EP3724454A1 - Aube multipale de rotor de turbomachine et rotor la comprenant - Google Patents
Aube multipale de rotor de turbomachine et rotor la comprenantInfo
- Publication number
- EP3724454A1 EP3724454A1 EP18829759.2A EP18829759A EP3724454A1 EP 3724454 A1 EP3724454 A1 EP 3724454A1 EP 18829759 A EP18829759 A EP 18829759A EP 3724454 A1 EP3724454 A1 EP 3724454A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- platform
- blades
- rotor
- axial direction
- 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
Links
- 241000272165 Charadriidae Species 0.000 claims description 63
- 238000005304 joining Methods 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 description 11
- 210000003462 vein Anatomy 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000003351 stiffener Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
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
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion 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
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/90—Mounting on supporting structures or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the present invention relates to the field of paddle rotors in turbomachines, more particularly the case where the blades are made individually and fixed on a disk to form the paddle rotor.
- a low pressure turbine rotor is generally composed of several tens or hundreds of vanes mounted on a disk.
- Each blade is composed of at least one blade, a clip to fit in the disk of the rotor and a platform, placed between the two, so as to form the inner face of the vein in which passes the flow of gas crossed by the blades.
- Such a rotor can be heavily loaded by a very high rotational speed.
- the maintenance of the blades on the rotors and the sealing against the flow of gas at the platforms are part of the problems to be solved in the design of these rotors and their blades.
- a two-blade blade 100 comprises two blades 101, 102 extending in span along a radial direction R between an internal platform 103 and an external platform 104 delimiting the vein of passage of the gas flow.
- the inner platform 103 also connects the blades 101, 102, and a monoblock foot 105 which fits between the teeth 106 of a rotor disc. 107 (shown only in the vicinity of the dawn).
- the dovetail-shaped fastener comprises a bulb 107 placed at the end of a stilt 108 in two parts, each of the two parts joining the base of a blade.
- the manufacture of the blade being made by casting, not to have a solid zone between the two parts of the stilt 108, a cavity 109 is formed between the two parts of the stilt 108 using a core used during the foundry process.
- the attachment foot 105 is substantially centered in the circumferential direction T between the two blades 101, 102, so as to balance the stresses to retain the blades under the centrifugal forces.
- Figure 1 that it requires the two parts of the stilt 108 to have a non-radial part to reach the base of the blades.
- the arrows in FIG. 1 schematically show the path of the stresses due to the centrifugal forces, along the stilt 108 and the blades 101, 102. In the part where the arrows are not aligned with the radial direction R this creates a moment in the stilt and therefore supplements constraints.
- the attachment foot 105 must hold two blades instead of one, withstanding additional constraints due to the offset of the foot 105 relative to the blades.
- the foot 105 being traversed by the core 109, it must be even wider than the double of a single foot to hold a single blade.
- the object of the invention is to propose a solution for minimizing the mass of the attachment of a two-blade blade, in particular by reducing the level of the stresses to which the fastening of the blades must withstand during the operation of the rotor.
- the invention also aims to avoid too much hyperstatism between the disk and the blade, which would require expensive adjustments in precision between the blade attachments and the fixing teeth on the disk.
- the invention also aims to minimize the mass of the entire rotor at the link with the blades.
- the invention relates to a turbomachine rotor blade comprising a first blade and a second blade arranged to form two successive blades of a blade rotor, a platform forming substantially an angular sector of wall in an axial direction, said two blades being connected at the platform by one of their ends extending substantially in a so-called radial direction substantially perpendicular to said axial direction, and attachment means connected to the platform which are intended to cooperate with fixing means on a rotor disc .
- said attachment means comprise two separate stilts, each stilt extending from the platform, in the radial direction, in the extension of one of said two blades, and carrying an attachment element to a end opposite the platform, said attachment member extending substantially parallel to said axial direction and having at least one surface facing the platform with a constant sectional profile perpendicular to said axial direction, so as to form a surface support for retaining the blade in said radial direction oriented from the platform to the blades.
