WO2013150263A1 - Disque aubagé monobloc pour turbine à flux axial - Google Patents

Disque aubagé monobloc pour turbine à flux axial Download PDF

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Publication number
WO2013150263A1
WO2013150263A1 PCT/GB2013/050441 GB2013050441W WO2013150263A1 WO 2013150263 A1 WO2013150263 A1 WO 2013150263A1 GB 2013050441 W GB2013050441 W GB 2013050441W WO 2013150263 A1 WO2013150263 A1 WO 2013150263A1
Authority
WO
WIPO (PCT)
Prior art keywords
blisc
wire
segments
shrouds
blades
Prior art date
Application number
PCT/GB2013/050441
Other languages
English (en)
Inventor
Ian Pinkney
Paul Eifion ROACH
Neil Ryan THOMAS
Ian Patrick Clare Brown
Peter Kay
Matthew Elijah MOORE
Francis Joseph Geoffrey Heyes
Jonathan Charles RIGGALL
Peter Moore
Original Assignee
Napier Turbochargers Limited
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 Napier Turbochargers Limited filed Critical Napier Turbochargers Limited
Publication of WO2013150263A1 publication Critical patent/WO2013150263A1/fr

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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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • 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 blisc for an axial flow turbine of a turbocharger.
  • Turbocharger axial flow turbines are conventionally formed by connecting separate, detachable blades to a central disc.
  • Each blade has a root portion (typically of dovetail or fir tree shape) that joins to a corresponding recessed profile formed in the outer edge of the disc.
  • the centrifugal blade loads are transferred from the root portions to disc posts which are formed between the recessed profiles. Since the amount of material contained within the posts is generally relatively small, the stresses in the posts can be high
  • Turbocharger turbine blades are also subject to high vibratory stresses originating from the pulsations of the gas pressure in the engine exhaust manifold which feeds gases to the turbine. As a result, the blades often need to be damped, for example using a damping wire which is threaded through holes in the blades before they are attached to the disc, to avoid blade loss due to fatigue.
  • other means of damping individual blades are also feasible, such as using blade dampers in or around the root forms of individual blades.
  • a blisc an integral disc and blades
  • a blisc has an advantage that, in operation, the centrifugal loads caused by the blades are taken up by the disc in a continuous manner, resulting in relatively low stresses in the disc portion.
  • a blisc may be less susceptible to blade fatigue than a conventional turbine with detachable blades, allowing higher rotational speeds and therefore higher turbine pressure ratios.
  • a damping wire can be difficult to fit to a blisc. For example, it may be necessary to fit the wire by hand, which increases the cost of the blisc.
  • the present invention is at least partly based on a recognition that, although the added mass of the shrouds increases the centrifugal loading of the blisc, this increased loading can be tolerated in a blisc when, in the corresponding situation, it would not be acceptable in a conventional disc with detachable blades.
  • the present invention provides a blisc for an axial flow turbine of a turbocharger, the blisc having integral blade shrouds at the radially outer ends of the blades of the blisc.
  • the shrouds can increase the aerodynamic efficiency of the turbine, while not unacceptably increasing the susceptibility of the blisc to blade fatigue.
  • the present invention provides a turbocharger having an axial flow turbine including the blisc of the first aspect.
  • the present invention provides a cartridge for parts of a turbocharger, the cartridge being a separately removable and replaceable module of the turbocharger; wherein ' the cartridge includes: an axial flow turbine rotor which is a blisc of the first aspect, a compressor wheel, a shaft and bearings assembly for the rotor and the compressor wheel, a hub casing for a diffuser of the turbine, and a main casing of the turbocharger.
  • the cartridge may further include a volute of the compressor, a diffuser of the compressor, and an insert casing of the compressor.
  • the shrouds may be provided by a circumferentially continuous shroud ring.
  • the shrouds are provided by a plurality of shroud ring segments, each segment providing the shroud(s) for a single blade or for two or more neighbouring blades, and being separated by respective gaps from its neighbouring segments.
  • the gaps allow the shroud ring to expand during thermal transients and thus help to avoids cracking of the blisc.
  • the blisc can be a forged or a cast component. Generally, forged components can take higher stresses than cast components. Preferably, however, particularly when the blisc has integral blade shrouds, the blisc is a cast component, as the complex shape of the shrouds can be difficult to produce by forging. Typically, the blisc is a metal (e.g. nickel-based super alloy) component.
  • the blisc may have a circumferentially continuous shroud ring, the gaps being formed by a post-casting cutting operation, such as electro discharge machining (EDM) or chemical erosion.
  • EDM electro discharge machining
  • a tool electrode can be provided having the shape of the gaps between the shroud segments, the tool being plunged radially inwards to cut one gap and then indexed around to cut a next gap.
