EP3183430B1 - Aube mobile de turbine - Google Patents

Aube mobile de turbine Download PDF

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Publication number
EP3183430B1
EP3183430B1 EP15787931.3A EP15787931A EP3183430B1 EP 3183430 B1 EP3183430 B1 EP 3183430B1 EP 15787931 A EP15787931 A EP 15787931A EP 3183430 B1 EP3183430 B1 EP 3183430B1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine rotor
rotor blade
flute
turbine
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
EP15787931.3A
Other languages
German (de)
English (en)
Other versions
EP3183430A1 (fr
Inventor
Fathi Ahmad
Radan RADULOVIC
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.)
Siemens AG
Original Assignee
Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP3183430A1 publication Critical patent/EP3183430A1/fr
Application granted granted Critical
Publication of EP3183430B1 publication Critical patent/EP3183430B1/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
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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 invention relates to a turbine blade in which along an imaginary blade longitudinal axis of the turbine blade from bottom to top of a blade root for attachment of the turbine blade on a rotor of the turbine, a transition region and an adjoining aerodynamically curved blade follows, wherein the blade root two opposing planar faces and two opposing, the two end faces interconnected contoured side surfaces, in which side surfaces to form a dovetail or fir-tree-shaped end surface contour in each case at least one support flank is formed and in which the support flanks pass over concave fillets in the transition region or free flanks.
  • the turbine blade described above is well known in the art and is particularly used in gas turbines.
  • the latter For fastening the turbine blade to the rotor, the latter either has a circumferential shaft collar or a rotor disk, on whose outer circumference largely retaining grooves extending in the axial direction are provided.
  • the retaining grooves are distributed along the circumference of the shaft collar or the rotor disk, so that a dedicated retaining groove is provided for each turbine blade.
  • the retaining grooves are shaped accordingly to the end contour of the blade root of the turbine blade, so that overall a positive connection between the turbine blade and rotor is present, which holds the turbine blade securely on the rotor during normal operation of a turbine blade having the turbine blade, regardless of the forces acting on the turbine blade centrifugal forces ,
  • the object of the invention is therefore to provide a turbine blade whose use in a blade carrier extends the life of the turbine blade carrier.
  • the object directed to the invention is achieved by a turbine blade according to claim 1.
  • the invention is based on the finding that the centrifugal force load caused by the turbine blade in the blade carrier varies in size along the length of the retaining nut. It has been found that at the - with respect to a flow direction of the working medium of the turbine - upstream and downstream end portions of the blade carrier stress concentrations occur that affect the predeterminable life of the blade carrier. For this reason, it is to extend the life of the blade carrier, for example. A rotor disc, helpful to reduce the voltages occurring there.
  • the turbine blade root along the Tragflankenerstreckung (from one of the two end faces of the blade root to the other of the two end faces) is designed to be different stiff.
  • the different stiffnesses are achieved in that at least two grooves according to claim 1 are provided in the region of the concave rounding.
  • the arrangement of the grooves in the region of the concave rounding reduces the load-bearing cross-section of the blade root present at this point. As such, the blade root becomes softer at this point compared to the stiffness of the blade root midway between the two opposing planar faces.
  • the groove has an edge contour with a tapered end, which shows said end to the opposite side wall.
  • At least two grooves are provided, of which one of the two recesses adjacent to the upstream end face and at the same time provided on the pressure-side side surface of the blade root and the other of the two grooves is arranged on the downstream end face and at the same time on the suction side side surface of the blade root.
  • the grooves are diagonally opposite each other.
  • This embodiment takes into account the fact that on the blade and flow forces act, through which the turbine blade experiences a torque, which Torque must be absorbed and compensated by the material of the blade carrier surrounding the retaining grooves.
  • the length of the extension of the recess is not more than 10%, preferably not more than 5% of said distance. It has been found that even a comparatively small recess can lead to a significant equalization of the loads in the material of the blade carrier.
  • each side surface of the blade root has at least two support flanks and thus the blade root provides a fir-tree-shaped end surface contour, wherein the groove is arranged above that supporting flank which, due to the coordination of the dimensions of the turbine blade root and the corresponding retaining groove of the blade carrier, is the largest should experience mechanical stress under centrifugal force. Since this is often the lowest arranged supporting flank, the groove is expediently arranged above the lowermost arranged supporting flank.
  • each support flank is arranged above each support flank.
  • downstream groove in the axial direction is made longer than the further upstream groove, as it has been found that in the downstream side, the loads caused by the flow forces are greater than on the upstream side.
  • the invention relates to a turbine blade for a thermal turbomachine, in which along a imaginary blade longitudinal axis of the turbine blade from bottom to top - specifically from a mounting side blade end to the opposite blade tip end blade other - a blade root for attachment of the turbine blade on a rotor of the turbine a transition region and an adjoining aerodynamically curved blade follows, the blade root two opposite each other planar end faces and two opposing, the two end faces interconnected contoured side surfaces, in which side surfaces to form a dovetail or fir-tree-shaped end surface contour in each case at least one support flank and a free flank is formed, and wherein the support flanks via concave fillets in the transition region or to pass over the free flanks.
  • the feature combination of the characterizing part of claim 1 is proposed.
  • FIG. 1 shows a perspective view of a turbine blade 10.
  • the turbine blade 10 includes along an imaginary longitudinal axis 12 from bottom to top a blade root 14, to which a transition region and an aerodynamically curved blade 18 connects thereto.
