EP2762681B1 - Tambour de rotor de turbomachine axiale et turbomachine associée - Google Patents

Tambour de rotor de turbomachine axiale et turbomachine associée Download PDF

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Publication number
EP2762681B1
EP2762681B1 EP13153799.5A EP13153799A EP2762681B1 EP 2762681 B1 EP2762681 B1 EP 2762681B1 EP 13153799 A EP13153799 A EP 13153799A EP 2762681 B1 EP2762681 B1 EP 2762681B1
Authority
EP
European Patent Office
Prior art keywords
drum
wall
retaining surfaces
annular
accordance
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.)
Active
Application number
EP13153799.5A
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German (de)
English (en)
French (fr)
Other versions
EP2762681A1 (fr
Inventor
Christophe Remy
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 Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
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 Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Priority to EP13153799.5A priority Critical patent/EP2762681B1/fr
Priority to CA2841344A priority patent/CA2841344A1/en
Priority to US14/168,530 priority patent/US9739150B2/en
Priority to RU2014103113A priority patent/RU2651697C2/ru
Priority to CN201410116548.2A priority patent/CN103967840B/zh
Publication of EP2762681A1 publication Critical patent/EP2762681A1/fr
Application granted granted Critical
Publication of EP2762681B1 publication Critical patent/EP2762681B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/38—Arrangement of components angled, e.g. sweep angle

