EP2818639B1 - Aube rotorique de turbomachine et turbomachine associée - Google Patents

Aube rotorique de turbomachine et turbomachine associée Download PDF

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Publication number
EP2818639B1
EP2818639B1 EP13174031.8A EP13174031A EP2818639B1 EP 2818639 B1 EP2818639 B1 EP 2818639B1 EP 13174031 A EP13174031 A EP 13174031A EP 2818639 B1 EP2818639 B1 EP 2818639B1
Authority
EP
European Patent Office
Prior art keywords
rotor blade
blade
pockets
pocket
walls
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
EP13174031.8A
Other languages
German (de)
English (en)
Other versions
EP2818639A1 (fr
Inventor
Krzysztof Skura
Marcin Kozdras
Lukasz Sosnowka
Manfred Feldmann
Manfred Schill
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to PL13174031T priority Critical patent/PL2818639T3/pl
Priority to ES13174031T priority patent/ES2718127T3/es
Priority to EP13174031.8A priority patent/EP2818639B1/fr
Priority to US14/316,035 priority patent/US9951631B2/en
Publication of EP2818639A1 publication Critical patent/EP2818639A1/fr
Application granted granted Critical
Publication of EP2818639B1 publication Critical patent/EP2818639B1/fr
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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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the present invention relates to a blade for a turbomachine and a turbomachine, in particular a gas turbine, with such a blade.
  • a blade for a turbomachine with a flow deflecting blade a blade root for attachment to a rotor of the turbomachine, an inner platform between the blade and the blade root, and a pocket defined by two axially spaced walls extending away from the blade Side of the platform to the blade root out.
  • These walls are offset with respect to a blade root edge in the direction of a radial longitudinal axis in order to improve the mechanical stress.
  • the pocket-facing outer sides of these walls are circumferentially parallel.
  • a blade having a circumferentially inwardly tapered pocket between an inner platform and a blade root is known to improve mechanical stress.
  • the pocket-facing outer sides are also circumferentially parallel.
  • blades are from the documents GB1062170A .
  • EP2586967A2 known.
  • a blade according to the preamble of claim 1 is in the document US5924699A disclosed.
  • An object of an embodiment of the present invention is to provide an improved turbomachine.
  • a blade for a turbomachine includes a flow deflecting blade having a pressure side, a suction side, leading and trailing edges (with respect to a flow direction in operation of the turbomachine).
  • a blade root for fastening the blade to a rotor of the turbomachine is connected to the blade leaf, in particular integrally or integrally.
  • the blade root can in particular be designed as a so-called fir tree root and have one or more ribs, which engage behind respective undercuts of a groove in the rotor and thus fix the rotor blade, in particular radially, on the rotor.
  • a (in the mounted state radially inner) platform which defines a flow channel for a working medium of the turbomachine radially inward.
  • Directional data such as axial, radial and circumferential direction generally relate in particular to the mounting position of the blade in the turbomachine.
  • the inner platform has one or two opposing axial flanges to form a labyrinth seal with adjacent baffles.
  • a pocket is arranged on both circumferentially opposite sides of the blade. At least one of them is defined in the axial direction by two axially spaced walls, which extend from the blade side facing away from the platform to the blade root and radially inward and are referred to below for compact representation as the first and second wall.
  • the first wall may be an upstream or downstream wall (relative to a flow direction during operation of the turbomachine).
  • the bag is in one embodiment in the circumferential direction on one side open or blind hole-like design, with a common Between wall in the circumferential direction opposite pockets of a blade from one another can limit or limit.