  • the shroud segments may move to relieve residual stresses, leading to uneven gap widths.
  • the flow passages between the blades may be filled, e.g. with a metal of relatively low melting point, prior to cutting.
  • This filler prevents undesirable movement of the component during cutting, facilitating the production of regular sized gaps.
  • the filler can be melted out from the component when all the gaps are cut. Post-casting cutting allows the gaps to be kept to a small size, which tends to improve aerodynamic performance, and allows the shape of the free ends of the shroud segments at the gaps to be controlled, which can improve
  • the present invention provides a method of producing such a blisc, the method including the steps of: casting the blisc such that in the as-cast form it has a circumferentially continuous shroud ring; and forming the gaps between the shroud segements by a post-casting cutting operation.
  • the method may include steps of: filling the flow passages between the blades with a filler of relatively low melting point prior to the forming step, and removing the filler after the forming step.
  • the shrouds typically have trailing edges which are at or rearward of the trailing edges of the blades at the radially outer ends thereof.
  • the shrouds may have leading edges which are at or forward of the leading edges of the blades at the radially outer ends thereof.
  • the shrouds may have leading edges which are rearward of the leading edges of the blades at the radially outer ends thereof. The position of the leading edges of the shrouds has less of an effect on aerodynamic losses, and by reducing the overall axial length of the shrouds, the centrifugal loading of the blisc can be lowered.
  • the radially outer side of the shrouds may form plural (e.g. two, three or four) axially spaced, annular fins which, in use, form a labyrinth seal with a casing surrounding the turbine.
  • a seal can reduce leakage flow over the radially outer ends of the blades.
  • the casing may have an abradable surface against which the fins rub to ensure that the casing/fin clearance is small, reducing leakage through the seal.
  • the radially outer side of the shrouds may form an annular hook formation which, in use, receives a damping wire.
  • the root forms of conventional, detachable blades allows a small amount of movement between the blades and disc in operation, so that vibrations of the turbine assembly can, to extent, be damped by friction between the blades and the disc.
  • the hook formation allows a damping wire to be fitted to the blisc, reducing the risk of fatigue-induced blade loss and allowing the turbine to be used in high pulsation applications.
  • the position of the hook formation avoids locating the damping wire in the working gas annulus of the turbine and thereby avoids the aerodynamic performance deficit associate with flow past the wire.
  • the shrouds are provided by a plurality of shroud ring segments, the wire allows the number and the widths of the gaps between the segments to be reduced.
  • the hook formation allows the wire to be fitted to a blisc in which the blades cannot be separated from the disc for threading of the wire through respective holes in the blades.
  • the hook formation may provide a receiving cavity for the damping wire, and a narrowed entrance to the cavity, the width of the narrowed entrance being less than the diameter of the damping wire such that forcing the wire through the entrance produces an elastic deformation of the hook formation and the wire which allows the wire to enter the cavity. When the wire reaches the cavity the elastic deformation can then reverse, trapping the wire in the cavity.
  • the ratio of the wire diameter to the entrance width may be in the range 1.003 to 1.085, such a range can help to avoid plastic deformation of the wire or hook formation during assembly.
  • the damping wire may be a single wire which extends around the circumference of the shroud ring, the length of the wire being selected such a gap is formed between the ends of the wire.
  • the gap can accommodate relative thermal expansion of the wire so that the ends of the wire do not touch in operation.
  • the damping wire may be divided into circumferentially arranged wire segments, with gaps being provided between the ends of each wire segment and the ends of its neighbouring wire segments. This arrangement can help to avoid buckling of the wire during thermal transients.
  • the hook formation is formed at the base of one of the fins. In this way, additional mass associated with providing the hook formation can be reduced.
  • the blisc may have a damping wire received in the hook formation.
  • Figure 1 shows schematically a longitudinal cross-section through an axial flow turbine of a turbocharger
  • Figure 2 shows schematically a smaller scale longitudinal cross-section through parts of the turbocharger of Figure 1 ;
  • Figure 3 shows schematically a front view of a blisc of the turbine of Figures 1 and 2;
  • Figure 4 shows schematicaily a side view of the radial end of a blade of the blisc of Figures 1 to 3;
  • Figure 5 shows schematically the blisc front view of Figure 3 and the positions of three wire segments; and Figure 6 shows schematically a longitudinal cross-section through the radial end of a blade of a variant of the blisc.
