EP1517004B1 - Roue de turbine pour turbomachine et procédé de montage d'une telle roue - Google Patents

Roue de turbine pour turbomachine et procédé de montage d'une telle roue Download PDF

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Publication number
EP1517004B1
EP1517004B1 EP04104494.2A EP04104494A EP1517004B1 EP 1517004 B1 EP1517004 B1 EP 1517004B1 EP 04104494 A EP04104494 A EP 04104494A EP 1517004 B1 EP1517004 B1 EP 1517004B1
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EP
European Patent Office
Prior art keywords
upstream
downstream
turbine
wheel
engagement means
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Active
Application number
EP04104494.2A
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German (de)
English (en)
French (fr)
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EP1517004A1 (fr
Inventor
Alain Marie Joseph Lardellier
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference
    • 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
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings

Definitions

  • the present invention relates generally to a turbomachine turbine wheel, of the type comprising a turbine disk and a plurality of blade segments mounted on the turbine disk.
  • the invention also relates to a method of mounting such a turbine wheel.
  • a turbomachine turbine wheel comprises a turbine disk and a plurality of blades mounted on the turbine disk, each blade comprising a foot extending from a radially inner profile. and being provided with retaining shapes known as "fir fasteners”.
  • the latter is usually provided with a series of substantially axial grooves open radially outwardly, having a shape complementary to that of the aforementioned "fir fasteners", and in which the blades can be inserted one after the other, to be maintained by the turbine disk.
  • the blade roots must necessarily be relatively bulky, as well as the complementary shapes (or teeth) of the turbine disk, in order to allow a good maintenance of these elements. compared to others, despite the high radial forces generated during the rotation of the turbine wheel. Naturally, these large volumes translate directly into weight constraints and material cost constraints. In this respect, it is also stated that the complex realization of the "fir" shapes of the vanes and the disk generates significant manufacturing costs.
  • this type of embodiment does not provide a sufficiently satisfactory seal between the turbine disc on the one hand and the blade segments on the other hand, it is generally necessary to add an upstream labyrinth connected by a system of flanges. to the turbine disk.
  • the upstream labyrinth thus makes it possible, while playing an axial stopping role of the turbine blades in their fasteners, to protect the cooling circuit of the blades from the inadvertent crossing of the hot gases coming from the turbine duct, which could pass through the turbine wheel. turbine by borrowing the existing gap between the disk and the blades.
  • the addition of the upstream labyrinth greatly limits the passage of cooling air between the turbine disk and the blade segments, through its participation in the creation of an intermediate upstream chamber allowing the feeding the blades with cooling air.
  • the upstream labyrinth required is a bulky piece, high mass and extremely complex to achieve, so that its presence is certainly a disadvantage largely detrimental, especially in terms of additional costs generated.
  • the object of the invention is therefore to propose a turbomachine turbine wheel comprising a turbine disc as well as a plurality of blade segments mounted on this turbine disk, and at least partially overcoming the aforementioned drawbacks relating to turbines. achievements of the prior art.
  • the invention also aims to present a method of mounting such a turbine wheel.
  • the invention firstly relates to a turbomachine turbine wheel comprising a turbine disk and a plurality of blade segments mounted on the turbine disk, each blade segment comprising a foot as well as at least one dawn attached to the foot.
  • the turbine disk comprises an upstream wing and a downstream wing each extending substantially annularly about a longitudinal main axis of the wheel and radially to a radial end of the disk, each blade segment mounted on the disk turbine being able to be retained by the latter in a radial outer direction by means of upstream engagement means belonging to the foot and able to cooperate with complementary upstream engagement means constituting a radial end external of the upstream wing, and with the aid of downstream engagement means also belonging to the foot and adapted to cooperate with complementary downstream engagement means constituting an outer radial end of the downstream wing.
  • the upstream and downstream wings of the turbine disk are designed to be able to be brought from a position spaced commitment to a close position, and vice versa, to allow mounting of each blade segment on the turbine disk.
  • at least one of the upstream and downstream wings is elastically designed so that the passage of these wings from the spaced apart position to the close position and the transition from the close position to the spaced apart position can respectively be operated by exerting pressure on the wings, and releasing the pressure exerted.
  • the specific design of the turbine wheel according to the invention is such that the assembly of the blade segments on the turbine disk is carried out by performing in particular a simple approximation of the upstream and downstream wings allowing a set up of these segments.