  • Mutually facing pockets of adjacent blades, particularly the faces of their first and second walls and inner platforms, may contact one another in an embodiment such that their walls have two, at least substantially, closed, axially spaced sealing rings or flanges between the rotor and the inner Form platform ring.
  • At least the first wall of one or two opposing pockets of the blade each have a pocket-facing outer surface or surface, in one or more, preferably - at least substantially - all cross-sections perpendicular to a radial longitudinal axis of the blade in Viewed circumferential direction of the blade away from the outside or away from the bag.
  • the outer side of the first wall diverges as it progresses in the circumferential direction on an adjacent blade or on an end face of the pocket or wall in the circumferential direction in the axial direction. Accordingly, the outer side converges or tapers from an end face of the first wall in the circumferential direction onto the blade towards axially inward direction or towards the pocket.
  • the second, axially opposite wall can also have an outer side facing away from the pocket, which is inclined in one or more, preferably - at least substantially - all cross sections perpendicular to the radial longitudinal axis in the circumferential direction away from the blade outwardly or in progression in Circumferential direction diverges on an adjacent blade or on an end face of the pocket or wall in the circumferential direction in the axial direction.
  • the outer side of the second wall is, at least substantially, aligned in the circumferential direction or circumferentially parallel.
  • an advantageous Entformungsschräge at least substantially provided by the first wall, while the second walls form a, at least substantially, circumferentially parallel sealing ring.
  • the outer sides of the first walls can be inclined to one another in a V-like manner.
  • the outside of the first wall is, at least substantially, parallel to an inside or surface of the first wall. Additionally or alternatively, the outside of the second wall may be, at least substantially, parallel to the inside of the second wall. This can be particularly advantageous in terms of manufacturing and / or loading technology. Additionally or alternatively, in one embodiment, a material accumulation due to a Entformungsschräge be minimized.
  • the first and / or second wall can be seen in the radial direction to be arched axially towards the pocket, in particular parabolic, as shown in the DE 10 2009 007 664 A1 is explained.
  • the first wall is seen in the radial direction, in particular parabolic, arched axially to the bag, wherein its outer side facing away from the pocket in at least one cross section perpendicular to the radial longitudinal axis in a radially outer half and in at least one cross section perpendicular to the radial longitudinal axis in a radially inner Half is inclined in each case outwards or diverges to an open end side of the pocket in the circumferential direction in the axial direction.
  • An outwardly inclined outer side may, in at least one cross-section perpendicular to the radial longitudinal axis of the blade, in particular uniform, be curved, preferably strictly concave.
  • an outwardly inclined outside in at least one cross section perpendicular to the radial longitudinal axis of the blade at least substantially, be straight.
  • a tangential plane to the outside in at least one cross section perpendicular to the radial longitudinal axis of the blade with the circumferential direction forms an angle which is at least 5 °, in particular at least 10 °, and / or at most 45 °, in particular at most 30 °.
  • At least the pocket in a further development also the blade leaf integrally formed therewith and / or the blade root integrally formed therewith, is formed in a particular way cast, and / or formed, in particular forged. Due to the inclined outer side (s), demoulding slopes for demolding the pocket from a casting mold or for executing a forming tool can be represented in one embodiment with a reduced material accumulation.