  • an axial flow turbine of a turbocharger incorporating the invention is generally indicated at 10 and has a principal and rotational axis X X.
  • the turbine comprises, in axial flow series, an exhaust gas intake 11 , a cascade of guide vanes 12, a blisc 13 having a central disc 14 and a cascade of blades 15, and an exhaust discharge diffuser 16.
  • a casing 17 generally surrounds the blisc 13 and also defines the outer wall of the diffuser 16.
  • the blisc is typically a nickel-based super alloy component.
  • engine exhaust gas enters the intake 11 , is swirled by the guide vanes 12, drives rotation of the blisc 13 and then exits via the diffuser 16.
  • the blisc is connected via a shaft (not shown) to an air impeller (not shown) at the other side of the turbocharger. The impeller is used to compress air entering the engine.
  • the turbocharger may have a cartridge which provides parts of the turbocharger.
  • the cartridge is a separately removable and replaceable module of the turbocharger.
  • Shown in Figure 2, which is a smaller scale cross-section through parts of the turbocharger of Figure 1 are a compressor wheel 30, a shaft and bearings assembly 31 for the blisc 13 and the compressor wheel, a hub casing 32 defining the radially inner wall of the diffuser 16, and a main casing 33 of the turbocharger. As indicated in Figure 2, all these parts are included in the cartridge. Conversely, other parts shown in Figure 2, such as the casing 17, the exhaust gas intake casing 34, and an exhaust gas volute 35 are not included in the cartridge and typically remain mounted to the engine.
  • the cartridge may further include other parts of the turbocharger, such as a volute of the compressor, a diffuser of the compressor, and an insert casing of the compressor.
  • FIG. 3 shows schematically a front view of the blisc 13.
  • the shrouds 18 are provided by six shroud ring segments 19, each segment forming, in this example, six neighbouring shrouds 18.
  • Each shroud ring segment 19 is separated by gaps 20 from its neighbouring segments.
  • the gaps 20 allow the shroud ring to expand during thermal transients, and thereby help to prevent stress-induced cracking of the blisc.
  • the blisc 13 is formed in an initial casting operation with a circumferentially continuous shroud ring providing the shrouds 18. In a subsequent machining operation, the gaps 20 are introduced into the continuous ring to produce the ring segments 19.
  • the cutting operation may be electro discharge machining (EDM), although other operations such as chemical erosion are feasible.
  • EDM electro discharge machining
  • a tool electrode may be formed in the shape of the gaps between the shroud segments. This electrode is plunged radially inwards to cut a gap and then indexed around to cut a next gap.
  • rod-like electrodes which plunge axially. Because there are generally residual stresses in the as-cast component, cutting the shroud ring can cause the component to distort before all the shroud segments have been cut.
  • the shroud segments can move to relieve residual stresses such that neighbouring segments grip the electrode.
  • the result can be overly wide gaps as the electrode erodes the segment parts gripping it.
  • the flow passages between the blades can be filled with a filler, such as a metal of low (say about 275°C) melting point.
  • the filler prevents movements of the component during EDM, facilitating the cutting of regular sized gaps, and can be melted out from the component when all the gaps are cut.
  • the filler is generally metal to allow the EDM process to work more effectively.
  • the filler metal can be an alloy of bismuth, lead, tin, cadmium and indium, e.g.
  • the cutting operation can use multiple tools (e g. several EDM tool electrodes), cutting plural gaps at the same time so that all, or at least a large fraction, of the cuts are made simultaneously. This might avoid a need for a filler. Fine detailed features in the outer surfaces of the shroud, such as the hook formation and the fins discussed below, can be turned or ground in a conventional manner. During these processes the filler (if used) may be left in place.
  • Figure 4 shows schematically a side view of the radial end of one of the blades 15 and better shows features of the shroud 18 of the blade 15.
  • the leading edge 21 of the shroud 18 is forward of the leading edge 22 of the blade at the blade end, although in other examples the leading edge of the blade may be forward of the leading edge of the shroud.
  • the trailing edge 23 of the shroud is rearward of the trailing edge 24 of blade.
  • Axially spaced annular fins 25 are formed at the radially outer sides of the shrouds 18.
  • the casing 17 may have an abradable stationary seal (not shown) which surrounds the blisc 13.
  • centrifugal forces cause the fins 25 to move radially outwards relative to the casing 17, allowing the fins 25 to cut respective annular recesses in the seal. In this way, gas leakage over the outer sides of the shrouds 18 can be reduced.
  • the shrouds 18 have an annular hook formation 26.
  • a damping wire 27 is pressed into the hook formation to join the packets of blades of the shroud ring segments 19. Without the damping wire 27, the individual and packets of blades 14 can be susceptible to vibration and thereby fatigue damage. However, the damping wire 27 damps these vibrations, allowing the blisc to be operated in high pulsation applications. Also, the wire 27 allows the number and the widths of the gaps 20 to be reduced, which in turn reduces aerodynamic efficiency losses associated with the gaps.