Definitions

  • the invention relates to an axial compressor bladed drum. More particularly, the invention relates to a drum on which the rotor blades are fixed by engagement with positive contact material. The invention also relates to a turbomachine provided with such a drum.
  • An axial turbomachine compressor advantageously has several compression stages. Each compression stage comprises an annular row of rotor vanes and an annular row of stator vanes.
  • a compressor rotor can be formed of a drum with an axially symmetrical wall, which allows for a lightweight and economical monoblock element.
  • a drum has a generally thin annular wall, on which the rotor blades are directly fixed.
  • the blades can be welded into openings in the drum wall.
  • the blade roots can also be inserted in axial grooves formed on the drum.
  • the drum may be provided with annular cavities inside which fixing surfaces are provided.
  • the rotor blades have corresponding attachment surfaces that allow them to be anchored in the cells.
  • the document EP 2 075 417 A1 discloses an axial turbomachine compressor rotor drum.
  • the drum has a symmetrical wall and annular cells. These are open radially outward and have a narrowing in the same direction. Blades are fixed inside these annular cells. They have for this purpose feet having profiles complementary to the cells and are inserted therein. They are thus retained radially.
  • the existence of the cell requires a large mass of material that weighs down the drum. This material also represents a cost.
  • an annular cell forms a discontinuity of material in the wall of the drum since it extends radially at height of the wall of the drum. It reduces its rigidity, which results in an increase in deformations during operation of the turbomachine.
  • the document EP 1 406 019 A1 also discloses a turbomachine rotor drum having a machined groove and blade retention surfaces, in accordance with the preambles of claims 1 and 3.
  • the document EP 0422433 A1 discloses a turbomachine rotor disk having a bearing rib projecting from the outer radial surface of the disk and having blade retention surfaces.
  • the invention aims to solve at least one of the problems raised by the prior art.
  • the invention also aims to facilitate the machining of the mounting surfaces of the drum.
  • the invention also aims to lighten an axial compressor bladed drum.
  • the invention also aims to stiffen an axial compressor bladed drum.
  • the invention relates to an axial turbomachine rotor drum according to claims 1 and 3.
  • the drum may be free of disks or annular disks.
  • the profile of each of the two retention surfaces forms an average angle of between 30 ° and 60 ° with the axis of rotation and / or the profiles of said surfaces form between them an average angle between 60 ° and 120 °.
  • the wall forms the drum structure, preferably from its front end to its rear end.
  • the wall of the drum has one or more annular ribs upstream and downstream, respectively, of the two retention surfaces, said ribs being configured to cooperate by abrasion with annular layers of abradable material, the wall extending substantially rectilinearly along the two retention surfaces, between said upstream and downstream ribs.
  • the two retention surfaces are generally radially raised relative to the adjacent wall.
  • the radial height of the retention surfaces represents between 1% and 10% of the average radius of the wall of the drum where they are arranged, preferably between 1% and 5%, more preferably between 1% and 3%.
  • This feature of the invention aims to reduce the radial size of the fastening surfaces and the fastening lugs and the annular body or collars.
  • a segment of the two annular retention surfaces comprises a blade mounting notch on only one of the two surfaces, so as to allow the blades to be fitted by an engagement movement with the retention surface. without notch, followed by a tilt penetrating the platform into the notch.
  • the two flanges are implanted on the wall, at a distance from one another, said distance being preferably greater than 10 mm.
  • the annular body may generally have a trapezoid profile whose parallel sides generally extend along the axis of rotation of the rotor, the smallest of these sides being arranged inwardly.
  • the annular body comprises a radially outwardly open annular groove configured to receive a preferably toric seal intended to be pressed against the platforms of the blades under the effect of the centrifugal force during the rotation. drum.
  • the drum comprises the row of blades, said blades each comprising a platform provided with two bearing surfaces configured to cooperate with the retaining surfaces on the wall.
  • the platform of the blades comprises a cavity open towards the wall of the drum and forming the bearing surfaces, the bottom of the cavity forming a radial bearing surface directed towards the inside of the drum.
  • the two contact surfaces of the blade platforms are situated essentially at the right of the leading and trailing edges, respectively, of the blades.
  • the subject of the invention is a turbomachine comprising a turbine or compressor rotor, preferably a low-pressure rotor, which is remarkable in that the rotor comprises a drum according to the invention, and preferably in that the drum comprises several sets of retention surfaces. each game corresponding to a row of blades.
  • the invention makes it possible to simplify the machining of a turbomachine drum.
  • the clearance around the retention surfaces is increased, which simplifies the corresponding manufacturing or metrology operations.
  • the invention allows positioning on the same side of the wall functional elements such as retention surfaces and wipers.
  • the volume to be machined inside is reduced.
  • This configuration provides a smooth interior surface, which facilitates the integration of interior supports to resume cutting efforts.
  • the invention makes it possible to stiffen the drum.
  • the profile of its wall has continuity of curvature and limits the changes of radii.
  • the variations in thickness of the profile are limited, which improves the longevity of the drum.
