EP2478186B1 - Rotor de turbomachine - Google Patents

Rotor de turbomachine Download PDF

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Publication number
EP2478186B1
EP2478186B1 EP10726886.4A EP10726886A EP2478186B1 EP 2478186 B1 EP2478186 B1 EP 2478186B1 EP 10726886 A EP10726886 A EP 10726886A EP 2478186 B1 EP2478186 B1 EP 2478186B1
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EP
European Patent Office
Prior art keywords
coupling element
radially
element segment
area
radially outside
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.)
Not-in-force
Application number
EP10726886.4A
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German (de)
English (en)
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EP2478186A1 (fr
Inventor
Tilmann Raible
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.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
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Publication date
Application filed by MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2478186A1 publication Critical patent/EP2478186A1/fr
Application granted granted Critical
Publication of EP2478186B1 publication Critical patent/EP2478186B1/fr
Not-in-force legal-status Critical Current
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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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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

Definitions

  • the invention relates to a rotor of a turbomachine according to the preamble of claim 1.
  • a rotor of a turbomachine in particular a gas turbine or steam turbine, has a rotor base body and a plurality of rotor blades which are fastened to the rotor base body.
  • the blades of such a turbomachinery rotor have a blade root and an airfoil, each blade being attached to the rotor body via its blade root and each blade having at least one coupler segment in the region of its blade which, when positioned radially outwardly of the airfoil, acts as Outside cover band segment is formed.
  • the coupling element segments, in particular outer shroud segments, of all the moving blades of such a turbomachine rotor together form at least one coupling element closed in the circumferential direction, in particular an outer shroud, of the rotor.
  • a width of a coupling element segment, in particular an outer shroud segment, of each blade is defined by edges extending substantially in the axial direction.
  • a depth in the axial direction of the coupling element segment, in particular the outer shroud segment, of each blade is defined by substantially circumferentially extending edges.
  • a coupling element segment, in particular an outer shroud segment, each blade is also characterized by a thickness in the radial direction.
  • Turbomachine rotors whose rotor blades have such coupling element segments for forming at least one coupling element can be installed both in the region of a compressor and in the region of a turbine of the turbomachine.
  • Turbomachinery rotors, on the rotor base body of which rotor blades are fastened, which have a coupling element segment formed radially on the outside of the airfoil as an outer cover band segment, are for example made DE 1 159 965 C , out DE 40 15 206 C1 as well as out US 4,400,915 A out GB 2 072 760 A and out GB 2 139 295 A known.
  • the coupling elements of such turbomachinery rotors designed as outer shrouds are exposed to high loads during operation, since they rotate with respect to a rotational axis of the turbomachine rotor to a maximum radius and are therefore exposed to high centrifugal forces.
  • corners or edges of the coupling element segments of the blades can bend outwards, which on the one hand in the coupling element voltage spikes are caused and on the other hand, a desired contact between adjacent coupling element segments adjacent blades is reduced to a punctiform contact or disappears completely.
  • a desired coupling between adjacent coupling element segments is reduced or eliminated, which ultimately worsens the vibration behavior of the turbomachine rotor.
  • the present invention is based on the problem to provide a rotor of a turbomachine, in which a good coupling of the coupling element segments of the blades is ensured during operation.
  • This problem is solved by a rotor according to claim 1.
  • the or each coupling element segment of each blade on a first side, on which a coupling element segment of a first, immediately adjacent blade follows in the circumferential direction is contoured in such a way that the flow inlet side adjacent to a flow inlet edge of the blade of the respective blade extending in the axial direction extending radially outer edge of the respective coupling element segment relative to the substantially axially extending radially inner edge of the respective coupling element segment in the circumferential direction, whereas on this first side flow exit side facing away from a flow outlet edge of the airfoil of the respective blade extending in the axial direction substantially extending radially inner edge against the substantially axially extending radially outer edge before TEHT.
  • the or each coupling element segment of each blade at one of the first side opposite second side, on the circumferentially seen a coupling element segment of a second immediately adjacent blade connects, so contoured that the flow outlet side adjacent to the flow edge of the blade of the respective blade itself extending in the axial direction extending radially outer edge of the respective coupling element segment relative to the substantially axially extending radially inner edge of the respective coupling element in the circumferential direction, whereas facing away from the flow inlet edge of the airfoil of the respective blade in the axial direction in this second side flow inlet side extending radially inner edge opposite to the substantially axially extending radially outer edge protrudes.
  • the contouring of the coupling element segments of the rotor blades at the edges extending essentially in the axial direction ensures optimal support and thus coupling of the coupling element segments forming the or each coupling element.
  • voltage peaks in the or each coupling element of the rotor can be significantly reduced during operation.
