EP1517004A1 - Schaufelrad für eine Turbomaschine und Methode zur Montage der Schaufeln auf der Narbe - Google Patents

Schaufelrad für eine Turbomaschine und Methode zur Montage der Schaufeln auf der Narbe Download PDF

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Publication number
EP1517004A1
EP1517004A1 EP04104494A EP04104494A EP1517004A1 EP 1517004 A1 EP1517004 A1 EP 1517004A1 EP 04104494 A EP04104494 A EP 04104494A EP 04104494 A EP04104494 A EP 04104494A EP 1517004 A1 EP1517004 A1 EP 1517004A1
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EP
European Patent Office
Prior art keywords
upstream
downstream
turbine
wheel
wings
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP04104494A
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English (en)
French (fr)
Other versions
EP1517004B1 (de
Inventor
Alain Marie Joseph Lardellier
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
Original Assignee
SNECMA Moteurs SA
SNECMA SAS
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Publication date
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Publication of EP1517004A1 publication Critical patent/EP1517004A1/de
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Publication of EP1517004B1 publication Critical patent/EP1517004B1/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
    • 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 in a turbomachine turbine wheel, type comprising a turbine disk and a plurality of blade segments mounted on this disk of turbine.
  • the invention relates also to a method of mounting such a wheel of turbine.
  • a turbomachine turbine wheel has a turbine disk and a plurality of vanes mounted on the turbine disc, each dawn having a foot extending from a profile radially inside, and being provided with holdings known as fasteners fir tree ".
  • the latter is usually provided of a series of essentially open axial grooves radially outward, having a shape complementary to that of the "fir fasteners" above mentioned, and in which the blades may be inserted one after the other, in order to be maintained by this turbine disk.
  • the feet of the blades must necessarily be relatively large, just as the shapes (or teeth) of the turbine disk, in the purpose of allowing these elements to be properly maintained against each other, despite the radial efforts generated during the rotation of the wheel of turbine.
  • these important volumes are translate directly into weight constraints and material cost constraints.
  • the complex realization of forms "fir tree" blades and disk generates significant manufacturing costs.
  • the upstream labyrinth required is a cumbersome, high mass and extremely complex to realize, so that its presence constitutes undoubtedly a very detrimental disadvantage, especially in terms of extra costs.
  • the object of the invention is therefore to propose a Turbomachine turbine wheel having a disk turbine and a plurality of blade segments mounted on this turbine disk, and remedying at least partially to the disadvantages mentioned above relating to the achievements of the prior art.
  • the invention also purpose of presenting a method of mounting such a wheel of turbine.
  • the invention firstly for object a turbomachine turbine wheel having a turbine disk and a plurality vane segments mounted on this turbine disk, each blade segment comprising a foot as well as less a dawn attached to the foot.
  • the turbine disk has an upstream wing and a downstream wing each extending substantially annularly around a longitudinal main axis of the wheel and radially to a radial end of the disc, each vane segment mounted on the turbine disc being likely to be retained by the latter in a external radial direction using means upstream commitment belonging to the foot and able to cooperate with means of upstream commitment complementary constituting a radial end the outer wing of the upstream wing, as well as by means of downstream commitment also belonging to the foot and able to cooperate with means of downstream engagement complementary constituting a radial end external of the downstream wing.
  • the upstream wings and downstream of the turbine disk are designed to can be brought from a position away 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 designed so elastic so that the passage of these wings of the position spread to the close position and the passage from the close position to the discarded position can be respectively operated by exercising a pressure on the wings, and releasing the pressure exercised.
  • the design specific to the turbine wheel according to the invention is such as mounting the blade segments on the disk of turbine is carried out by realizing in particular a simple bringing the upstream and downstream wings together setting up these segments.
  • the record turbine is advantageously designed so that when the upstream and downstream wings occupy their position close, the means of commitment upstream and downstream additional resources are sufficiently clear of the location they occupy when the upstream wings and downstream are in the open commitment position, to enable segments to be put in place by insertion into each other of each blade segment and the turbine disk.
  • vane segments can each be moved freely radially with respect to the turbine disk, without being hampered by upstream and downstream commitment complementary, which are respectively further downstream that the means of upstream engagement of the blade segments, and more upstream than the downstream commitment these same segments.
  • the upstream and downstream wings can again be brought in their outset commitment position, in which complementary upstream and downstream commitment resources are then able to fulfill their primary function, namely, in combination with the means of engagement upstream and downstream, to ensure radial restraint towards the outside of each blade segment with respect to turbine disk.
  • the wheel of turbine according to the invention is such that the assembly of vane segments on the turbine disk can be completed as soon as the upstream and downstream wings are brought in their discarded commitment position after being close-quarters, or understand operations subsequent additions as will be stated from detailed way below.
  • the configuration of the various means of engagement can be such that the mere displacement of the upstream wings and downstream in the disconnected position of engagement, causes the automatic commitment of these means of engagement.