  • the invention also makes it possible to improve the fastening stability of the vanes on the rotor. Indeed, it comes into contact with surfaces that can more easily be extended or removed from each other, without increasing the amount of material needed to obtain the drum, or without weighing it down.
  • inner and outer refer to a positioning relative to the axis of rotation of the turbomachine.
  • the figure 1 illustrates an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • a first compression level called a low-pressure compressor 4
  • a second compression level called a high-pressure compressor 6
  • a combustion chamber 8 and one or more levels of turbines 10.
  • Reducing means can increase the speed of rotation transmitted to the compressors.
  • the different turbine stages can each be connected to the compressor stages via concentric shafts.
  • the compressor comprises several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor 12 around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 10.
  • a commonly designated fan inlet fan 16 is coupled to the rotor 12 and generates a flow of air which is divided into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical walls or ferrules which can be internal and external.
  • the figure 2 is a sectional view of a low-pressure compressor 4 of an axial turbomachine 2 such as that of the figure 1 . It is possible to observe a portion of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20.
  • the rotor 12 comprises several rows of rotor blades 24, in the specific case of the figure 2 three rows are planned.
  • the low-pressure compressor 4 comprises a plurality of rectifiers, for example four, which each contain a row of stator vanes 26.
  • the rectifiers are associated with the fan 16 or with a row of rotor vanes 24 for straightening the air flow, so as to convert the speed of the flow into pressure.
  • the rotor vanes 24 extend substantially radially from the rotor 12. They are regularly spaced from each other, and have the same angular orientation in the flow. Advantageously, these rotor vanes 24 are identical. Optionally, the spacing between the vanes may vary locally, as can their angular orientation. Some blades may be different from the rest of the blades in the row.
  • the rotor 12 comprises a drum 28.
  • the drum 28 has a wall 30 with a profile of revolution about the axis of rotation 14.
  • the profile of revolution of the wall may have a generally continuous curvature. It radially follows the section variation of the inner surface of the primary flow.
  • the wall 30 is essentially thin. Its thickness is generally constant. Its thickness is less than 10.00 mm, preferably less than 5.00 mm, more preferably less than 2.00 mm.
  • the wall 30 forms a hollow body which delimits a hollow space, having a cylinder or ogive shape.
  • the drum 28 and / or the rotor blades 24 are made of metal materials, preferably titanium. They are each from matter.
  • the drum 28 comprises annular ribs 32 or wipers. They form annular lamellae which extend radially. They are intended to cooperate by abrasion with annular layers of abradable material so as to ensure a seal. Generally, a single layer of abradable cooperates with two ribs 32.
  • the rotor 12 can deform. It may, for example, expand or increase in diameter under the effect of centrifugal force. These deformations can be observed on the wall 30.
  • the rotor 12 has annular retention surfaces.
  • the rotor vanes 24 comprise corresponding retention surfaces which cooperate with the retaining surfaces of the drum, making it possible to fasten the rotor blades thereon.
  • the rotor blades 24 have lower platforms 34 arranged opposite the rotor 12. The attachment surfaces are arranged between the rotor 12 and the lower platforms 34.
  • the figure 3 represents a drum according to a first embodiment of the invention.
  • the drum 28 comprises on its outer surface an annular body 36.
  • the latter has a general trapezoidal profile whose parallel edges are substantially parallel to the axis of rotation 14, the two other inclined sides extending essentially radially.
  • the inclined sides of the trapezoidal profile generate by rotation about the axis of rotation 14 a set of two annular retention surfaces 38.
  • the drum 28 may have several sets of such retention surfaces. Each set of retention surfaces 38 is separated from the other sets by ribs 32.
  • the radial thickness of the annular body 36 is greater than 5.00 mm, preferably greater than 10.00 mm, more preferably greater than 20.00 mm.
  • the annular body 36 forms an outer ring which makes it possible to reinforce and stiffen the drum 28. It makes it possible to reduce the deformations of the drum 28 related to the centrifugal force.
  • the annular body 36 makes it possible to replace the inner annular reinforcements of the drum or "leeks".
  • a drum is generally machined by turning from a drum-shaped machining blank whose walls encompass the finished drum. The crude must embrace the surfaces radially retentions and leeks. The set requires to perform important machining. Since the annular body 36 is located on the same side as the retention surfaces 38, the machining stock can be thinned and the corresponding machining reduced.
  • the rotor blade 24 comprises attachment lugs 40 extending radially and axially beneath its lower platform 28.
  • the attachment lugs 40 are inclined towards each other.
  • the corresponding retention surfaces 42 are implanted on the inner surfaces of the fastening tabs 40.
  • the corresponding retention surfaces 42 are opposite one another.
  • the retention surfaces 38 and the corresponding retention surfaces 42 are complementary. They marry on most of their expanses. They can be frustoconical. They are configured to cooperate by engagement of material so as to fix the rotor blade 24 on the drum 28. They form a dovetail type fastener.
  • the flared section of the corresponding retention surfaces 42, together with the narrowed section defined by the retaining surfaces 38 of the drum allow radial retention of the vane 24 towards the drum 28.
  • the revolution profiles of the retention surfaces 38 and 42 are inclined relative to the perpendicular 44 to the axis of rotation 14 by an angle ⁇ , which is between 10 ° and 80 °, preferably between 30 ° and 60 ° included.
  • the profiles of the retention surfaces 38 and 42 are inclined relative to each other by an angle ⁇ .