  • the turbine disk is advantageously designed so that when the upstream and downstream wings occupy their close position, the complementary upstream and downstream engagement means are sufficiently clear of the location they occupy when the upstream and downstream wings are in the open position of engagement, to allow a placement of the segments, by insertion into each other of each blade segment and the turbine disk.
  • the complementary upstream and downstream engagement means are sufficiently close together so that when the blade segments are inserted into the turbine disk by a radial displacement thereof inwardly of the wheel, they do not form a stop for the upstream and downstream engagement means belonging to the legs of the segments. Consequently, the blade segments can each be moved freely radially relative to the turbine disk, without being impeded by the complementary upstream and downstream engagement means, which are respectively further downstream than the upstream engagement means of the segments. of blades, and more upstream than the downstream engagement means of these same segments.
  • the upstream and downstream wings can again be brought into their spaced engagement position, in which the upstream and downstream engagement means Further downstream are then able to fulfill their primary function, namely, in combination with the upstream and downstream engagement means, to ensure the radial outward restraint of each blade segment with respect to the turbine disk.
  • the turbine wheel according to the invention is such that the mounting of the blade segments on the turbine disk can be completed as soon as the upstream and downstream wings are brought in their outset commitment position after being reconciled, or further subsequent operations as will be discussed in detail below.
  • the configuration of the various engagement means may be such that the simple movement of the upstream and downstream wings in the position spread of commitment, causes the automatic commitment of these engagement means.
  • the upstream and downstream engagement means of the blade segments cooperate respectively with the complementary upstream and downstream engagement means of the rotor disk. turbine, and the blade segments are automatically blocked in the outer radial direction relative to the disk.
  • this configuration can in particular be obtained by providing engagement means ensuring not only a blocking of the blade segments in the outer radial direction, but also a locking of these segments in the internal radial direction relative to the disk of turbine. This makes it possible to prevent the upstream and downstream engagement means of some of these blade segments from being disengaged by gravity from the complementary upstream and downstream engagement means. Under these conditions, once mounted, the blade segments therefore have no freedom of radial displacement relative to the turbine disk.
  • each of the upstream and downstream wings of the turbine disk is elastic.
  • the turbine wheel so that the spread position of engagement of these wings corresponds to a rest position, it is then easily possible to bring these wings from the position of engagement away to the close position by applying a simple effort on the latter, so as to generate a deformation of these same wings.
  • the return to the spread position of commitment is then automatically released releasing the force exerted, because of the elasticity of these wings.
  • the complementary upstream and downstream engagement means extend annularly around the longitudinal main axis of the wheel, and the upstream and downstream engagement means of each blade segment foot are each made of to form an annular portion of the same axis, extending circumferentially all along the foot of the blade segment. Therefore, because of the long circumferential length of cooperation between the various engagement means, it is possible to obtain a mechanical maintenance of the blade segments very efficient and easily resistant to the radial forces generated during the rotation of the wheel of turbine. Furthermore, this arrangement also makes it possible to ensure a very satisfactory seal between, on the one hand, the blade segments, and on the other hand the turbine disk.
  • the complementary upstream and downstream engagement means as well as the upstream and downstream engagement means of the foot of each blade segment each have a hook-shaped longitudinal section, this shape being entirely adapted to ensure a blockage in the outer radial direction.
  • the complementary upstream engagement means have a longitudinal hook-shaped section projecting upstream and defining an engagement opening substantially oriented radially towards the inside of the wheel, that the upstream engagement means have a hook-shaped longitudinal section projecting downstream and defining a substantially radially outwardly oriented engagement opening of the wheel, that the complementary downstream engagement means have a longitudinal section; hook-shaped projecting downstream and defining an opening engagement member substantially oriented radially towards the inside of the wheel, and finally that the downstream engagement means have a hook-shaped longitudinal section projecting upstream and defining a substantially radially oriented engagement opening towards the outside the wheel.
  • each blade segment further comprises holding means for ensuring, when cooperating with the turbine disk, a permanent cooperation between the upstream and downstream engagement means of the assembled blade segment. on the turbine disk, and respectively complementary upstream and downstream engagement means of the same turbine disk.
  • the permanent cooperation between the various engagement means advantageously makes it possible to maintain the segments of blades fixed with respect to the turbine disk, and thus to obtain a precise radial and circumferential indexing of each of these blade segments. relative to the turbine disk.
