each axial projection 46 may include a fixing hole 460b on its upstream face 46b, allowing the insertion of a fixing means 49, for example a screw or a bolt.
  • Each axial projection 46 may also include an insertion orifice 460a on its external face 46a, allowing the insertion of a fixing element 47, for example an insert, comprising a threaded hole.
  • an upstream retention flange 50 for example a ferrule
  • the fixing of an upstream retention flange 50 can thus be carried out at the level of an axial projection 46, by inserting for example the fixing means 49 through a flange orifice 52 and the orifice fixing element 460b of the projection, the fixing element 49 then being fixed, for example screwed, to the fixing element 47 inserted through the insertion hole 460a of the projection.
  • the retention flange 50 being fixed to the disc 40, an upper surface 54 of the flange 50 then makes it possible to ensure the radial retention of the platform 30.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Plattform (30), die imstande ist, zwischen zwei benachbarten Schaufeln (20) eines Fans (2) angeordnet zu sein und aufweist:
    - eine Kanalwand (34), um einen Luftströmungskanal des Fans (2) zu definieren,
    - eine Bodenwand (36) mit einer Hauptoberfläche (36a), um sich auf einer Fanscheibe (40) abzustützen;
    wobei die Plattform (30) eine axiale und radiale Halteoberfläche aufweist, die auf zwei axialen Enden der Plattform (30) angeordnet sind, wobei eine radiale Halteoberfläche (38) auf dem vorgelagerten axialen Ende der Plattform (30) und radial versetzt in der Stützrichtung der Bodenwand (36) auf der Scheibe (40) im Verhältnis zur Hauptoberfläche (36a) der Bodenwand (36) angeordnet ist, wobei die Bodenwand (36) eine im Verhältnis zur Hauptoberfläche (36a) der Bodenwand (36) geneigte Oberfläche (36b) aufweist, die die Hauptoberfläche (36a) der Bodenwand (36) und die radiale Halteoberfläche (38), die am vorgelagerten axialen Ende der Plattform (30) angeordnet ist, kontinuierlich verbindet, dadurch gekennzeichnet, dass die geneigte Oberfläche (36b) ausgelegt ist, um sich auf einer abgeschrägten Oberfläche (44b) eines Zahns (44) der Fanscheibe (40) abzustützen.
  2. Plattform (30) nach Anspruch 1, wobei die geneigte Oberfläche (36b) ein gerader Wandabschnitt ist.
  3. Plattform (30) nach Anspruch 1, wobei die geneigte Oberfläche (36b) ein gekrümmter Wandabschnitt ist.
  4. Plattform (30) nach einem der Ansprüche 1 bis 3, wobei die geneigte Oberfläche (36b) und die Kanalwand (34) etwa parallel sind.
  5. Anordnung, die mindestens eine Plattform (30) nach einem der Ansprüche 1 bis 4 umfasst und eine Scheibe (40), die imstande ist, Plattformen (30) und Schaufeln (20) eines Fans (2) zu tragen, wobei die Scheibe (40) eine äußere Oberfläche (40a) aufweist, die eine Abfolge von Rillen (42) zur Aufnahme der Schaufeln (20) von Fan und von Zähnen (44) aufweist, die zwischen den Rillen (42) angeordnet sind, um die Fanplattformen (30) zu stützen, eine der Scheibe vorgelagerte Fläche (40b) und eine Vielzahl axialer Vorsprünge (46), die radial um eine Achse A der Scheibe auf der vorgelagerten Fläche (40b) der Scheibe (40) angeordnet sind und imstande, an einem Halteflansch (50) der Fanplattform befestigt zu sein, wobei die Vorsprünge (46) radial zum Inneren der Scheibe (40) im Verhältnis zu den Zähnen (44) der Scheibe (40) versetzt sind, wobei ein vorgelagertes axiales Ende der Zähne (44) der Scheibe eine abgeschrägte Oberfläche (44b) aufweist, wobei, wenn sich die Plattform (30) auf einem Zahn (44) der Scheibe (40) abstützt, die geneigte Oberfläche (36b) der Bodenwand (36) mit der abgeschrägten Oberfläche (44b) des Zahns (44) der Scheibe im Kontakt ist, wobei die Anordnung ferner mindestens einen vorgelagerten Halteflansch (50) umfasst, um den axialen und radialen Halt des vorgelagerten axialen Endes der Plattform (30) zu sichern, wobei der vorgelagerte Halteflansch (50) auf mindestens einem axialen Vorsprung (46) der Vielzahl axialer Vorsprünge (46) der vorgelagerten Fläche (40b) der Scheibe (40) befestigt ist.
  6. Anordnung nach Anspruch 5, wobei die axialen Vorsprünge (46) Klötzchen sind, die auf der vorgelagerten Fläche (40b) der Scheibe ausgearbeitet sind.
  7. Anordnung nach Anspruch 5 oder 6, wobei die geneigte Oberfläche (36b) und die abgeschrägte Oberfläche (44b) parallel sind.
  8. Anordnung nach einem der Ansprüche 5 bis 7, wobei der vorgelagerte Halteflansch (50) ein Ring ist.
  9. Fan (2) einer Turbomaschine, umfassend eine Anordnung nach einem der Ansprüche 5 bis 8 und eine Vielzahl von Schaufeln (20), die in den Rillen (42) der Scheibe (40) angebracht sind.
EP17716956.2A 2016-03-21 2017-03-20 Plattform, fananordnung und fan Active EP3433469B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1652401A FR3048997B1 (fr) 2016-03-21 2016-03-21 Plateforme d'aube et disque de soufflante de turbomachine aeronautique
PCT/FR2017/050649 WO2017162975A1 (fr) 2016-03-21 2017-03-20 Plateforme, disque et ensemble de soufflante