  • the angle ⁇ is between 60 ° and 120 °. The greater the angle ⁇ , the less the centrifugal force tends to move the fastening tabs 40 during operation of the turbomachine.
  • the retention surfaces 38 are substantially in radial elevation with respect to the wall 30 of the drum 28.
  • the wipers 32 are axially spaced therefrom.
  • the drum 28 is free axially surface capable of forming an obstacle to the retention surfaces 38 to more than 5.00 mm, preferably to more than 15.00 mm, more preferably to more than 30.00 mm.
  • the retention surfaces 38 are therefore easily accessible for machining, for example to achieve a blank and a finish.
  • the wall 30 of the drum 28 can extend substantially rectilinearly at the retention surfaces 38, preferably between the ribs 32 arranged upstream and downstream. This feature makes it possible to preserve the rigidity of the drum 28. In particular, it is more resistant to axial compression. One consequence is that its wall 30 can be thinned.
  • the profile of the inner surface of the wall 30 may be generally straight or substantially curved. This aspect reduces the stress concentrations and improves the life of the drum.
  • the annular body 36 has an annular groove open radially outwardly.
  • the rotor 12 comprises an O-ring 48 housed inside this annular groove.
  • the inner radius of the O-ring 48 is less than or equal to the radius of the bottom of the groove, the radii being measured from the axis of rotation 14.
  • the O-ring 48 is essentially elastic. Under the effect of the centrifugal force that appears during the operation of the turbomachine, the O-ring 48 is pressed against the inner surface of the lower platform 34 of the rotor blade 24. It thus ensures a seal between the upstream and downstream sides. of dawn 24.
  • the annular body 36 comprises radial bearing surfaces 50 arranged upstream and downstream. They can be essentially cylindrical and are oriented radially outwards.
  • the rotor blade 24 has corresponding bearing surfaces 52 which are able to cooperate with the bearing surfaces 50 of the drum.
  • the bearing surfaces 52 are arranged facing the bearing surfaces 50 of the drum.
  • these surfaces 50 and 52 are spaced apart from each other. Centrifugal force keeps them at bay. They are able to come into contact with one another or at least to be adjacent in the event of a change in the operating condition of the turbomachine.
  • These surfaces 50 and 52 make it possible to reduce or block the downstream upstream tilting of the vanes 24 with respect to the drum 28, this phenomenon being known by the term "rocking".
  • the figure 4 represents the annular body 36 of the drum 28 seen radially from the outside.
  • a rotor blade 24 is mounted therein by means of its fixing lugs 40.
  • the annular body 36 has at least one axial notch 53 at one of the retention surfaces, in order to be able to fit the rotor blades 24.
  • a latch (not shown) or several locks can close the notch 53 and can serve to tangentially block the blades 24.
  • the locks can overlap the annular body 36 or cross axially.
  • the figure 5 illustrates a section of the drum according to the first embodiment of the invention, the section being taken along the axis 5-5 traced on the figure 4 .
  • a segment or section of the two annular retention surfaces may comprise a single mounting notch 53 of the vanes on only one of the two retention surfaces 38, so as to allow the vanes 24 to be mounted by a movement of engagement with the retention surface without notch, vis-à-vis the notch 53, followed by a tilt partially penetrating the bracket 40 of the platform 34 in the notch 53.
  • the blade 24 can then be slid in the circumferential direction of the drum, so that its fixing lugs 40 are no longer at the level of the notch (s) 53.
  • the figure 6 represents a rotor according to a second embodiment of the invention. This figure 6 resumes the numbering of the preceding figures for identical or similar elements, however the number is incremented by 100. Furthermore, reference is made in particular to the description of the preceding figures for their similar or equivalent elements. Specific numbers are used for the specific elements of this embodiment.
  • the drum 128 comprises two annular flanges 154.
  • the flanges 154 are inclined, preferably relative to one another. They move away from each other to the outside. Their profiles have an average length and width. The length is greater than three times the average width, preferably greater than five times.
  • the junctions of the collars 154 to the wall 130 may be distant from each other. the other.
  • the axial distance between the retention surfaces measured at the junction with the outer surface of the wall 130 is greater than the average length of the profile of the flanges 154, preferably greater than 1.5 times, more preferably greater than twice.
  • the wall 130 may be locally thickened between the flanges 154 so as to strengthen it.
  • This configuration makes it possible to axially separate the retention surfaces 138 from each other without making the drum 128 heavier.
  • the stability of the blade 124 on the drum is improved.
  • the inclination angles of the profiles of the retention surfaces 138 and 142 can be chosen with greater freedom.
  • the collars 154 define between them an annular space 156.
  • One of them may have a thickening so as to receive an annular groove and an O-ring capable of sealing against the platform of the rotor blade 124.
  • the collars 154 help to stiffen the drum in the manner of strapping.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13153799.5A 2013-02-04 2013-02-04 Tambour de rotor de turbomachine axiale et turbomachine associée Active EP2762681B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP13153799.5A EP2762681B1 (fr) 2013-02-04 2013-02-04 Tambour de rotor de turbomachine axiale et turbomachine associée
CA2841344A CA2841344A1 (en) 2013-02-04 2014-01-24 Attaching the blades of an axial turbocompressor to the compressor drum
US14/168,530 US9739150B2 (en) 2013-02-04 2014-01-30 Attaching the blades of an axial turbocompressor to the compressor drum
RU2014103113A RU2651697C2 (ru) 2013-02-04 2014-01-30 Барабан ротора осевой турбомашины и турбомашина
CN201410116548.2A CN103967840B (zh) 2013-02-04 2014-02-07 将轴流涡轮压缩机的叶片连接至压缩机鼓