  • the width of the gaps 20 between the shroud segments 19 is determined by the amount by which each shroud segment moves relative to its neighbour and by the need to prevent the segments 19 from touching. If the segments 19 did touch, they would tend to fret and wear, increasing the gap width. The relative movement is caused by twisting of the blades 15 (and shroud segments 19) under centrifugal loading and blade vibration. The damping wire 27 tends to resist the twisting and damps the vibrations. Thus the wire 27 allows the gap width to be reduced.
  • the number of gaps 20 is important to aerodynamic performance since losses increase in proportion to gap number multiplied by gap width.
  • a packet of blades 15 linked by a shroud segment 19 tends to be more rigid than a single blade and thus resists twisting under centrifugal loads to a greater degree than a single blade. This allows a reduction of gap width.
  • a packet of blades 15 is also a more complex structure than a single blade and the modes of vibration are more complex.
  • a blade packet tends to have higher vibratory stresses than a single blade. Without the damping wire 27, such vibratory stresses can crack portions of the blade packet (either in a blade or in a shroud).
  • the hook formation 26 is outside the gas annulus of the turbine, and thereby avoids contributing to aerodynamic losses.
  • the damping wire 27 may be produced as a single length which extends around almost the entire circumference of the shroud ring. Generally, the length is selected so that there is a gap between the ends of the wire, the gap accommodating relative thermal expansion of the wire so that the ends of the wire do not touch in operation.
  • the single wire may be cut into multiple wire segments, with gaps being provided between the ends of each wire segment and the ends of the neighbouring wire segments. The sum total of all the gaps can then be greater than the increase in total wire length produced by thermal expansion of the wire segments in operation.
  • each gap between wire segments is preferably smaller than the circumferential length of an individual blade.
  • Figure 5 shows schematically the blisc front view of Figure 3 and the positions of three wire segments 30 relative to the six shroud segments 19. The length of each of the three gaps 31 between the wire segments is less than the circumferential blade length.
  • Figure 6 shows schematically a longitudinal cross-section through the radial end of a blade of a variant of the blisc, again showing features of the shroud 18 of the blade 15.
  • the leading edge 21 of the shroud 18 is forward of the leading edge 22 of the blade at the blade end, and the trailing edge 23 of the shroud is rearward of the trailing edge 24 of the blade ( Figure 5 actually showing the trailing edge 24 of an adjacent blade).
  • the hook formation 26 is adapted to reduce or eliminate a possibility that the damping wire may exit the hook during operation, e.g. due to vibration or twisting of the blades 15 in operation, or due to thermal growth of the wire during transient operation causing the wire to buckle.
  • the hook formation provides a receiving cavity 28 for the wire, and a narrowed entrance 29 to the cavity.
  • the width of the entrance can be smaller than the wire diameter such that forcing the wire through the entrance on assembly produces an elastic deformation of the hook formation and the wire which allows the wire to enter the cavity. When the wire reaches the cavity the elastic deformation reverses, trapping the wire in the cavity.
  • the ratio of the wire diameter to the entrance width may be in the range 1.003 to 1.085. Such a range allows for typical tolerances on wire diameter and machining of the hook formation 26, while helping to ensure the wire stays in place during operation and that there is no plastic deformation of wire or hook formation during assembly.
  • Another approach is simply to mechanically crimp the hook formation 26 around the wire after the wire has been fitted. This allows the machining tolerance of the hook formation to be relaxed as its entrance width in the as-machined state can simply be greater than the wire diameter.
  • the crimping produces a permanent mechanical deformation of the hook formation which can make it difficult to replace the wire if necessary.
  • the crimping may only need to be performed at spaced circumferential locations, rather than around the entire circumference of the shroud ring. For example, the crimping may be performed as a minimum at six to eight locations, or as a maximum up to the number of blades 15.
  • the shrouds 18 increase the aerodynamic efficiency of the turbine 10 by controlling the gas flow at the ends of the blades 15 to reduce tip losses. Although the shrouds 18 also increase the centrifugal loading of the blisc 13, the integral nature of the blades 15 and central disc 14 can safely accommodate that loading. By breaking up the shroud ring into shroud segments 19, the shroud ring can expand during thermal transients. Further, the hook formation 26 and damping wire 27 reduce vibration-induced fatigue while avoiding efficiency losses associated with flow over the wire.