  • a blade according to the invention is used in a turbine or compressor stage of a gas turbine, in particular of an aircraft engine.
  • a turbomachine in particular a gas turbine, preferably an aircraft engine, according to one aspect of the present invention, a rotor and one or more of the above-described blades, which are fixed by means of their blade roots on the rotor, in particular form-fitting and / or releasably.
  • Fig. 1 shows a part of a rotor of a gas turbine according to an embodiment of the present invention in perspective view
  • Fig. 2 a section perpendicular to a radial longitudinal axis of the blade.
  • the blade has an airfoil 1, to which a blade root 2 is connected, which is designed as a so-called fir tree root.
  • an inner platform 3 is arranged, which has two opposite axial flanges, of which in the Fig. 1, 2 only one flange 3.1 can be seen.
  • a pocket 4 and 5 is arranged on both circumferentially opposite sides (top, bottom in Fig. 2 ) of the blade. This is in each case in the axial direction (horizontal in Fig. 2 ) are defined by a first wall 4.1 and 5.1, respectively, and a second wall 4.2 or 5.2 axially spaced therefrom, which faces away from the blade side (at the bottom in FIG Fig. 1 ) of the platform 3 to the blade root 2 and extend radially inward. In the radial direction bounded outside (top in Fig.
  • the pocket 4 or 5 is open on one side in the circumferential direction, wherein a common partition wall 45 delimits the two circumferentially opposite pockets 4, 5 from each other.
  • the first walls 4.1, 5.1 each have a pocket facing away (right in Fig. 2 ) Outside 4.1A and 5.1A, in particular in the cross section of Fig. 2 is inclined outwards, ie viewed in the circumferential direction on an open end side of the pocket axially diverged away from the pocket.
  • the in Fig. 2 bottom outside 4.1A diverges in the illustrated cross-section from top to bottom viewed to the right
  • the in Fig. 2 upper outer side 5.1A diverges from bottom to top, looking to the right.
  • the outside 4.1A converges from the front side (bottom in FIG Fig. 2 ) of the first wall 4.1 viewed in the circumferential direction (upwards in Fig.
  • the outside 5.1A converges from the end face (top in FIG Fig. 2 ) of the first wall 5.1 viewed in the circumferential direction (down in Fig. 2 ) to the blade 1 to.
  • the outsides 4.1A, 5.1A of the first walls 4.1, 5.1 are V-like inclined to each other.
  • the outer sides 4.2A, 5.2A of the second walls 4.2, 5.2 are, however, in the circumferential direction (vertically in Fig. 2 ).
  • the outer sides 4.1A, 5.1A of the first walls 4.1, 5.1 are parallel to the pocket-facing inner sides 4.1B and 5.1B of the first walls 4.1 and 5.1, respectively.
  • the outer sides 4.2A, 5.2A of the second walls 4.2, 5.2 parallel to the inner sides 4.2B and 5.2B of the second walls 4.2 and 5.2, so that the first and second walls in the circumferential direction have constant wall thicknesses.
  • the first and second walls 4.1, 5.1 and 4.2, 5.2 of the two opposite pockets 4, 5 are seen in the radial direction (vertically in Fig. 1 ) arched parabolic to the bag.
  • the pocket-facing outer side 4.1A or 5.1A of the first wall 4.1 or 5.1 of the pocket 4 or 5 is in cross-sections perpendicular to the radial longitudinal axis in a radially outer (top in Fig. 1 ) Half, like Fig. 2 one, and also in cross-sections perpendicular to the radial longitudinal axis in a radially inner (bottom in Fig. 1 ) Half each outwardly inclined.
  • the outer sides 4.1A, 5.1A due to the parabolic curvature as well as the parallel thereto inner sides 4.1B and 5.1B are substantially circumferentially parallel.
  • the pocket-facing outer sides 4.1A, 5.1A which are inclined away from the pocket, are straight in substantially all cross-sections perpendicular to the radial longitudinal axis of the blade.
  • the outsides 4.1A, 5.1A of the two pockets 4, 5 go in the execution of Fig. 1, 2 in a radius into one another, which is arranged at the height of the intermediate wall 45.