  • the natural frequency behavior and thus vibration behavior of the rotor according to the invention can be improved.
  • the radially outer edge extending substantially in the axial direction and the radially inner edge of the respective coupling element segment extending substantially in the axial direction each delimit two surfaces separated from each other by a turning point-free parting line, namely one in the viewing direction radially outwardly hidden surface and each visible in the direction of radially outward surface, wherein on the first side of the radially outwardly hidden surface flow inlet side and the radially outwardly visible surface is positioned on the flow exit side, and wherein on the second side of the radially outwardly hidden Surface flow outlet side and the radially outwardly visible surface is positioned on the flow inlet side, and wherein on the first side and on the second side of the respective coupling element segment in the viewing direction along the respective Wendddlingfre
  • the dividing line is seen from the surface concealed from radially outside the radial direction is inclined by a first angle and the surface visible from the radial outside with respect to the radial direction by
  • the radially outer edge extending essentially in the axial direction and the radially inner edge extending essentially in the axial direction are congruent at only one axial position , Also by this feature can be ensured while ensuring optimum coupling of the coupling element segments easy manufacturability of the blades of the rotor according to the invention.
  • the present invention relates to a rotor of a turbomachine, in particular a rotor of a compressor or a turbine of a turbomachine designed as a gas turbine or steam turbine.
  • the invention is not limited to these applications, but the invention can be used in all turbomachinery rotors.
  • a rotor of a turbomachine basically has a rotor main body and a plurality of rotor blades, which are fastened to the rotor base body via blade feet.
  • Fig. 1 to 8 the rotor body and the blade roots of blades are not shown, as these details are familiar to those skilled in the art.
  • FIG. 1 to 6 show different views of a detail of a rotor according to the invention of a turbomachine according to a first embodiment of the invention, wherein in Fig. 1 to 6 each different views of a designed as outer shroud segment coupling element segment 10 are shown.
  • the outer shroud segment 10 is as best as possible 4 to 6 can be removed, is associated with a radially outer end of a blade 11 of a blade.
  • the airfoil 11 has a flow inlet edge 12, a flow outlet edge 13 and a suction side 14 and pressure side 15 extending between the flow inlet edge 12 and the flow outlet edge 13.
  • Fig. 1, 2, 3 and 4 are indicated by arrows a radial direction R, a circumferential direction U and an axial direction A of the outer shroud segment 10 and the blade 11 and thus a blade and a rotor of a turbomachine according to the invention.
  • the outer shroud segment 10 assigned radially to the outer airfoil 11 has a width in the circumferential direction U which is defined by edges extending essentially in the axial direction A.
  • a radially outer edge 18 or 19 extending essentially in the axial direction A and respectively a radially inner edge 20 or 21 extending essentially in the axial direction A extend.
  • the distance between this radially outer edge 18 or 19 and this radially inner edge 20 or 21 determined on the sides 16 and 17 in the radial direction R, the thickness of the outer shroud segment 10th
  • a depth in the axial direction A of the outer shroud segment 10 is defined by edges extending substantially in the circumferential direction U, namely again by radially outer edges 22 and 23 and radially inner edges 24 and 25, respectively, where edges 22 and 24 are flow inlet side Edges and at the edges 23 and 25 flow outlet side edges. Also, the distance between these edges determined in the radial direction R, the thickness of the outer shroud segment 10, namely the flow inlet side and the flow outlet side.
  • second side 17 of the outer shroud segment 10 to which an immediately adjacent second blade with its outer shroud segment, namely with a first side thereof, adjoins, the same is contoured such that the flow exit side adjacent to the flow outlet edge 13 of the blade 11, the extending in the axial direction A, radially outer edge 19 of the outer shroud segment 10 relative to the also extending substantially in the axial direction A, radially inner edge 21 protrudes in the circumferential direction U, whereas in this second side 17 facing away from the flow inlet edge 12, the flow inlet side substantially extending in the axial direction A, radially inner edge 21 opposite to the also extending substantially in the axial direction A, radially outer edge 19 in the circumferential direction U protrudes.
  • the radially outer edges 18 and 19 extending substantially in the axial direction A, together with the respective radially inner edges 20 and 21 also extending substantially in the axial direction A, delimit two each separated by a dividing line 26 and 27, respectively Areas, namely in each case one in the viewing direction of radially outwardly hidden surface 28 and 29 and in each case one seen in the viewing direction from radially outside surface 30 and 31st
  • the surface 28, which is concealed from the outside is positioned on the flow inlet side and the surface 30, which is visible from the radial outside, is positioned on the flow exit side.
  • the surface 29 which is concealed from the outside is positioned on the flow exit side and the surface 31 which is visible from the radial outside is positioned on the flow inlet side.
  • the dividing lines 26 and 27 which separate the surfaces 28 and 30 and the surfaces 29 and 31 from each other on the first side 16 and on the second side 17 are executed according to a preferred embodiment of the invention without turning points, wherein the same in the embodiment of Fig. 1 to 6 run straight. This allows a particularly simple production. Likewise, the substantially extending in the axial direction A edges 18, 19, 20 and 21 are executed without turning points.