  • the blade 18 is aerodynamically curved in a known manner and comprises a leading edge 20 and an outflow edge 22, which are connected to each other via a pressure side wall 21 and a suction side wall 24.
  • the blade root 14 is designed dovetailed in the illustrated embodiment and thus comprises two flat end faces 26, 28 which are opposite to each other, of which one end face 26 upstream and the other end face 28 is arranged downstream.
  • the two end faces 26, 28 are connected to each other by means of two opposite side surfaces 30, 32, wherein in each case a support flank 34 and a free flank 35 is formed in the said side surfaces 30, 32, so that the contours of the end faces 26, 28 give a dovetail shape.
  • the support flanks 34 pass over a concave rounding 36 into the transition region 16, which on the one hand can comprise a blade neck and on the other hand a platform which can limit the flow path of the thermal turbomachine on the rotor side.
  • the mutually radially immediately adjacent support flank 34 and free flank 35 of the blade root 14 are connected to each other via a convex fillet and thus form a in the respective side surface 30, 32 arranged bead which extends from the upstream end surface 26 to the downstream end surface 28.
  • a groove 38 which adjoins the front side 26 is arranged, the extent of which is along the side surfaces 30 is smaller than that of the support flank 34 and the supporting surface (see FIG. 2 ) of the support flank 34 is reduced (compared to the respective support flank 34 without the groove adjacent thereto).
  • a turbine blade assembly 40 comprising a normally rotatable turbine blade carrier 42 having a plurality of retaining grooves 48 distributed uniformly along the periphery thereof and having the turbine blade 10 disposed there are less mechanical stresses. which prolongs the life of the turbine blade carrier 42.
  • FIG. 2 11 shows a section of the turbine blade assembly 40 in which a turbine blade carrier 42 is formed as a rotor disk that can be rotated about a machine axis 44. On the outer circumference 46 of the rotor disk 42 only one of the circumferentially U uniformly distributed retaining grooves 48 is shown for turbine blades, in which a turbine blade 10 is used. Due to the arranged in both side surfaces 30, 32 of the blade root 14 supporting flanks 34 and free flanks 35 results for the end face 26 of the blade root 14 a contour in the form of a Christmas tree.
  • the support flanks 34 are configured symmetrically to the imaginary longitudinal axis 12 of the turbine blade 10.
  • the groove 38 is arranged so that the distance F between the opposed concave fillets 36 and the groove 38 is reduced compared to the no-fill distance.
  • the groove 38 is designed such that the contact surface of the support flank 34 of the blade root 40 and the supporting flank 48 of the retaining groove 48 lying opposite it in the region of the flute 38 is reduced compared to that contact region in which no flute is provided.
  • FIG. 3 shows a plan view of the side surface 30 of the blade root 14 of the turbine blade 10.
  • the two flat end faces 26, 28 are opposite in a 100% normalized distance A, wherein the longitudinal extent of the groove 38 has a length L, measured from the end face 26 of which adjoins the groove 38 from, does not exceed an amount of 10%, preferably not more than 5% of the distance A.
  • it is 3%.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. Aube (10) mobile de turbine pour une turbomachine thermique,
    dans laquelle, le long d'un axe (12) longitudinal imaginaire de l'aube (10) mobile de turbine, de bas en haut, à une emplanture (14) d'aube, pour fixer l'aube (10) mobile de la turbine à un rotor de la turbine, fait suite une partie (16) de transition, ainsi qu'une lame d'aube à courbure aérodynamique s'y raccordant,
    la lame d'aube comprenant une paroi (21) d'intrados et une paroi (24) d'extrados, qui s'étendent, pour un fluide de travail d'un bord (20) d'attaque à un bord (22) de fuite, dans laquelle l'emplanture (14) de l'aube a deux surfaces (26, 28) frontales planes opposées l'une à l'autre et deux surfaces (30, 32) latérales à contour, opposées l'une à l'autre et reliant entre elles les deux surfaces frontales, au moins un flanc (34) portant étant constitué dans les surfaces (30, 32) latérales et dans laquelle les flancs (34) portant se transforment par des arrondis (36) concaves en la partie de transition ou en des flancs (35) libres, constitués sur les surfaces (30, 32) latérales, dans laquelle, dans au moins un arrondi (36) concave, est prévue une gorge (38), qui est voisine des deux côtés (26, 28) frontaux et dont l'étendue, le long de la surface frontale, est plus petite que celle du flanc portant, caractérisée en ce que le contour de bord de la gorge (38) a une extrémité en pointe, ladite extrémité pointant vers la paroi latérale opposée,
    en ce que les deux côtés (26, 28) frontaux sont en face à une distance normée de 100% et la longueur axiale de l'étendue de la gorge (38) ne représente pas plus de 10% de ladite distance (A) et
    en ce qu'il est prévu au moins deux gorges (38), dont l'une des deux gorges (38) est voisine de la surface (26) frontale du côté d'attaque et est prévue sur la surface (36) latérale d'intrados, et l'autre des deux gorges est disposée sur la surface (28) frontale du côté de fuite et sur la surface (32) latérale d'extrados.
  2. Aube (10) mobile de turbine suivant la revendication 1, dans laquelle chaque surface (30, 32) latérale a au moins deux flancs (34) portant et la gorge est disposée au-dessus du au moins un flanc (34) portant le plus bas.
  3. Aube (10) mobile de turbine suivant la revendication 1 ou 2,
    dans laquelle au moins une gorge (38) est prévue au-dessus de chaque flanc (34) portant.
  4. Aube (10) mobile de turbine suivant l'une des revendications précédentes,
    dans laquelle la longueur axiale de l'étendue de l'évidement ne représente pas plus de 5% de ladite distance (A).
  5. Aube (10) mobile de turbine suivant l'une des revendications précédentes,
    dans laquelle les longueurs axiales des gorges (32), opposées l'une à l'autre en diagonale, sont différentes.
  6. Agencement (40) d'aube mobile de turbine, comprenant un support (42) d'aube mobile de turbine tournant en utilisation conforme, sur le pourtour extérieur duquel sont répartis uniformément le long du pourtour une pluralité de rainures (48) de maintien, dans lesquelles des aubes (10) mobiles de turbine, suivant l'une des revendications précédentes, sont montées.
EP15787931.3A 2014-10-28 2015-10-22 Aube mobile de turbine Active EP3183430B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14190587.7A EP3015652A1 (fr) 2014-10-28 2014-10-28 Aube mobile de turbine
PCT/EP2015/074435 WO2016066511A1 (fr) 2014-10-28 2015-10-22 Aube mobile de turbine