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13153799.5A EP2762681B1 (fr) 2013-02-04 2013-02-04 Tambour de rotor de turbomachine axiale et turbomachine associée

Publications (2)

Publication Number Publication Date
EP2762681A1 EP2762681A1 (fr) 2014-08-06
EP2762681B1 true EP2762681B1 (fr) 2017-09-06

Family

ID=47722003

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13153799.5A Active EP2762681B1 (fr) 2013-02-04 2013-02-04 Tambour de rotor de turbomachine axiale et turbomachine associée

Country Status (5)

Country Link
US (1) US9739150B2 (ru)
EP (1) EP2762681B1 (ru)
CN (1) CN103967840B (ru)
CA (1) CA2841344A1 (ru)
RU (1) RU2651697C2 (ru)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3027071B1 (fr) 2014-10-13 2019-08-23 Safran Aircraft Engines Procede d'intervention sur un rotor et clinquant associe
FR3039225B1 (fr) * 2015-07-20 2017-07-21 Snecma Turbomachine, telle par exemple qu'un turboreacteur d'avion
CN110005637B (zh) * 2018-01-04 2021-03-26 中国航发商用航空发动机有限责任公司 轴流式航空发动机转子
US11085315B2 (en) * 2019-07-09 2021-08-10 General Electric Company Turbine engine with a seal
IT201900014736A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di tenuta integrali per pale trattenute in un rotore a tamburo esterno anulare girevole in una turbomacchina.

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DE1957614C3 (de) * 1969-11-15 1974-03-14 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Laufschaufelkranz für Gasturbinentriebwerke mit hoher DrehzahL
GB2001398A (en) * 1977-07-22 1979-01-31 Rolls Royce Bladed Rotor for Gas Turbine Engine
DE3839672A1 (de) * 1988-11-24 1990-05-31 Mtu Muenchen Gmbh Schaufelfussbefestigung fuer eine fasertechnische rotorschaufel
DE3934207A1 (de) * 1989-10-13 1991-04-25 Mtu Muenchen Gmbh Anordnung zur befestigung von turboschaufeln
DE4442157A1 (de) * 1994-11-26 1996-05-30 Abb Management Ag Verfahren und Vorrichtung zur Beeinflussung des Radialspieles der Beschaufelung in axialdurchströmten Verdichtern
US6409472B1 (en) 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
FR2845436B1 (fr) * 2002-10-02 2004-12-31 Snecma Moteurs Tambour formant en particulier un rotor de turbomachine, compresseur et turbomoteur comprenant un tel tambour
RU2270937C1 (ru) * 2004-08-10 2006-02-27 Акционерное общество открытого типа Авиамоторный научно-технический комплекс "Союз" Осевой компрессор газотурбинного двигателя (варианты)
EP2075417B1 (fr) 2007-12-27 2016-04-06 Techspace Aero Plateforme pour une roue aubagée de turbomachine, roue aubagée et compresseur ou turbomachine comportant une telle roue aubagée
EP2400160B1 (fr) * 2010-06-23 2014-01-01 Techspace Aero S.A. Rotor allégé de compresseur axial

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Also Published As

Publication number Publication date
US9739150B2 (en) 2017-08-22
CN103967840B (zh) 2018-12-18
CA2841344A1 (en) 2014-08-04
RU2651697C2 (ru) 2018-04-23
US20140219803A1 (en) 2014-08-07
EP2762681A1 (fr) 2014-08-06
RU2014103113A (ru) 2015-08-10
CN103967840A (zh) 2014-08-06

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