  • dividing line 26 of the first side 16 is visible from radially outside, whereas the dividing line 27 of the second side 17 is hidden from the outside when viewed radially.
  • dividing lines 26 and 27 of the two sides 16, 17, starting from the flow inlet-side edges to flow-outlet-side edges, run in each case from radially outside to radially inside.
  • first side 16 of the outer shroud segment 10 and the opposite, second side 17 of the outer shroud segment 10 are seen in the viewing direction along the respective parting line 26 and 27 from the radially outer hidden surfaces 28 and 29 and the visible from radially outside surfaces 30th or 31 each with respect to the radial direction R inclined at an angle.
  • the surfaces 28 and 29, which are concealed radially from the outside are inclined by a first angle relative to the radial direction R and the surfaces 30 and 31, which are visible from the radially outside, are inclined by a second angle relative to the radial direction R.
  • first angle and the second angle are equal in magnitude, but have different signs. This is particularly advantageous in terms of manufacturing technology. In contrast to this, however, it is also possible for the first angle and the second angle to be different in magnitude on the first side 16 and on the second side 17, but in turn have different signs.
  • Fig. 1 can be removed, as viewed from radially outside both on the first side 16 and on the second side 17 of the outer shroud segment 10 extending substantially in the axial direction A, radially outer edge 18 and 19 and which are substantially in the axial direction A extending, radially inner edge 20 and 21 congruent only at an axial position. It is in the embodiment of Fig. 1 to 6 This axial position is positioned approximately in the middle between the flow inlet-side edges 22 and 24 and the flow outlet-side edges 23 and 25 of the outer shroud segment 10.
  • Fig. 7 to 9 can be removed, by corresponding inclination of the edges 18, 20 and 19, 21 in the region of the sides 16 and 17 relative to the axial direction A, this axial position at which the edges 18 and 20 and the edges 19 and 21 are congruent, even with respect to Center between the flow inlet-side edges 22, 24 and flow outlet-side edges 23, 25 of the outer shroud segment 10 are moved, wherein in Fig. 7 this axial position is positioned closer to the flow exit-side edges 23, 25. In contrast, it is also possible that this axial position is positioned closer to the flow inlet-side edges 22, 24.
  • Fig. 1 to 6 are formed in the region of the first side 16 and the second side 17 of the outer shroud segment 10, radially outwardly hidden surfaces 28 and 29 and radially visible from the outside surfaces 30 and 31 respectively formed as two-dimensionally contoured, flat surfaces.
  • Fig. 7 to 9 an embodiment of the present invention, in which these surfaces 28, 29, 30 and 31 are designed as three-dimensionally contoured, spatially radially curved surfaces.
  • Fig. 7 to 9 can be taken that substantially radially extending edges 32 which define the outer shroud segment 10 together with the edges 18, 19, 20, 21, 22, 23, 24 and 25, in contrast to the embodiment of the Fig. 1 to 6 not straight but radially curved contoured.
  • 10 to 12 show a third embodiment of the invention, in which additionally the radially outer edges 18 and 19 and the radially inner edges 20 and 21 which extend substantially in the axial direction A and define the width of the outer shroud segment 10 in the circumferential direction U, on both opposite sides 16 and 17, as well as the dividing lines 26, 27 each have a curved contour or a curved, but non-point-free course.
  • the embodiment of the 10 to 12 with the embodiment of Fig. 7 to 9 match, so that the same reference numerals are used for this embodiment for the same components and reference is made to the above statements.
  • FIG. 13 Another embodiment of the invention shows Fig. 13 in which the blade 11 of the rotor of the rotor according to the invention not only has a coupling element segment designed as an outer cover strip segment 10 but additionally also a coupling element segment designed as an inner coupling element segment 33.
  • the outer shroud segment 10 and the inner coupling element segment 33 of the embodiment of Fig. 13 are analogous to the outer shroud segment 10 of the embodiment of Fig. 1 to 6 educated.
  • the illustrated blade may have a plurality of radially spaced apart inner coupling element segments 33.
  • the rotor blade of a rotor according to the invention is not assigned an outer shroud segment 10 but exclusively at least one coupling element segment designed as an inner coupling element segment 33.
  • each inner coupling element segment 33 is preferably positioned at a radial position along the radial blade length of the respective airfoil 11, which corresponds to between 40% and 90%, in particular between 60% and 90%, of the radial blade length.
  • outer shroud segments 10 lie at a radial position along the radial blade length of the respective blade 11, which corresponds to 100% of the radial blade length.
  • FIGS. 14 to 17 Another embodiment of the invention show FIGS. 14 to 17 ,
  • the embodiment of FIGS. 14 to 17 corresponds substantially to the embodiment of Fig. 1 to 6 Therefore, to avoid unnecessary repetition for the same components same reference numerals are used and will be discussed below only on such details, by which the embodiment of the invention FIGS. 14 to 17 from the Fig. 1 to 6 different.
  • the dividing line 26 of the first side 16 as seen from radially outwardly concealed, whereas the dividing line 27 of the second side 17 is seen from radially outside visible.
  • Fig. 15, 16 and 17 The dividing lines 26 and 27 of the two sides 16, 17 run from radially inward to radially outward from flow-entry-side edges to flow-exit-side edges.
  • the embodiment of the FIGS. 14 to 17 with the embodiment of Fig. 1 to 6 match, so that reference is made to the above statements.
  • the invention allows for the operation of the rotor optimal coupling of coupling element segments 10, 33 adjacent blades.
  • the natural frequency behavior and thus vibration behavior of the rotor is positively influenced, in particular in the region of an outer cover band.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (16)