Landscapes

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

Claims (8)

  1. Aube rotorique de turbomachine, comprenant une pale (1) pour la déviation de l'écoulement, un pied d'aube (2) destiné à être fixé sur un rotor de la turbomachine, une plate-forme intérieure (3) située entre la pale et le pied d'aube, ainsi qu'une première et une seconde poches (4, 5) disposées sur des côtés circonférentiellement opposés, de l'aube rotorique, une première des poches (4, 5) étant définie par deux parois (4.1, 4.2 ; 5.1, 5.2), qui s'étendent depuis le côté de la plate-forme, distant de la pale, jusqu'au pied d'aube et sont espacées l'une de l'autre dans le sens axial, une première (4.1, 5.1) de ces parois ayant un côté extérieur (4.1A, 5.1A) distant de la poche, qui est incliné, dans au moins une section, vers l'extérieur, perpendiculairement à un axe longitudinal radial de l'aube rotorique, de telle sorte que le côté extérieur (4.1A, 5.1A) de la première paroi (4.1, 5.1) diverge dans la direction axiale à mesure qu'il s'éloigne circonférentiellement de l'aube rotorique (α), caractérisé en ce que ledit côté extérieur (4.1A, 5.1A) distant de la poche est au moins sensiblement parallèle à un côté intérieur (4.1B, 4.2B, 5.1B, 5.2B), faisant face à la poche, de la première (4.1, 5.1) de ces parois.
  2. Aube rotorique selon la revendication 1, caractérisée en ce qu'une seconde (4.2, 5.2) de ces parois présente un côté extérieur (4.2A, 5.2A) distant de la poche, qui est au moins sensiblement aligné circonférentiellement.
  3. Aube rotorique selon la revendication 1, caractérisée en ce qu'une seconde de ces parois présente un côté extérieur (4.2A, 5.2A) distant de la poche, qui est incliné, dans au moins une section, vers l'extérieur, perpendiculairement à un axe longitudinal radial de l'aube rotorique.
  4. Aube rotorique selon l'une des revendications précédentes caractérisée en ce qu'au moins un côté extérieur (4.1A, 5.1A, 4.2A, 5.2A) distant de la poche, qui est incliné, dans au moins une section, vers l'extérieur, perpendiculairement à un axe longitudinal radial de l'aube rotorique, est incurvé ou, au moins sensiblement, droit.
  5. Aube rotorique selon l'une des revendications précédentes, caractérisée en ce que la première et/ou la seconde paroi (4.1, 4.2, 5.1, 5.2), vue dans la direction radiale, est bombée axialement vers la première poche.
  6. Aube rotorique selon l'une des revendications précédentes, caractérisée en ce que la première poche subit un façonnement primaire, est notamment coulée, et/ou est transformée, notamment forgée.
  7. Aube rotorique selon l'une des revendications précédentes, caractérisée en ce que l'autre seconde poche (5) circonférentiellement opposée est définie par deux autres parois (5.1, 5.2) axialement espacées l'une de l'autre, lesquelles parois s'étendent depuis le côté de la plateforme, distant de la pale, jusqu'au pied d'aube, au moins une première (5.1) de ces parois supplémentaires ayant un côté extérieur (5.1A) supplémentaire distant de la poche, qui est incliné, dans au moins une section, vers l'extérieur, perpendiculairement à un axe longitudinal radial de l'aube rotorique.
  8. Turbomachine, notamment turbine à gaz, comprenant un rotor et au moins une aube rotorique selon l'une des revendications précédentes, et qui est fixée au rotor, en particulier par complémentarité de forme et/ou de manière amovible.
EP13174031.8A 2013-06-27 2013-06-27 Aube rotorique de turbomachine et turbomachine associée Active EP2818639B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
PL13174031T PL2818639T3 (pl) 2013-06-27 2013-06-27 Łopata maszyny wirnikowej i przynależna maszyna wirnikowa
ES13174031T ES2718127T3 (es) 2013-06-27 2013-06-27 Pala de rotor de turbomáquina y turbomáquina respectiva
EP13174031.8A EP2818639B1 (fr) 2013-06-27 2013-06-27 Aube rotorique de turbomachine et turbomachine associée
US14/316,035 US9951631B2 (en) 2013-06-27 2014-06-26 Turbomachine rotor blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13174031.8A EP2818639B1 (fr) 2013-06-27 2013-06-27 Aube rotorique de turbomachine et turbomachine associée

Publications (2)

Publication Number Publication Date
EP2818639A1 EP2818639A1 (fr) 2014-12-31
EP2818639B1 true EP2818639B1 (fr) 2019-03-13

Family

ID=48808153

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13174031.8A Active EP2818639B1 (fr) 2013-06-27 2013-06-27 Aube rotorique de turbomachine et turbomachine associée

Country Status (4)

Country Link
US (1) US9951631B2 (fr)
EP (1) EP2818639B1 (fr)
ES (1) ES2718127T3 (fr)
PL (1) PL2818639T3 (fr)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1062170A (en) * 1965-08-20 1967-03-15 Gen Electric Turbomachine cooling system
US4497613A (en) * 1983-01-26 1985-02-05 General Electric Company Tapered core exit for gas turbine bucket
US4595340A (en) 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
US7547192B2 (en) * 2005-02-25 2009-06-16 General Electric Company Torque-tuned, integrally-covered bucket and related method
US7549846B2 (en) * 2005-08-03 2009-06-23 United Technologies Corporation Turbine blades
DE102009007664A1 (de) 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine
US9045992B2 (en) * 2010-06-28 2015-06-02 Herakles Turbomachine blades or vanes having complementary even/odd geometry
US9366142B2 (en) * 2011-10-28 2016-06-14 General Electric Company Thermal plug for turbine bucket shank cavity and related method
US9366151B2 (en) * 2012-05-07 2016-06-14 General Electric Company System and method for covering a blade mounting region of turbine blades

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal

Also Published As

Publication number Publication date
US20150003988A1 (en) 2015-01-01
PL2818639T3 (pl) 2020-01-31
EP2818639A1 (fr) 2014-12-31
ES2718127T3 (es) 2019-06-27
US9951631B2 (en) 2018-04-24

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