  • the holding means comprise at least one flexible blade belonging to the foot and a free end of which is able to bear on the turbine disk, each of these flexible blades being then accosted on the disk only after that the upstream and downstream wings have been brought back to their spaced engagement position, and the corresponding blade segment having been radially biased outwardly to bear on the complementary engagement means of the disk.
  • the upstream and downstream wings of the turbine disk define between them an annular space arranged around the longitudinal main axis of the wheel, this annular space communicating with cooling passages provided on the blade segments of the feet.
  • the upstream wing of the turbine disk has at least one injection hole passing through it and opening inside the annular space, each injection hole being intended to cooperate with a cooling air injector. of the turbomachine.
  • the turbine disk is monobloc.
  • FIG. 1 With reference jointly to figures 1 and 2 , there is shown a turbine wheel 1 for turbomachine, according to a first preferred embodiment of the present invention.
  • the turbine wheel 1, of longitudinal main axis 2 comprises a turbine disk 4, preferably one-piece, as well as a plurality of blade segments 6 mounted on the disk 4, only one of these segments 6 being represented on the figure 2 .
  • Each blade segment 6 comprises a foot 8 extended radially outwards by a blade 10, or preferably by several blades 10.
  • each segment 6 is provided with three blades 10 integral with a part external radial 11 of the foot 8, this portion 11 of the metal plate type optionally variable thickness can for example take substantially the shape of an angular sector of a cylindrical geometry axis identical to the longitudinal main axis 2.
  • the turbine wheel 1 may be designed to have about twenty segments 6 of three blades 10, these segments 6 being evenly distributed around the longitudinal main axis 2 and mounted on the turbine disk 4.
  • each space (not shown) between two segments directly consecutive 6 is sealed in a conventional manner, using means known to those skilled in the art.
  • the turbine disc 4 comprises an internal body 12, preferably of the solid body type, or more conventionally pierced with a central hole if necessary to pass a low pressure turbine shaft for example, this inner body 12 being centered on the axis main longitudinal 2.
  • the inner body 12 is extended radially outwards on the one hand by an upstream wing 14a, and on the other by a downstream wing 14b.
  • the upstream and downstream flanges 14a and 14b each extend substantially annularly around the longitudinal main axis 2 of the wheel 1, and each extend radially to a radial end of the disc 4.
  • upstream and downstream are defined with respect to a main direction of gas flow through the turbine wheel 1, this direction being shown schematically by the arrow Dp on the figure 1 .
  • the upstream and downstream wings 14a and 14b are both resilient, so that they can be easily moved from a position of engagement away as shown in FIGS. figures 1 and 2 at a close position, and vice versa.
  • This specificity allows to allow the assembly of the blade segments 6 on the disc 4 monobloc, as will be explained in more detail later.
  • the blade segments 6 are not only retained in an external radial direction indicated schematically by the arrow Re, but also retained in an internal radial direction indicated schematically by the arrow Ri.
  • the specificity of this first mode of The preferred embodiment of the present invention resides in the fact that the blade segments 6 have no freedom of radial displacement with respect to the turbine disk 4.
  • each segment 6 comprises upstream engagement means 16a and 16b downstream engagement means, ci extending radially inwardly from the portion 11 of the foot 8, to which they are secured.
  • These upstream engagement means 16a and downstream 16b respectively cooperate with complementary upstream engagement means 18a constituting a radial outer end of the upstream wing 14a, and with complementary downstream engagement means 18b constituting an outer radial end of the downstream wing 14b.
  • the various engagement means 16a, 16b, 18a and 18b effectively provide retention, in the outer radial direction Re, of each segment 6 with respect to the disc 4.
  • the blade segments 6 are in radial outer abutment against the turbine disc 4, and these segments 6 do not can not move in the external radial direction Re with respect to this same disk 4.
  • the complementary upstream engagement means 18a and the complementary downstream engagement means 18b, as well as the upstream and downstream engagement means 16a of the foot 8 of each blade segment 6, each have a hook-shaped longitudinal section.
  • the complementary upstream engagement means 18a have a hook-shaped longitudinal section projecting upstream.
  • the complementary upstream engaging means 18a project upstream relative to the rest of the upstream wing 14a.
  • these means 18a define an engagement opening 20a substantially oriented radially towards the inside of the wheel 1, as clearly shown on the figure 3 .
  • the free end 22a of the hook points radially towards the inside of the wheel 1.
  • the upstream engagement means 16a also have a hook-shaped longitudinal section, the latter projecting downstream.
  • these means 16a define an engagement opening 24a substantially oriented radially outwardly of the wheel 1.
  • the free end 26a of hook points radially outward of the wheel 1.