  1. Rotor d'une turbo machine, comportant un corps de base de rotor et plusieurs aubes mobiles, dans lequel chaque aube mobile présente un pied d'aube et une pale, dans lequel chaque aube mobile est fixée par l'intermédiaire de son pied d'aube au corps de base de rotor, dans lequel chaque aube mobile présente au niveau de sa pale au moins un segment d'élément de couplage, et dans lequel dans la direction circonférentielle une largeur de ou chaque segment d'élément de couplage de chaque pale présente une première face (16) et une deuxième face (17) qui sont définis respectivement par des arêtes extérieures radiales (18, 19) et des arêtes intérieures radiales (20, 21) s'étendant essentiellement dans la direction axiale, caractérisé en ce que dans le sens de visualisation radicalement à l'extérieur le ou chaque segment d'élément de couplage (10, 33) de chaque aube mobile sur la première face (16), auquel se rattache, vu dans la direction circonférentielle un segment d'élément de couplage d'une première aube mobile directement voisine, présente des contours tels que du côté d'entrée de flux à proximité d'une arrête d'entrée d'écoulement (12) de la pale de l'aube mobile respective, l'arête extérieure radiale s'étendant essentiellement dans la direction axiale (18) du segment d'élément de couplage respectif dépasse en saillie par rapport à l'arrête intérieure radiale s'étendant essentiellement dans la direction axiale (20) du segment d'élément de couplage respectif, alors que sur cette première face (16) du côté de sortie de flux se détournant d'une arrête de sortie de flux (13) de la pale de l'aube mobile respective l'arrête intérieure radiale s'étendant essentiellement dans la direction axiale (20) dépasse en saillie par rapport à l'arête extérieure radiale s'étendant essentiellement dans la direction axiale (18) dans la direction circonférentielle et en ce que le ou chaque segment d'élément de couplage (10, 33) de chaque aube mobile sur la deuxième face (17) opposés à la première face (16), auquel se rattache dans la direction circonférentielle un segment d'élément de couplage d'une deuxième aube mobile directement voisine, présentent des contours tels que du côté de sortie de flux à proximité de l'arête de sortie de flux (13) de la pale mobile respective l'arête extérieure radiale s'étendant essentiellement dans la direction axiale (19) du segment d'élément de couplage dépasse en saillie par rapport à l'arrête intérieure radiale s'étendant essentiellement dans la direction axiale (21) du segment d'élément de couplage respectif dans la direction circonférentielle, alors que sur cette deuxième face (17) du côté d'entrée de flux se détournant de l'arrête d'entrée de flux (12) de la pale de l'aube mobile respective l'arrête intérieure radiale s'étendant essentiellement dans la direction axiale (21) dépasse en saillie par rapport à l'arrête extérieure radiale s'étendant essentiellement dans la direction axiale (19) dans la direction circonférentielle.
  2. Rotor selon la revendication 1, caractérisée en ce que sur la première face (16) et sur la deuxième face (17) l'arête extérieure radiale s'étendant essentiellement dans la direction axiale (18, 19) et l'arrête intérieure radiale s'étendant essentiellement dans la direction axiale (20, 21) du segment d'élément de couplage respectif délimitent respectivement deux surfaces séparées l'une de l'autre par une ligne de séparation (26, 27), à savoir respectivement une surface couverte radialement de l'extérieur dans le sens de visualisation (28, 29) et respectivement une surface visible radialement de l'extérieur dans le sens de visualisation (30, 31), dans lequel sur la première face (16) la surface couverte radialement de l'extérieur (28) est positionnée du côté d'entrée de flux et la surface visible radialement de l'extérieur (30) est positionnée du côté de sortie de flux et dans lequel sur la deuxième face (17) la surface couverte radialement de l'extérieur (29) est positionnée du côté de sortie de flux et la surface visible radialement de l'extérieur (31) est positionnée du côté d'entrée de flux.
  3. Rotor selon la revendication 2, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) les lignes de séparation (26, 27), qui séparent l'une de l'autre sur la première face (16) et sur la deuxième face (17) la surface couverte radialement de l'extérieur (28, 29) et la surface visible radialement de l'extérieur (30, 31), sont conçues sans tournant.