Publications (2)

Publication Number Publication Date
EP3433469A1 EP3433469A1 (de) 2019-01-30
EP3433469B1 true EP3433469B1 (de) 2023-04-26

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EP17716956.2A Active EP3433469B1 (de) 2016-03-21 2017-03-20 Plattform, fananordnung und fan

Country Status (8)

Country Link
US (1) US11021973B2 (de)
EP (1) EP3433469B1 (de)
JP (1) JP7164435B2 (de)
CN (1) CN108884720B (de)
CA (1) CA3018448A1 (de)
FR (1) FR3048997B1 (de)
RU (1) RU2728547C2 (de)
WO (1) WO2017162975A1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3089548B1 (fr) * 2018-12-07 2021-03-19 Safran Aircraft Engines Soufflante comprenant une plateforme inter-aubes fixee a l’amont par une virole
FR3120813B1 (fr) 2021-03-16 2024-02-09 Safran Aircraft Engines Procédé de fabrication d’un disque de soufflante avec partie en fabrication additive

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2484988A (en) * 2010-11-01 2012-05-02 Rolls Royce Plc Annulus filler for gas turbine engine rotor disc
EP2463482A2 (de) * 2010-12-09 2012-06-13 Rolls-Royce PLC Ringförmiges Füllerelement für eine Rotorscheibe eines Gasturbinentriebwerks
EP2503102A2 (de) * 2011-03-25 2012-09-26 Rolls-Royce plc Rotor mit Plattformen zwischen den Schaufeln
US20160069355A1 (en) * 2014-09-08 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Panels of a fan of a gas turbine
FR3029563A1 (fr) * 2014-12-08 2016-06-10 Snecma Plateforme a faible rapport de moyeu
FR3033179A1 (fr) * 2015-02-26 2016-09-02 Snecma Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante

Family Cites Families (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2006883B (en) * 1977-10-27 1982-02-24 Rolls Royce Fan or compressor stage for a gas turbine engine
US4265595A (en) * 1979-01-02 1981-05-05 General Electric Company Turbomachinery blade retaining assembly
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
US5281096A (en) * 1992-09-10 1994-01-25 General Electric Company Fan assembly having lightweight platforms
FR2814495B1 (fr) * 2000-09-28 2003-01-17 Snecma Moteurs Systeme de retention amont pour aubes et plates-formes de soufflante
US6634863B1 (en) * 2000-11-27 2003-10-21 General Electric Company Circular arc multi-bore fan disk assembly
US6447250B1 (en) * 2000-11-27 2002-09-10 General Electric Company Non-integral fan platform
US6481971B1 (en) * 2000-11-27 2002-11-19 General Electric Company Blade spacer
US6520742B1 (en) * 2000-11-27 2003-02-18 General Electric Company Circular arc multi-bore fan disk
US6764282B2 (en) * 2001-11-14 2004-07-20 United Technologies Corporation Blade for turbine engine
JP4045993B2 (ja) * 2003-03-28 2008-02-13 株式会社Ｉｈｉ ファン静翼、航空エンジン用ファン、及び航空エンジン
JP4807113B2 (ja) * 2006-03-14 2011-11-02 株式会社Ｉｈｉ ファンのダブテール構造
FR2913734B1 (fr) * 2007-03-16 2009-05-01 Snecma Sa Soufflante de turbomachine
FR2930595B1 (fr) 2008-04-24 2011-10-14 Snecma Rotor de soufflante d'une turbomachine ou d'un moteur d'essai
FR2931871B1 (fr) * 2008-05-29 2011-08-19 Snecma Rotor de soufflante pour une turbomachine.
FR2949142B1 (fr) * 2009-08-11 2011-10-14 Snecma Cale amortisseuse de vibrations pour aube de soufflante
US8435006B2 (en) * 2009-09-30 2013-05-07 Rolls-Royce Corporation Fan
US8353161B2 (en) * 2010-04-19 2013-01-15 Honeywell International Inc. High diffusion turbine wheel with hub bulb
US8827651B2 (en) * 2010-11-01 2014-09-09 Rolls-Royce Plc Annulus filler
FR2974864B1 (fr) * 2011-05-04 2016-05-27 Snecma Rotor de turbomachine avec moyen de retenue axiale des aubes
FR2987086B1 (fr) * 2012-02-22 2014-03-21 Snecma Joint lineaire de plateforme inter-aubes
FR2989724B1 (fr) * 2012-04-20 2015-12-25 Snecma Etage de turbine pour une turbomachine
CN202645641U (zh) * 2012-05-10 2013-01-02 中航商用航空发动机有限责任公司 一种轮盘
US9399922B2 (en) * 2012-12-31 2016-07-26 General Electric Company Non-integral fan blade platform
US9759226B2 (en) * 2013-02-15 2017-09-12 United Technologies Corporation Low profile fan platform attachment
EP2971524A4 (de) * 2013-03-12 2016-11-02 United Technologies Corp T-förmige drehverhinderungslaschen für eine plattformleitkante
GB201314542D0 (en) * 2013-08-14 2013-09-25 Rolls Royce Plc Annulus Filler
DE102014217887A1 (de) * 2014-09-08 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Füllelemente eines Fans einer Gasturbine
US10605117B2 (en) * 2015-10-08 2020-03-31 General Electric Company Fan platform for a gas turbine engine
FR3082876B1 (fr) * 2018-06-21 2021-01-22 Safran Aircraft Engines Soufflante comprenant une plateforme et un verrou de blocage

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2484988A (en) * 2010-11-01 2012-05-02 Rolls Royce Plc Annulus filler for gas turbine engine rotor disc
EP2463482A2 (de) * 2010-12-09 2012-06-13 Rolls-Royce PLC Ringförmiges Füllerelement für eine Rotorscheibe eines Gasturbinentriebwerks
EP2503102A2 (de) * 2011-03-25 2012-09-26 Rolls-Royce plc Rotor mit Plattformen zwischen den Schaufeln
US20160069355A1 (en) * 2014-09-08 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Panels of a fan of a gas turbine
FR3029563A1 (fr) * 2014-12-08 2016-06-10 Snecma Plateforme a faible rapport de moyeu
FR3033179A1 (fr) * 2015-02-26 2016-09-02 Snecma Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante

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FR3048997B1 (fr) 2020-03-27
RU2728547C2 (ru) 2020-07-30
CN108884720A (zh) 2018-11-23
RU2018136891A (ru) 2020-04-22
US11021973B2 (en) 2021-06-01
WO2017162975A1 (fr) 2017-09-28
FR3048997A1 (fr) 2017-09-22
JP7164435B2 (ja) 2022-11-01
CA3018448A1 (fr) 2017-09-28
RU2018136891A3 (de) 2020-06-03
BR112018069179A2 (pt) 2019-01-29
EP3433469A1 (de) 2019-01-30
US20190055847A1 (en) 2019-02-21
JP2019512639A (ja) 2019-05-16
CN108884720B (zh) 2021-11-02

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