  • the complementary upstream engagement means 18a preferably extending annularly around the longitudinal main axis 2 of the wheel 1, and the upstream engagement means 16a of each blade segment 6 being each made of so as to form an annular portion of the same axis extending circumferentially along the foot 8 along a circumferential length L, it is then possible to obtain a particularly satisfactory upstream seal.
  • the centrifugal force generated during the rotation of the wheel 1 causes a significant pressure on the one hand between the free end 26a and the hook bottom 30a, and / or on the other hand between the free end 22a and hook bottom 28a.
  • the observed support is substantially circumferential axis identical to the longitudinal main axis 2, and therefore strongly contributes to obtaining an upstream tightness perfectly adapted to the needs encountered.
  • the complementary downstream engagement means 18b have a hook-shaped longitudinal section projecting downstream.
  • the complementary downstream engagement means 18b projects downstream from the rest of the downstream wing 14b.
  • these means 18b define an engagement opening 20b substantially oriented radially towards the inside of the wheel 1, as is clearly apparent on the figure 3 .
  • the free end 22b of the hook points radially towards the inside of the wheel 1.
  • downstream engagement means 16b also have a hook-shaped longitudinal section, the latter protruding upstream.
  • these means 16b define an engagement opening 24b substantially oriented radially outwardly of the wheel 1.
  • the free end 26b of the hook points radially outwardly of the wheel 1.
  • the complementary downstream engaging means 18b also preferably extending annularly around the longitudinal main axis 2 of the wheel 1, and the downstream engaging means 16b of each blade segment 6 being each made so as to form an annular portion of the same axis extending circumferentially along the foot 8 to a circumferential length identical to that of the upstream engagement means 16a, it is thus possible to obtain a particularly satisfactory downstream seal. This is always due to the centrifugal force generated during the rotation of the wheel 1, causing a significant pressure on the one hand between the free end 26b and the hook bottom 30b, and on the other hand between the free end 22b and hook bottom 28b.
  • each segments blade 6 of the turbine wheel 1 also has holding means 32a and 32b ensuring the retention of these segments 6 in the internal radial direction Ri.
  • the holding means 32a of each segment 6 take the form of an upstream flexible blade, the latter extending radially towards the inside of the wheel 1.
  • the upstream flexible blade 32a has an integral end of the upstream engagement means 16a of the segment 6, and a free end 34a having a notch 36a.
  • a nipple 38a integral with the upstream flange 14a and projecting from it upstream is inserted into the bottom of the notch 36a open radially towards the inside of the wheel 1. Therefore, the nipple 38a thus provides the function of internal radial abutment for the segment 6 concerned.
  • the holding means 32b of each segment 6 take the form of a downstream flexible blade, the latter extending radially towards the inside of the wheel 1.
  • the downstream flexible blade 32b has a integral end of the downstream engagement means 16b of the segment 6, and a free end 34b having a notch (not referenced).
  • a pin 38b integral with the downstream flange 14b and projecting from it downstream is inserted into the bottom of the notch open radially towards the inside of the wheel 1 Therefore, the pin 38b therefore ensures also the internal radial stop function for the segment 6 concerned.
  • the upstream flexible blades 32a and downstream 32b may be respectively connected to the upstream engagement means 16a and the downstream engagement means 16b, at a portion of these means 16a and 16b defining the hook funds 28a and 28b.
  • the junction between the flexible blades 32a and 32b and the engagement means 16a and 16b is effected at a portion of these means 16a and 16b located radially towards the inside of the wheel.
  • the upstream and downstream flanges 14a and 14b define, when they occupy their spaced engagement position, an annular space 40 arranged around the longitudinal main axis 2.
  • This annular space 40 radially outwardly, therefore communicates with cooling passages 42 provided on the foot 8 of the blade segments 6, and more precisely on the outer radial portion 11 of the same foot.
  • the upstream flange 14a has at least one injection hole 44 therethrough and opening into the annular space 40.
  • each injection hole 44 is intended to cooperate with an injection system.
  • injection of cooling air of the turbomachine it is therefore easily possible to cool the blades 10 without requiring an upstream labyrinth.
  • the cooling air ejected from the injectors can then successively borrow the injection holes 44, the annular space 40, then the cooling passages 42 communicating with a cooling circuit (not shown) formed inside the vanes 10.
  • a first step of this method consists in bringing the upstream 14a and downstream wings 14b from the engaged engagement position to the close position.
  • This is done using appropriate tools schematically represented by the numerals 46, and whose function is to exert pressure on the upstream wings 14a and downstream 14b of the monobloc disk 4, so that they deform and get closer to each other.
  • the two wings 14a and 14b are each subjected to a pressure distributed annularly around the main axis longitudinal 2, and respectively applied on an upstream face of the upstream wing 14a and on a downstream face of the downstream wing 14b.