  4. Rotor selon la revendication 2 ou 3, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) du segment d'élément de couplage respectif vu dans le sens de visualisation le long des lignes de séparation (26, 27) la surface couverte radialement de l'extérieur (28, 29) est inclinée par rapport à la direction radiale d'un premier angle et la surface visible radialement de l'extérieur (30, 31) est inclinée par rapport à la direction radiale d'un deuxième angle.
  5. Rotor selon la revendication 4, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) du segment d'élément de couplage respectif le premier angle et le deuxième angle sont proportionnellement de même grandeur et présentent des signes différents.
  6. Rotor selon la revendication 4, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) du segment d'élément de couplage respectif le premier angle et le deuxième angle sont proportionnellement de grandeur différente et présentent des signes différents.
  7. Rotor selon une des revendications 2 à 6, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) du segment d'élément de couplage respectif la surface couverte radialement de l'extérieur (28, 29) et la surface visible radialement de l'extérieur (30, 31) sont de même grandeur et présentent donc un rapport de surface de 1 :1.
  8. Rotor selon une des revendications 2 à 6, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) du segment d'élément de couplage respectif la surface couverte radialement de l'extérieur (28, 29) et la surface visible radialement de l'extérieur (30, 31) sont de grandeur différente.
  9. Rotor selon la revendication 8, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) la surface couverte radialement de l'extérieur (28, 29) et la surface visible radialement de l'extérieur (30, 31) présentent un rapport de surface allant jusqu'à 1:5 ou allant jusqu'à 5:1, notamment un rapport de surface allant jusqu'à 1 :3 ou allant jusqu'à 3:1.
  10. Rotor selon une des revendications 2 à 9, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) du segment d'élément de couplage respectif la surface couverte radialement de l'extérieur (28, 29) et la surface visible radialement de l'extérieur (30, 31) sont respectivement des surfaces plates, à contours en deux dimensions.
  11. Rotor selon une des revendications 2 à 10, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) du segment d'élément de couplage respectif la surface couverte radialement de l'extérieur (28, 29) et la surface visible radialement de l'extérieur (30, 31) sont respectivement des surfaces incurvées spatialement, à contours en trois dimensions.
  12. Rotor selon une des revendications 2 à 11, caractérisé en ce sur la première face (16) et sur la deuxième face (17) du segment d'élément de couplage respectif dans le sens de visualisation radialement de l'extérieur l'arête extérieure radiale s'étendant essentiellement dans la direction axiale (18, 19) et l'arrête intérieure radiale s'étendant essentiellement dans la direction radiale (20, 21) se recouvrent réciproquement exclusivement à une position axiale.
  13. Rotor selon la revendication 12, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) cette position axiale est positionnée au centre entre les arêtes du côté d'entrée d'écoulement (22, 24) et les arêtes du côté de sortie d'écoulement (23, 25) du segment d'élément de couplage (10, 33).
  14. Rotor selon la revendication 12, caractérisé en ce que sur la première face (16) et sur la deuxième face (17) cette position axiale est positionnée plus près des arêtes du côté d'entrée d'écoulement (22, 24) ou plus près des arêtes du côté de sortie d'écoulement (23, 25) du segment d'élément de couplage (10, 33).
  15. Rotor selon une des revendications 1 à 14, caractérisé en ce que chaque aube mobile présente au niveau de sa pale radialement à l'extérieur un segment d'élément de couplage (10) conçu comme un segment de bande de couverture extérieure.
  16. Rotor selon des revendications 1 à 15, caractérisé en ce que chaque aube mobile présente au niveau de sa pale au moins un segment d'élément de couplage (33) conçu comme un segment d'élément de couplage intérieur.
EP10726886.4A 2009-09-18 2010-05-25 Rotor de turbomachine Not-in-force EP2478186B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009029587A DE102009029587A1 (de) 2009-09-18 2009-09-18 Rotor einer Turbomaschine
PCT/DE2010/050029 WO2011032548A1 (fr) 2009-09-18 2010-05-25 Rotor de turbomachine