- each stilt extends parallel to the axial direction with a constant profile of the bearing surface makes it possible to mount the blade according to the invention by sliding the fastening element. against teeth of the rotor disk in the axial direction.
- the disc when the disc is thus equipped with a succession of vanes such that the blades can be associated two by two with stilts which are in their extension, it may be sufficient to provide holding teeth only in a circumferential interval out of two between the stilts. Indeed, if the fastening means are symmetrical, every second interval corresponds to the presence of the bearing surfaces and the other is empty holding means.
- the invention makes it possible to limit the hyperstatic character of the radial retention. against centrifugal efforts. Indeed, compared to a solution of the state of the art for a two-blade blade with a complete attachment under each blade, the blade according to the invention has only two contact planes instead of four. With four contact planes, much tighter manufacturing tolerances should be imposed than in the state of the art to ensure that one or two of the bearing surfaces are not inoperative.
- bearing surfaces are also advantageous for positioning the blades of the blade relative to the disk and therefore their positioning in the engine.
- these bearing surfaces define with the teeth of the disk contact surfaces that position the blades. The greater the distance between the two contact surfaces, the more defects on these surfaces will have a small impact on the angular positioning defect of the blades.
- the bearing surface of the fastening element carried by each stilt is on one side of the outer fastening element with respect to the two stilts in a circumferential direction perpendicular to said axial and radial directions.
- the stilts with their attachment element can be slid to the mounting between two successive teeth of the disc leaving a gap between the two stilts.
- the bearing surface is itself generally inclined relative to the radial direction.
- the placement of the bearing surfaces circumferentially outside the stilts contributes to the stability of the connection to the disc vis-à-vis the forces exerted on the blade during operation of the rotor.
- each stilt comprises a substantially plane web parallel to the axial direction forming said end bearing the fastening element, said web and the fastener element being arranged to have a side face turned in the opposite direction to the another stilt that is parallel to the axial direction with a constant profile.
- a part of the web can also be engaged between the teeth of the disc and thus cooperate with the teeth to participate in the lateral retention of the blade.
- the fastening element comprises a lug forming a lug with respect to said end veil of the stilt.
- This embodiment minimizes the mass used to achieve the attachment of the blade.
- the blades being offset by a given distance at their junction with the platform in a circumferential direction, perpendicular to said axial and radial directions, said ends of the two stilts carrying the attachment element are offset by a distance substantially equal to said given distance.
- the fasteners of several successive blades on the rotor create a repetitive pattern that can cooperate with a uniform distribution of similar teeth at the periphery of the rotor disc.
- each stilt is positioned in a circumferential direction, perpendicular to said axial and radial directions, on an average position of the end connected to the platform of the corresponding blade.
- each stilt is shaped so that the junction of the stilt with the platform follows the junction with the platform of the corresponding blade in its evolution along the axial direction.
- the blade may advantageously comprise at least one wall connecting the two stilts transversely to said axial direction.
- Such a wall has a stiffener function. It will prevent the deformations of the stilts under the centrifugal forces and can make it possible to reduce the thickness of the stilts, therefore their mass.
- Said wall may extend radially between the stilts from the platform to a line joining the radial ends of the fastening elements opposite the platform.
- the invention also relates to a turbomachine rotor comprising blades as described above.
- the disk of said rotor carries at its periphery a succession of similar teeth shaped to cooperate with the blade attachment means, two successive teeth being separated in the circumferential direction by a distance at least equal to the width of a tooth following this direction.
- Figure 1 shows a rear view along the axis of rotation of a two-blade blade according to the state of the art cut in a radial plane.
- Figure 2 shows a rear view along the axis of rotation of a two-blade blade according to the invention.
- FIG. 3 shows a rear view along the axis of rotation of a two-blade blade according to the invention cut in a radial plane.
- FIG. 4 represents a radial projection view on the internal platform of the elements of a blade according to the invention.
- FIG. 5 represents a detail of FIG. 3 with the representation of a fictitious tooth eliminated by virtue of the invention with respect to certain embodiments according to the state of the art.
- Figure 6 shows a perspective view of the rear of an improvement of the two-blade blade according to the invention cut in a radial plane.