  • the close position is obtained when the complementary upstream engagement means 18a and complementary downstream engagement means 18b are sufficiently clear of the location they occupy when the upstream wings 14a and downstream 14b are in the engaged position , to allow placement of the segments 6 by insertion into each other of each blade segment 6 and the turbine disk 4.
  • a next step is to set up the various segments 6 with respect to the turbine disk 4, as shown in FIG. figure 6b .
  • the positioning is preferably carried out by moving each of the segments 6 radially towards the inside of the wheel 1, so that complementary complementary upstream 18a and complementary downstream engagement means 18b are inserted inside these same segments. 6, without being impeded by the upstream engagement means 16a and downstream 16b.
  • the complementary engagement means 18a and 18b can therefore easily be introduced into a space delimited jointly by the upstream engagement means 16a, the downstream engagement means 16b, and the outer radial portion 11 of the foot 8 of the segment 6 concerned.
  • this placing step is completed only when the segments 6 have been placed sufficiently radially inwards by relative to the disc 4, so that when the upstream wings 14a and downstream 14b are again brought into their spaced engagement position, the upstream engagement means 16a and downstream 16b of the foot 8 of each segment 6 are able to s' respectively engage with complementary upstream engaging means 18a and complementary downstream 18b of the turbine disk 4, during a relative radial displacement of these various elements.
  • this placing step only ends when the complementary engagement means 18a and 18b have come into contact with the part 11 of the foot 8 of each segment 8, as shows it figure 6b .
  • the complementary engagement means 18a and 18b then fulfill an internal radial abutment function for the segments 6, indicating that the vane segments 6 are indeed correctly put in place.
  • the free ends 22a, 22b, 26a and 26b are respectively opposite and at a distance from the engagement openings 24a, 24b, 20a and 20b, and the complementary engagement means 18a and 18b are preferably always in contact with the external radial portion 11 of the feet 8.
  • the flexible blades 32a and 32b are respectively pressed against the end of the pins 38a and 38b, but that they do not yet cooperate with the notches 36a because of the radial offset existing at this time of the implementation of the method.
  • the next step of this mounting method may then be to move each of the blade segments 6 in the outer radial direction Re with respect to the disk 4, so as to ensure engagement between the various engagement means. 16a, 16b, 18a and 18b, that is to say to cause the introduction of the free ends 22a, 22b, 26a and 26b respectively into the engagement openings 24a, 24b, 20a and 20b.
  • this radial displacement is stopped by the cooperation between the various engagement means 16a, 16b, 18a and 18b, namely by the coming into contact of the free ends 22a, 22b, 26a and 26b respectively with the hook funds 28a, 28b, 30a and 30b.
  • the method of mounting the wheel 1 may comprise conventional preliminary or subsequent steps, such as those for sealing the various spaces formed between the blade segments 6, for example by introducing sealing tongues 39 such as represented on the figure 2 , at the level of the foot 8 and between two consecutive segments of blades 6. This step is of course implemented before proceeding to the final indexing of these segments 6 on the disk 4.
  • turbine wheels 100 and 200 for turbomachine respectively according to a second and a third preferred embodiments of the present invention.
  • the turbine wheel 100 according to the second preferred embodiment shown in FIG. figure 4 is substantially similar to the wheel 1 according to the first preferred embodiment described above.
  • the main difference is that the segments 6 of the wheel 100 do not have holding means to obtain permanent cooperation between the various engagement means 16a, 16b, 18a and 18b, the latter being moreover substantially identical to those described for the turbine wheel 1.
  • some segments are in internal radial abutment against the complementary engagement means 18a and 18b, due to gravity.
  • the turbine wheel 200 according to the third preferred embodiment shown in FIG. figure 5 differs from the turbine wheels 1 and 100 in that the repositioning of the upstream wings 14a and downstream 14b in their spaced engagement position simultaneously causes engagement and cooperation between the various engagement means 16a, 16b, 18a and 18b.
  • these various engagement means 16a, 16b, 18a and 18b are designed so that when they cooperate with each other, they ensure the retention of the segments 6 relative to the disk 4 in the outer radial direction Re, as well as in the internal radial direction Ri.
  • the blade segments 6 therefore do not require holding means such as those described for the turbine wheel 1.
  • the upstream engagement means 16a and downstream 16b may each comprise an annular groove 48a and 48b respectively open downstream and open upstream.
  • the complementary engagement means 18a and 18b may each be provided with an annular projection 50a and 50b respectively protruding upstream and downstream, and having a shape complementary to that of the annular grooves 48a and 48b so as to be properly maintained. With such an arrangement, the engagement means 16a, 16b, 18a and 18b therefore no longer require the shape of a hook in longitudinal section.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04104494.2A 2003-09-19 2004-09-16 Roue de turbine pour turbomachine et procédé de montage d'une telle roue Active EP1517004B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0350576A FR2860031B1 (fr) 2003-09-19 2003-09-19 Roue de turbine pour turbomachine et procede de montage d'une telle roue
FR0350576 2003-09-19