Publications (2)

Publication Number Publication Date
EP2478186A1 EP2478186A1 (fr) 2012-07-25
EP2478186B1 true EP2478186B1 (fr) 2015-07-29

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EP10726886.4A Not-in-force EP2478186B1 (fr) 2009-09-18 2010-05-25 Rotor de turbomachine

Country Status (6)

Country Link
US (1) US9127562B2 (fr)
EP (1) EP2478186B1 (fr)
JP (1) JP5314194B2 (fr)
CN (1) CN102597426B (fr)
DE (1) DE102009029587A1 (fr)
WO (1) WO2011032548A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010031213A1 (de) * 2010-07-12 2012-01-12 Man Diesel & Turbo Se Rotor einer Turbomaschine
US10465531B2 (en) 2013-02-21 2019-11-05 General Electric Company Turbine blade tip shroud and mid-span snubber with compound contact angle
EP3039249B8 (fr) 2013-08-30 2021-04-07 Raytheon Technologies Corporation Surfaces de face d'accouplement ayant une certaine géométrie sur un appareil de turbomachine
EP2918784A1 (fr) * 2014-03-13 2015-09-16 Siemens Aktiengesellschaft Pied d'aube pour une aube de turbine
EP2963245A1 (fr) * 2014-07-03 2016-01-06 Siemens Aktiengesellschaft Accouplement intermittent d'aubes mobiles disposées de façon adjacente
DE102014014287A1 (de) * 2014-09-24 2016-03-24 Ziehl-Abegg Se Lüfterrad
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WO2011032548A1 (fr) 2011-03-24
US9127562B2 (en) 2015-09-08
JP2013505385A (ja) 2013-02-14
JP5314194B2 (ja) 2013-10-16
CN102597426B (zh) 2014-09-17
DE102009029587A1 (de) 2011-03-24
CN102597426A (zh) 2012-07-18
EP2478186A1 (fr) 2012-07-25
US20120230826A1 (en) 2012-09-13

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