  • the means of upstream and downstream engagement of blade segments cooperate respectively with the means of engagement upstream and downstream of the turbine disk, and the blade segments are automatically blocked in the outer radial direction with respect to disk.
  • this configuration can in particular be obtained by providing commitment ensuring not only a blockage of blade segments in the outer radial direction, but also a blockage of these segments in the internal radial direction with respect to the disc of turbine. This avoids the means upstream and downstream commitment of some of these segments of blades does not disengage by gravity means complementary upstream and downstream commitment. In these conditions, once mounted, the blade segments therefore no freedom of radial displacement compared to the turbine disk.
  • each of the upstream wings and downstream of the turbine disk is elastic.
  • the turbine wheel so that the spaced engagement position of these wings corresponds at a rest position, it is then easily possible to bring these wings from the discarded position commitment 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 discarded position commitment then automatically takes place releasing the effort exerted, because of the elasticity of these wings.
  • the engagement means complementary upstream and downstream annular around the longitudinal main axis of the wheel, and the means of commitment upstream and downstream of each foot of the blade segment 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 means of engagement it is possible to obtain a mechanical maintenance of the blade segments very powerful and easily resistant to efforts radials generated during the rotation of the wheel of turbine. Moreover, this arrangement also allows to ensure a very satisfactory seal between a apart from the blade segments, and on the other hand the disk of turbine.
  • the engagement means upstream and downstream complementary as well as the means upstream and downstream commitment of the foot of each segment of blades each have a longitudinal section in hook shape, this shape being quite adapted to ensure a locking in the radial direction external.
  • complementary means of upstream commitment have a longitudinal section in the form of hook projecting upstream and defining a substantially oriented engagement opening radially towards the inside of the wheel
  • the means upstream commitment have a longitudinal section hook-shaped projecting downstream and defining an engagement opening substantially radially outwardly of the wheel
  • the complementary downstream engagement means a longitudinal section in the form of a hook projecting downstream and defining an opening substantially radially oriented inside the wheel
  • means downstream commitment have a longitudinal section hook-shaped protruding upstream and defining an engagement opening substantially oriented radially outwardly of the wheel.
  • this preferred solution makes it possible to obtain a commitment then cooperation between the various means of engagement by simple radial relative movement between each of the vane segments and the turbine disk.
  • the relative radial movement is preferably performed in moving this segment in the outer radial direction, while holding the fixed disk.
  • each blade segment further comprises means for maintenance to ensure, when cooperating with the turbine disk, permanent cooperation between the upstream and downstream commitment means of the segment blade mounted on the turbine disk, and respectively upstream and downstream commitment means complementary to this same turbine disk.
  • the permanent cooperation between the various means of engagement advantageously allows to maintain the vanes segments fixed with respect to the disk of turbine, and thus to obtain a radial indexing and circumferential accuracy of each of these segments of blades with respect to the turbine disk.
  • holding means comprise at least one blade flexible belonging to the foot and one end free is able to take support on the record of turbine, each of these flexible blades being then accosted to the disc only after the wings upstream and downstream were brought back into their position spread of commitment, and the paddle segment correspondent having been radially solicited towards the outside to take support on the means of engagement complementary of the disc.
  • the upstream and downstream wings of the turbine disc define between them a space annular arranged around the longitudinal main axis of the wheel, this annular space communicating with cooling passages provided on the feet of segments of blades.
  • the upstream wing of the turbine has at least one injection hole crossing and opening inside the space ring, each injection hole being intended for cooperate with a cooling air injector from the turbomachine.
  • the disc of turbine is monobloc.
  • FIGS. 2 With reference in conjunction with FIGS. 2, there is shown a turbine wheel 1 for turbomachine, according to a first embodiment preferred embodiment of the present invention.
  • the turbine wheel 1, main axis longitudinal section 2, comprises a turbine disk 4, monoblock preference, as well as a plurality of segments of blades 6 mounted on the disc 4, only one of these segments 6 being shown in FIG.
  • Each blade segment 6 comprises a foot 8 extended radially outwards by a blade 10, or preferably by several blades.
  • each segment 6 is provided with three blades 10 secured to an outer radial portion 11 of the foot 8, this part 11 of the metal plate type thickness possibly variable, for example take substantially the form of an angular sector of a cylindrical geometry with axis identical to the axis 2.
  • the wheel of turbine 1 may be designed in such a way as to twenty segments 6 of three blades 10, these segments 6 being regularly distributed around the axis main longitudinal 2 and mounted on the disk of turbine 4.
  • each space (not shown) between two directly consecutive segments 6 is sealed in a conventional manner using known means of the skilled person.
  • the turbine disc 4 includes a body internal 12, preferably of the solid body type, or more classically pierced with a central hole if necessary to pass a low pressure turbine shaft through 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 secondly by a downstream wing 14b.