Publications (2)

Publication Number Publication Date
EP1517004A1 EP1517004A1 (fr) 2005-03-23
EP1517004B1 true EP1517004B1 (fr) 2014-12-17

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US (1) US7134843B2 (ja)
EP (1) EP1517004B1 (ja)
JP (1) JP4058030B2 (ja)
FR (1) FR2860031B1 (ja)

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FR2901305B1 (fr) * 2006-05-18 2012-11-16 Snecma Disque de turbine monobloc
FR2922587B1 (fr) * 2007-10-22 2010-02-26 Snecma Roue de turbomachine
US8388310B1 (en) * 2008-01-30 2013-03-05 Siemens Energy, Inc. Turbine disc sealing assembly
FR2927086B1 (fr) * 2008-02-01 2010-03-19 Eurovia Utilisation d'un melange exothermique pour la fabrication d'un enrobe bitumineux.
GB2472572A (en) * 2009-08-10 2011-02-16 Rolls Royce Plc Mounting for aerofoil blade using elastomeric bush
FR2961847B1 (fr) * 2010-06-25 2012-08-17 Snecma Roue mobile a aubes en materiau composite pour moteur a turbine a gaz a liaison pied d'aube/disque par serrage
US9518471B2 (en) * 2013-10-16 2016-12-13 General Electric Company Locking spacer assembly
US9341071B2 (en) * 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
KR102182102B1 (ko) * 2014-11-27 2020-11-23 한화에어로스페이스 주식회사 터빈 장치
DE102016123248A1 (de) * 2016-12-01 2018-06-07 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine
US11339673B2 (en) * 2020-01-17 2022-05-24 Raytheon Technologies Corporation Rotor assembly with internal vanes
US11371351B2 (en) 2020-01-17 2022-06-28 Raytheon Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment

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GB1036739A (en) * 1965-04-02 1966-07-20 Rolls Royce Rotor and blade assemblies
FR2491549B1 (fr) * 1980-10-08 1985-07-05 Snecma Dispositif de refroidissement d'une turbine a gaz, par prelevement d'air au niveau du compresseur
DE4132332A1 (de) * 1990-12-14 1992-06-25 Ottomar Gradl Anordnung zum befestigen von schaufeln an der scheibe eines rotors

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US20050106019A1 (en) 2005-05-19
FR2860031B1 (fr) 2007-09-07
US7134843B2 (en) 2006-11-14
EP1517004A1 (fr) 2005-03-23
FR2860031A1 (fr) 2005-03-25
JP2005098300A (ja) 2005-04-14
JP4058030B2 (ja) 2008-03-05

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