- FIG. 7 represents part of the rear view along the axis of rotation of a variant with respect to the blade of FIG. 6.
- FIG. 8 represents a view part of the rear of a variant with respect to the blade of FIG. 6.
- a blade 1 of a turbine comprises two blades 2, 3 extending in a span along a radial direction R between an internal platform 4 and a platform external 5.
- the blade 1 is fixed on a rotor disc 6 movable about a direction axis X (shown in Figure 4), of which only a peripheral portion is shown with the teeth 7 holding the blade.
- the axial and radial directions refer to the axis of the rotor, the internal and external terms refer to the radial direction.
- the terms upstream and downstream in the axial direction refer to the direction of flow for which the vanes were designed.
- the inner and outer platforms 5 and 5 delimit an angular sector of the vein of passage of the flow of gas around said axis X.
- the outer platform 5 is not concerned with the invention and may possibly not exist, it is elsewhere, generally, the case for compressor blades. It is therefore not described further.
- the internal platform 4 is delimited in the circumferential direction T between two axial planes, so as to adjust with the platforms adjacent blades to ensure continuity of the vein wall.
- the body 8 of the internal platform 4 defining the vein has a radial profile determined by the design of the turbine which can be inclined relative to the radial direction R. In the example, this profile deviates from the axis X of the rotor from upstream to downstream.
- the inner platform 4 here comprises an upstream radial web 9 and a downstream radial web 10 which extend radially so as to come into contact with the holding teeth 7 on the disc 6, at the same distance of the X axis.
- the upstream web 9 and the downstream web 10 have a function of maintaining the blade 1, on the one hand to block its movement in the radial direction towards the X axis, on the other hand to block rotation around a direction parallel to the X axis.
- the inner platform 4 generally comprises devices attached to the upstream and downstream sails 9, for example annular spoilers January 1, for sealing with the stator elements. of the turbine that surround the rotor in the axial direction.
- the two blades 2, 3 have a curved profile inclined with respect to the axial direction X which can evolve along their span in the radial direction R.
- FIG. 4 shows the shape of this profile at the base of the blades 2, 3, at their junction with the platform 4.
- the geometries of the two blades 2, 3 are similar with an angular offset corresponding to the rotor design and the number of blades to be installed.
- the bases of the blades 2, 3 are therefore shifted by a distance D determined at the level of the internal platform 4.
- the attachment of the blade 1 to the disc 6 here comprises two separate stilts 12, 13 which are connected to the body 8 of the platform 4 and extend therefrom in the radial extension of one of the blades 2, 3, having substantially the same extension as said blades 2, 3 in the axial direction X.
- Each stub 12, 13 ends here, on the opposite side to the platform, by an axial web 14, 15, parallel to the radial direction R , which is connected to a tab 16, 17, parallel to the axial direction X and inclined relative to the radial direction, which tab forms the free end of the stilt.
- Said tab 16, 17 deviates laterally outwards starting from the axial web 14, 15, forming, in transverse section, an end pin, so that its outer lateral surface S1, S2 is turned towards the platform 4.
- the bearing surface S1, S2 is generally inclined relative to the radial direction.
- the angle of inclination depends on the design made by the skilled person according to the geometry of the turbine and operating constraints. Classically it takes values between 40 and 50 °, but can be outside this range.
- Each lug 16, 17 thus forms an attachment element of the blade 1 and the surfaces S1, S2 form bearing surfaces for retaining the blade in the radial direction R oriented from the platform to the blades.
- the axial webs 14, 15 of the stilts 12, 13 and the end tabs 16, 17 cooperate with the teeth 7 of the disc 6 to maintain the blade 1 according to an operation which will be described later.
- the axial webs 14, 15 of the ends of each stalk 12, 13 are centered on an average position of the bases of the blades 2, 3 on the platform 4 in the circumferential direction T and are therefore shifted in this direction by a distance D 'substantially equal to the offset D between the bases of said blades 2, 3.
- the sets formed of the axial webs 14, 15 and the end tabs 16, 17 are substantially symmetrical with respect to an axial plane passing through the middle of the stilts 12, 13.