  • the upstream wings 14a and the downstream wings 14b extend each substantially annularly around the axis longitudinal head 2 of wheel 1, and extend each radially to a radial end of the disc 4.
  • upstream and downstream are defined by relative to a main direction of gas flow through the turbine wheel 1, this direction being schematically represented by the arrow Dp on the figure 1.
  • the upstream wings 14a and downstream 14b are both elastic, so as to can be easily moved from one position deviation from commitment as shown on the Figures 1 and 2, at a close position, and Conversely.
  • This specificity makes it possible to authorize mounting the blade segments 6 on the disk 4 monoblock, as will be exposed more detailed later.
  • each segment 6 includes upstream commitment means 16a as well as downstream engagement means 16b, these extending radially inward from part 11 of the foot 8, to which they are joined.
  • These means upstream 16a and downstream 16b cooperate respectively with means of upstream commitment complementary 18a constituting a radial end external of the upstream wing 14a, and with means complementary downstream commitment 18b constituting a outer radial end of the downstream wing 14b.
  • upstream commitment complementary 18a constituting a radial end external of the upstream wing 14a
  • means complementary downstream commitment 18b constituting a outer radial end of the downstream wing 14b.
  • the blade segments 6 are in external radial abutment against the turbine disc 4, and these segments 6 can not therefore move in the external radial direction Re with respect to this same disc 4.
  • the means complementary upstream commitment 18a and the means additional commitment agreements 18b, as well as upstream engagement means 16a and downstream 16b of the foot 8 of each blade segment 6, each have a section longitudinal hook-shaped.
  • the means of engagement upstream complementary 18a have a section longitudinal hook-shaped projecting towards upstream.
  • the means of engagement complementary upstream 18a project upstream relative to the rest of the upstream wing 14a.
  • these means 18a define an engagement opening 20a substantially oriented radially inwards of the wheel 1, as it appears clearly in the figure 3.
  • the free end 22a of the hook point radially inward of the wheel 1.
  • the upstream engagement means 16a also have a shaped longitudinal section hook, the latter protruding downstream.
  • these means 16a define an opening 24a engagement substantially radially oriented towards the outside of the wheel 1. Always in a preferred way and in longitudinal section, the free end 26a of the hook tip radially outward of the wheel 1.
  • the free end 22a passes through the opening of engagement 24a and is in contact with a background of hook 28a of upstream engagement means 16a.
  • the free end 26a crosses the engagement opening 20a and is in contact with a hook bottom 30a means of upstream commitment complementary 18a.
  • manufacture it might be decided to favor one or the other of the contacts 28a or 30a, without leaving the framework of the invention.
  • the means of engagement complementary upstream 18a extending preferentially annularly around the main axis longitudinal axis 2 of the wheel 1, and the engagement means upstream 16a of each blade segment 6 being each made to form an annular portion of same axis extending circumferentially all the way of the foot 8 on a circumferential length L, it is then possible to obtain an upstream seal particularly satisfactory.
  • the centrifugal force generated during the rotation of wheel 1 causes 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 the 28a hook background.
  • the observed support is substantially circumferential axis identical to the longitudinal main axis 2, and thus contributes strongly to obtain an upstream seal perfectly adapted to the needs encountered.
  • the means of engagement complementary downstream 18b have a section longitudinal hook-shaped projecting towards downstream.
  • the means of engagement complementary downstream 18b project downstream through compared to the rest of the downstream wing 14b.
  • these means 18b define a commitment opening 20b substantially oriented radially inwards of the wheel 1, as it appears clearly in the figure 3.
  • the free end 22b of the hook point radially inward of the wheel 1.
  • downstream engagement means 16b also have a shaped longitudinal section hook, the latter protruding upstream.
  • these means 16b define an opening 24b engagement substantially radially oriented towards the outside of the wheel 1. Always in a preferred way and in longitudinal section, the free end 26b of hook tip radially outward of the wheel 1.
  • the means of engagement complementary downstream 18b also extending preferably annularly around the axis longitudinal head 2 of wheel 1, and the means downstream commitment 16b of each blade segment 6 being each made to form an annular portion of the same axis extending circumferentially all the along the foot 8 along a circumferential length identical to that of the upstream commitment means 16a, it it is possible to obtain a downstream seal particularly satisfactory. This is explained always because of the centrifugal force generated during of the rotation of the wheel 1, causing a pressure important on the one hand between the free end 26b and the 30b hook bottom, and secondly between the end free 22b and hook bottom 28b.
  • each of the segments of blades 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 inwards of the wheel 1.
  • the upstream flexible blade 32a has a solidarity end of the means upstream commitment 16a of the segment 6, and an end free 34a having a notch 36a. So, in the state mounted shown in Figures 1 and 2, a pin 38a secured to the upstream wing 14a and protruding from this one upstream, is inserted until the bottom notch 36a open radially inwards of the wheel 1. Therefore, the pin 38a therefore ensures the internal radial stop function for segment 6 concerned.
  • the holding means 32b of each segment 6 take the form of a blade downstream flexible, the latter extending radially towards the inside of the wheel 1.
  • the blade downstream flexible hose 32b has an integral end of downstream commitment means 16b of the segment 6, and a free end 34b having a notch (no referenced).
  • a pin 38b secured to 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 function of internal radial stop for the segment 6 concerned.