Publications (2)

Publication Number Publication Date
EP3183430A1 EP3183430A1 (fr) 2017-06-28
EP3183430B1 true EP3183430B1 (fr) 2019-03-20

Family

ID=51830220

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14190587.7A Withdrawn EP3015652A1 (fr) 2014-10-28 2014-10-28 Aube mobile de turbine
EP15787931.3A Active EP3183430B1 (fr) 2014-10-28 2015-10-22 Aube mobile de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP14190587.7A Withdrawn EP3015652A1 (fr) 2014-10-28 2014-10-28 Aube mobile de turbine

Country Status (3)

Country Link
US (1) US10781703B2 (fr)
EP (2) EP3015652A1 (fr)
WO (1) WO2016066511A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019207620A1 (de) * 2019-05-24 2020-11-26 MTU Aero Engines AG Laufschaufel mit Schaufelfußkontur mit in einem konkaven Konturabschnitt vorgesehenem Geradenabschnitt
US11203944B2 (en) * 2019-09-05 2021-12-21 Raytheon Technologies Corporation Flared fan hub slot

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19705323A1 (de) * 1997-02-12 1998-08-27 Siemens Ag Reduzierung von lokalen Spannungen in Schaufelfußnuten
US5836744A (en) * 1997-04-24 1998-11-17 United Technologies Corporation Frangible fan blade
JP2005136572A (ja) 2003-10-29 2005-05-26 Renesas Technology Corp 無線通信用半導体集積回路およびデータ処理用半導体集積回路並びに携帯端末
US7594799B2 (en) * 2006-09-13 2009-09-29 General Electric Company Undercut fillet radius for blade dovetails
EP2045444B1 (fr) * 2007-10-01 2015-11-18 Alstom Technology Ltd Aube de rotor, procédé de fabrication d'une aube de rotor, et compresseur avec une telle aube
US20090297351A1 (en) * 2008-05-28 2009-12-03 General Electric Company Compressor rotor blade undercut
EP2546465A1 (fr) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Pied d'aube, aube, disque de rotor et ensemble de turbomachine associés
US9151167B2 (en) * 2012-02-10 2015-10-06 General Electric Company Turbine assembly
US9359905B2 (en) * 2012-02-27 2016-06-07 Solar Turbines Incorporated Turbine engine rotor blade groove

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US20170241275A1 (en) 2017-08-24
US10781703B2 (en) 2020-09-22
EP3015652A1 (fr) 2016-05-04
WO2016066511A1 (fr) 2016-05-06
EP3183430A1 (fr) 2017-06-28

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