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

Abstract

L'invention concerne un disque aubagé monobloc pour une turbine à flux axial d'un turbocompresseur, ledit disque aubagé monobloc ayant des talons d'aubes formés d'une seule pièce au niveau de leurs extrémités extérieures, dans le sens radial des aubes du disque aubagé monobloc. Les talons sont réalisé sous forme d'une pluralité de segments d'une couronne périphérique, chaque segment formant le ou les talons d'une seule aube ou de deux ou plusieurs aubes voisines, et étant séparé par des espaces respectifs des segments voisins. Le disque aubagé monobloc est une pièce coulée, et comporte à l'état brut de coulée une couronne périphérique de circonférence continue, les espaces étant formés par une opération de découpe après la coulée.
PCT/GB2013/050441 2012-04-05 2013-02-22 Disque aubagé monobloc pour turbine à flux axial WO2013150263A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB1206269.1A GB201206269D0 (en) 2012-04-05 2012-04-05 Axial Flow Turbine Blisc
GB1206269.1 2012-04-05

Publications (1)

Publication Number Publication Date
WO2013150263A1 true WO2013150263A1 (fr) 2013-10-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2013/050441 WO2013150263A1 (fr) 2012-04-05 2013-02-22 Disque aubagé monobloc pour turbine à flux axial

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GB (1) GB201206269D0 (fr)
WO (1) WO2013150263A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150098802A1 (en) * 2013-10-08 2015-04-09 General Electric Company Shrouded turbine blisk and method of manufacturing same
US20150354361A1 (en) * 2014-06-09 2015-12-10 General Electric Company Rotor assembly and method of manufacturing thereof
WO2015191330A1 (fr) * 2014-06-09 2015-12-17 General Electric Company Disque aubagé monobloc et son procédé de fabrication
WO2018069552A1 (fr) * 2016-10-14 2018-04-19 Abb Schweiz Ag Ensemble turbomachine coulé intégralement et procédé de fabrication d'un ensemble turbomachine
FR3071540A1 (fr) * 2017-09-26 2019-03-29 Safran Aircraft Engines Joint d'etancheite a labyrinthe pour une turbomachine d'aeronef

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
US6371727B1 (en) * 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper
US20020122725A1 (en) * 2001-03-05 2002-09-05 Daam Thomas J. Van Article having dampening member installed into an imbedded cavity
DE102009052305A1 (de) * 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Blisk, Gasturbine und Verfahren zur Herstellung einer derartigen Blisk

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
US6371727B1 (en) * 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper
US20020122725A1 (en) * 2001-03-05 2002-09-05 Daam Thomas J. Van Article having dampening member installed into an imbedded cavity
DE102009052305A1 (de) * 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Blisk, Gasturbine und Verfahren zur Herstellung einer derartigen Blisk

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150098802A1 (en) * 2013-10-08 2015-04-09 General Electric Company Shrouded turbine blisk and method of manufacturing same
US20150354361A1 (en) * 2014-06-09 2015-12-10 General Electric Company Rotor assembly and method of manufacturing thereof
EP2955329A1 (fr) * 2014-06-09 2015-12-16 General Electric Company Ensemble de rotor formé en une seule pièce avec arbre et blisks
WO2015191330A1 (fr) * 2014-06-09 2015-12-17 General Electric Company Disque aubagé monobloc et son procédé de fabrication
WO2018069552A1 (fr) * 2016-10-14 2018-04-19 Abb Schweiz Ag Ensemble turbomachine coulé intégralement et procédé de fabrication d'un ensemble turbomachine
FR3071540A1 (fr) * 2017-09-26 2019-03-29 Safran Aircraft Engines Joint d'etancheite a labyrinthe pour une turbomachine d'aeronef

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