  • the flexible blades upstream 32a and downstream 32b can be connected respectively to the upstream commitment means 16a and the means downstream commitment 16b, at a portion of these means 16a and 16b defining the hook bottoms 28a and 28b.
  • the junction between the blades flexible 32a and 32b and the engagement means 16a and 16b is carried out at the level of a portion of these means 16a and 16b located radially the most inwards of the turbine wheel 1.
  • the upstream wings 14a and downstream 14b define between them, when they occupy their position spread of engagement, an annular space 40 arranged around the longitudinal main axis 2.
  • This space ring 40 open radially outward, therefore communicates with cooling passages 42 provided on the foot 8 of the blade segments 6, and more precisely on the outer radial part 11 of this same foot.
  • the upstream wing 14a has least one injection hole 44 passing through it and opening into the annular space 40. From this way, each injection hole 44 being intended for cooperate with an air injection system from cooling of the turbomachine (not shown), it so is easily possible to cool the blades 10 without requiring an upstream labyrinth. Indeed, the cooling air ejected injectors can then borrow successively injection holes 44, the annular space 40, then the cooling passages 42 communicating with a cooling circuit (not shown) practiced in inside the blades 10.
  • FIGS. 6a to 6d it is represented various stages of a mounting process according to a preferred embodiment of this invention, of the turbine wheel 1 which has just been described.
  • a first step of this process consists in bringing the upstream wings 14a and downstream 14b of the deviated position of commitment, to the position close. This is done using a tool appropriate diagrammatically represented by the references 46, and whose function is to exercise a pressure on the upstream wings 14a and downstream 14b of the disc monobloc 4, so that they deform and become bring one closer to the other.
  • both wings 14a and 14b are each subjected to pressure distributed annularly around the main axis longitudinal 2, and respectively applied to a upstream face of the upstream wing 14a and on a downstream face of the downstream wing 14b.
  • a next step is to set up the various segments 6 with respect to turbine disc 4, as shown on the Figure 6b.
  • the installation is preferably carried out in moving radially towards the inside of the wheel 1 each of the segments 6, so that the means complementary upstream commitment 18a and downstream 18b are inserted within those same segments 6, without being hampered by the means upstream commitment 16a and downstream 16b.
  • the engagement means complements 18a and 18b can therefore easily be introduced in a space delimited jointly by the upstream commitment means 16a, the means 16b downstream engagement, as well as the radial portion external 11 of the foot 8 of segment 6 concerned.
  • this step of setting up is completed only when segments 6 have been placed sufficiently radially inwards by compared to disk 4, so that when the upstream wings 14a and downstream 14b are again brought into their deviated position of commitment, means of engagement upstream 16a and downstream 16b of the foot 8 of each segment 6 able to engage respectively with the complementary upstream commitment means 18a and downstream 18b of the turbine disk 4, during a relative radial displacement of these various elements.
  • this step of setting up only ends when the means of engagement 18a and 18b have come into contact with the part 11 of the foot 8 of each segment 8, as the shows Figure 6b.
  • the means complementary commitment 18a and 18b then an internal radial stop function for the segments 6, indicating that the blade segments 6 are actually correctly set up.
  • the next step in this assembly process can then consist in carrying out a displacement of each of the blade segments 6 in the radial direction external Re relative to the disk 4, so as to ensure commitment between the various means commitment 16a, 16b, 18a and 18b, that is to say cause the introduction of the free ends 22a, 22b, 26a and 26b respectively in the openings engagement 24a, 24b, 20a and 20b.
  • this radial displacement is stopped by the cooperation between the various means of engagement 16a, 16b, 18a and 18b, namely by the coming into contact of the free ends 22a, 22b, 26a and 26b respectively with the hook bottoms 28a, 28b, 30a and 30b.
  • turbine wheels 100 and 200 for a turbomachine respectively according to a second and according to a third embodiment preferred embodiments of the present invention.
  • the turbine wheel 100 according to the second preferred embodiment shown in the FIG. 4 is substantially similar to wheel 1 according to the first preferred embodiment described above.
  • the main difference is that segments 6 of the wheel 100 do not have means of maintenance permitting 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.
  • the various engagement means 16a, 16b, 18a and 18b being moreover substantially identical to those described for the turbine wheel 1.
  • the turbine wheel 200 according to the third preferred embodiment shown in FIG. 5 differs from the turbine wheels 1 and 100 in that the repositioning upstream wings 14a and downstream 14b in their discarded commitment position causes simultaneously a commitment and a cooperation between the various engagement means 16a, 16b, 18a and 18b.
  • these various means of engagement 16a, 16b, 18a and 18b are designed so that when they cooperate with each other, they ensure the restraint of segments 6 relative to the disk 4 in the outer radial direction Re, as well only in the internal radial direction Ri. Segments 6 blades do not require means of maintenance such as those described for the turbine wheel 1.
  • the upstream commitment means 16a and the downstream commitment device 16b each may have an annular groove 48a and 48b respectively open downstream and open towards upstream.
  • the means of engagement complementary 18a and 18b can each be provided an annular projection 50a and 50b making respectively upstream and downstream, and having a form complementary to that of annular grooves 48a and 48b so as to be maintained correctly. With such an arrangement, the engagement means 16a, 16b, 18a and 18b do not require so more to present the shape of a hook in section longitudinal.