- Each stilt 12, 13 has a three-dimensional shape between the axial web 14, 15, and the platform 4, to follow the profile of the base of the corresponding blade 2, 3 at its junction with the body 8 of the platform 4.
- the disc 6 of the rotor comprises at its periphery a ring of similar teeth 7 which are offset in the circumferential direction T by a distance substantially equal to twice the offset distance D between the bases of the blades 2, 3, of so that there are half as many teeth 7 than blades 2, 3 on the rotor.
- Each tooth 7 extends here parallel to the X axis over a distance substantially corresponding to the gap between the upstream and downstream sails 10 of the platform, with a constant transverse profile.
- the blade 1 described above can be installed between two successive teeth 7 by sliding, in the axial direction X, the axial webs 14, 15 of the stilts 12, 13 and the end lugs 16, 17, between two successive 7 teeth.
- Known devices, not described here, then allow to maintain the blade 1 in its axial position relative to the rotor. These devices are not concerned by the invention.
- the profile of each tooth 7 here has the shape of a bulb. Starting from the outer surface of the disc 6, the tooth therefore has a portion of constant thickness given followed by enlargement.
- the shape of this widening is defined so as to form, on one side of the tooth 7, a surface facing the disk 6 which is in contact with the bearing surface S1 connected to one of the stilts 12 of the blade 1 and forming on the other side of the tooth, another surface facing the disk 6 which is in contact with the bearing surface S2 connected to the other of the stilts 13 of an adjacent blade, similar to the dawn 1.
- the fastening elements 16, 17, of the two stems 12, 13 of the vanes are symmetrical, as described above, the profile of the teeth 7 is symmetrical with respect to a median radial plane of the tooth.
- the tooth 7 has a radially outer surface substantially flat or forming a circular cylinder portion centered on the axis X of the rotor.
- the bearing surface S1, S2 of the end lug 16, 17, carried by each stalk 12, 13 is designed to take up about half of the centrifugal forces applied to the blade 1, ie substantially those corresponding to one of said blades. 2, 3.
- a stilt 12, 13 with its end tab 16, 17 must be dimensioned substantially to withstand the stresses imposed by a blade.
- the three-dimensional portion of the stilt 12, 13 takes up these forces towards the base of the corresponding blade 2, 3 with a small radial inclination since it is here essentially to compensate for the curved shape of the profile of the blade 2, 3 but not a circumferential offset of half a gap with said blade.
- the invention also allows a saving in mass on the disc 6. It can be seen in Figures 3 and 4 that the space between the two stalks 12, 13 of a two-blade blade 1 is empty of tooth. On the other hand, by repetition of a blade 1 to another, each tooth 7 of the disk 6 occupies a space extending between two blades in the circumferential direction T, one belonging to a blade, the other belonging to the next dawn. Therefore, compared to the known solution of a two-blade blade with a central foot, the teeth 7 of a disk adapted to blades according to the invention are significantly smaller than for a disk adapted to two-blade blades with a single foot , as can be seen by comparing Figure 3 and Figure 1. Moreover, FIG.
- FIG. 5 illustrates the gain in mass obtained with respect to the use of single blades or two-blade vanes with two fasteners according to the state of the art and which would therefore have 4 contact surfaces between the disc. and dawn.
- the teeth with the single blades would have a smaller thickness in the circumferential direction T but would be twice as many since it would be necessary to add the indicated tooth T in dotted lines to retain each blade, which results in the fact that, overall, the invention allows to gain on the mass of the teeth of the disc.
- the blade 21 further comprises one or more transverse stiffening webs 18 which connect the two stilts 13, 14.
- a stiffening web 18 extends radially to from the body 8 of the platform 4. In the example shown in FIG. 6, it closes the space between the stilts 12, 13 only at the level of the three-dimensional part, leaving free the space between the axial webs 14, 15. As shown in Figure 7, such a realization leaves free an air passage zone under the platform 4 and the upstream sails 9 and downstream 10, between the teeth 7 of the disc 6 of the rotor.