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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 Schaufelrad für eine Turbomaschine und Methode zur Montage der Schaufeln auf der Nabe Active EP1517004B1 (de)

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 true EP1517004A1 (de) 2005-03-23
EP1517004B1 EP1517004B1 (de) 2014-12-17

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EP04104494.2A Active EP1517004B1 (de) 2003-09-19 2004-09-16 Schaufelrad für eine Turbomaschine und Methode zur Montage der Schaufeln auf der Nabe

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2901305A1 (fr) * 2006-05-18 2007-11-23 Snecma Sa Disque de turbine monobloc
WO2018100160A1 (de) * 2016-12-01 2018-06-07 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US9341071B2 (en) * 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
US9518471B2 (en) * 2013-10-16 2016-12-13 General Electric Company Locking spacer assembly
KR102182102B1 (ko) * 2014-11-27 2020-11-23 한화에어로스페이스 주식회사 터빈 장치
US11371351B2 (en) 2020-01-17 2022-06-28 Raytheon Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment
US11339673B2 (en) * 2020-01-17 2022-05-24 Raytheon Technologies Corporation Rotor assembly with internal vanes

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US2401826A (en) * 1941-11-21 1946-06-11 Dehavilland Aircraft Turbine
US2857132A (en) * 1952-02-19 1958-10-21 Gen Motors Corp Turbine wheel
DE1247335B (de) * 1965-04-02 1967-08-17 Rolls Royce Stroemungsmaschinen-Laufrad

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US819106A (en) * 1905-08-09 1906-05-01 Wilkinson Turbine Company Turbine bucket-wheel.
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

Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
US2401826A (en) * 1941-11-21 1946-06-11 Dehavilland Aircraft Turbine
US2857132A (en) * 1952-02-19 1958-10-21 Gen Motors Corp Turbine wheel
DE1247335B (de) * 1965-04-02 1967-08-17 Rolls Royce Stroemungsmaschinen-Laufrad

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2901305A1 (fr) * 2006-05-18 2007-11-23 Snecma Sa Disque de turbine monobloc
WO2018100160A1 (de) * 2016-12-01 2018-06-07 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine

Also Published As

Publication number Publication date
EP1517004B1 (de) 2014-12-17
FR2860031A1 (fr) 2005-03-25
JP4058030B2 (ja) 2008-03-05
JP2005098300A (ja) 2005-04-14
US7134843B2 (en) 2006-11-14
US20050106019A1 (en) 2005-05-19
FR2860031B1 (fr) 2007-09-07

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