- the blade 31 comprises at least one stiffening web 19 which extends to the radial end of the fastening lugs 16, 17 carried by the stilts 12, 13, in the following manner. the periphery of the disc 6, so as to close the axial passage of the air between the teeth 7 under the platform 4 and the upstream and downstream sails 9 9.
- the description of the embodiments of the invention made in this document is not limiting.
- the dawn described here is two-bladed but one can consider blades having a succession of pairs of blades with their stilts in the extension. In this case, however, the mounting of the bearing surfaces on the teeth becomes hyperstatic for the dawn, so more difficult to adjust.
- Other embodiments of the connection means with the disk, not shown, can also be envisaged.
- the radial blocking of the blade towards the axis can be provided by an element carried by the stilts which presses on the disc 6 or on the radial crown of the teeth 7.
- the inner platform 4 may then have no sail upstream or downstream having a holding function.
- the invention has been described in the case of a turbine blade but it can also relate to blades adapted to other types of rotors, such as compressor rotors, for example.
- an attachment element at the end of the stilts 12, 13 other than a tab forming a bend with respect to the axial web 14, 15 may be used to make the bearing surfaces S1, S2. It can be realized, for example, by spoilers deviating from the surface of the veil. The shape of the teeth on the disc will then be adapted to the shape of the fasteners used on the blade.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1762028A FR3074839B1 (fr) | 2017-12-13 | 2017-12-13 | Aube multipale de rotor de turbomachine et rotor la comprenant |
PCT/EP2018/084462 WO2019115578A1 (fr) | 2017-12-13 | 2018-12-12 | Aube multipale de rotor de turbomachine et rotor la comprenant |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3724454A1 true EP3724454A1 (fr) | 2020-10-21 |
EP3724454B1 EP3724454B1 (fr) | 2022-02-16 |
Family
ID=61224105
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18829759.2A Active EP3724454B1 (fr) | 2017-12-13 | 2018-12-12 | Aube multipale de rotor de turbomachine et rotor la comprenant |
Country Status (5)
Country | Link |
---|---|
US (1) | US11156108B2 (fr) |
EP (1) | EP3724454B1 (fr) |
CN (1) | CN111448366B (fr) |
FR (1) | FR3074839B1 (fr) |
WO (1) | WO2019115578A1 (fr) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5735673A (en) * | 1996-12-04 | 1998-04-07 | United Technologies Corporation | Turbine engine rotor blade pair |
FR2851285B1 (fr) | 2003-02-13 | 2007-03-16 | Snecma Moteurs | Realisation de turbines pour turbomachines ayant des aubes a frequences de resonance ajustees differentes et procede d'ajustement de la frequence de resonance d'une aube de turbine |
EP1881163B1 (fr) * | 2006-07-18 | 2008-10-29 | Industria de Turbo Propulsores S.A. | Rotor de minceur élevée |
RU2645510C2 (ru) * | 2012-11-13 | 2018-02-21 | Снекма | Заготовка и моноблочный лопаточный модуль для промежуточного корпуса газотурбинного двигателя |
US9677405B2 (en) * | 2013-03-05 | 2017-06-13 | Rolls-Royce Corporation | Composite gas turbine engine blade having multiple airfoils |
-
2017
- 2017-12-13 FR FR1762028A patent/FR3074839B1/fr not_active Expired - Fee Related
-
2018
- 2018-12-12 WO PCT/EP2018/084462 patent/WO2019115578A1/fr unknown
- 2018-12-12 CN CN201880079927.5A patent/CN111448366B/zh active Active
- 2018-12-12 US US16/770,856 patent/US11156108B2/en active Active
- 2018-12-12 EP EP18829759.2A patent/EP3724454B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
FR3074839A1 (fr) | 2019-06-14 |
EP3724454B1 (fr) | 2022-02-16 |
CN111448366A (zh) | 2020-07-24 |
US11156108B2 (en) | 2021-10-26 |
FR3074839B1 (fr) | 2019-11-08 |
WO2019115578A1 (fr) | 2019-06-20 |
US20200392855A1 (en) | 2020-12-17 |
CN111448366B (zh) | 2022-09-16 |
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