EP3183430A1 - Aube mobile de turbine - Google Patents

Aube mobile de turbine

Info

Publication number
EP3183430A1
EP3183430A1 EP15787931.3A EP15787931A EP3183430A1 EP 3183430 A1 EP3183430 A1 EP 3183430A1 EP 15787931 A EP15787931 A EP 15787931A EP 3183430 A1 EP3183430 A1 EP 3183430A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine blade
turbine
grooves
turbine rotor
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
Application number
EP15787931.3A
Other languages
German (de)
English (en)
Other versions
EP3183430B1 (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
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 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
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 a itself
  • Turbinenlaufschaufel on the rotor latter has either a circumferential shaft collar or a rotor disk, on the outer circumference are provided largely extending in the axial direction retaining grooves.
  • 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 for
  • Turbine blade securely holds on the rotor, regardless of the forces acting on the turbine blade centrifugal forces. Nevertheless, particularly in the operation of stationary gas turbines due to the weight of the turbine blade such high centrifugal forces occur that the blade carrier is locally loaded inadmissible high. This locally inadmissibly high load leads to a reduced service life of the blade carrier or the rotor disk, which is undesirable.
  • 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 invention is based on the finding that the centrifugal force load caused by the turbine blade in the
  • Blade carrier along the retaining mat is different in size. 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 voltage concentrations occur that affect the predeterminable life of the blade carrier. For this reason, it is helpful to extend the service life of the blade carrier, for example a rotor disk , to reduce the stresses that occur there.
  • Stiffnesses are achieved in that in the region of the concave rounding, a groove adjoining at least one of the two end faces is arranged.
  • ⁇ An arrangement of the groove in the region of the concave fillet of existing at this point load-bearing cross-section of the blade root is reduced.
  • the blade root becomes softer at this point compared to the stiffness of the blade root midway between the two opposing planar faces.
  • the increased elasticity in the region of the frontal surfaces of the blade root causes centrifugal force to reduce the contact pressure of the turbine blade on the supporting flanks of the blade carrier there lo ⁇ cal and thus the previously occurring there Stress concentration can be reduced in the blade carrier.
  • the groove has an edge contour with a tapering end, which shows said end to the opposite side wall.
  • the notch load in the region of the groove can be kept low.
  • each side surface of the blade root has at least two supporting flanks and thus the blade root is a fir tree-shaped
  • End face contour provides, wherein the groove is disposed above the support flank, which should learn due to the vote of the dimensions of the turbine blade root and the corresponding holding groove of the blade carrier, the largest mechanical load under centrifugal force. Since this is often the lowest arranged supporting flank, the groove is expediently arranged above the bottommost angeord ⁇ Neten supporting flank. Of course, it is possible that at least one groove is arranged above each support flank. However, particularly preferred is that Turbinenlaufschau ⁇ fel, wherein the blade comprises a pressure side wall and a suction side wall extending for a working fluid from a leading edge to a trailing edge and in which at least two grooves are provided, of which one of the two recesses on the inflow
  • This refinement takes into account the fact that flow forces act on the blade 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 slots.
  • downstream groove in the axial direction is made longer than the further upstream groove, since it has been found that in the downstream side the loads caused by the flow forces are greater than on the
  • the invention relates to a turbine blade for a thermal turbomachine, in which along a imaginary blade longitudinal axis of the turbine blade of un ⁇ th upward - to be precise by a fastening-side blade end other to the opposite schaufelspitz brieflyem blade end - follows a blade root for securing the turbine blade to a rotor of the turbine an over ⁇ transition region and an adjoining aerodyna ⁇ mixed curved blade, wherein the blade root has two mutually opposite planar end faces and two opposing, the two end faces miteinan- connecting contoured side surfaces, in wel ⁇ chen 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 in the Pass the supporting flanks over concave fillets into the transition area or to the free flanks.
  • the blade root has two mutually opposite planar end faces and two opposing, the two end faces miteinan- connecting contoured side surfaces, in wel ⁇
  • Blade carrier extends the life of Turbinenlaufschaufelträ ⁇ gers, it is proposed that in at least one concave fillet a adjacent to one of the two end faces groove is arranged, the extent of which along the side surface is less than that of the support flank.
  • FIG. 2 shows the side view of the detail of a blade carrier with a retaining ⁇ and a seated therein turbine blade and
  • FIG 3 is a side view of the side surfaces of the blade foot ⁇ the turbine blade of FIG. 2
  • identical features are provided with the same reference numerals.
  • FIG. 1 shows a perspective view of a turbine rotor 10.
  • the turbine rotor blade 10 comprises an imaginary longitudinal axis 12 from bottom to top
  • 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 a
  • 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.
  • 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 one another via a convex rounding and thus form a bead arranged in the respective side surface 30, 32, which extends from the inflow-side end face 26 to the outflow-side end face 28.
  • a recess 38 adjoining the front side 26 is arranged, the first along the side surfaces 30 is smaller than that of the support flank 34 and the bearing surface (see Figure 2) of the support flank 34 is reduced (compared to the respective support flank 34 without the adjacent groove).
  • the groove 38 occur in a turbine blade ⁇ arrangement 40 - comprising a rotatable in normal use turbine blade carrier 42, at its outer circumference evenly distributed along the circumference a plurality of retaining grooves 48 are provided, and in which the turbine blade 10 is arranged - lower mechanical Belastun ⁇ gene on, which extends the life of the turbine blade carrier 42nd
  • FIG. 2 shows a detail of the turbine blade arrangement 40, in which a turbine blade carrier 42 is designed as a rotor disk, which can be rotated about a machine axis 44.
  • a turbine blade carrier 42 is designed as a rotor disk, which can be rotated about a machine axis 44.
  • 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 concave between the opposite fillets 36 and the groove 38 lying reduced distance F is compared with the distance from ⁇ without groove.
  • 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.
  • Figure 3 shows a plan view of the side surface 30 of the blade root 14 of turbine blade 10.
  • the two ebe ⁇ NEN 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 front side 26, at which the groove 38 adjoins an amount of 10 ⁇ 6, before preferably not more than 5% of the distance A does not exceed. Here it is 3%.

Landscapes

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

Abstract

L'invention concerne une aube mobile de turbine (10) destinée à une turbomachine thermique. Le long d'un axe longitudinal (12) imaginaire de l'aube mobile de turbine (10), une zone de transition (16) à laquelle se raccorde un corps d'aube courbé de manière aérodynamique suit de bas en haut une emplanture d'aube (14) destinée à fixer l'aube mobile de turbine (10) sur un rotor de la turbine. L'emplanture (14) de l'aube comprend deux faces frontales (26, 28) planes opposées l'une à l'autre et deux faces latérales (30, 32) profilées opposées l'une à l'autre, qui relient les deux faces frontales, faces latérales (30, 32) dans lesquelles est constitué respectivement au moins un flanc d'appui (34), ce qui entraîne la formation d'un profil de face frontale en forme de queue d'aronde ou de sapin, et les flancs d'appui (34) se prolongeant dans la zone de transition ou vers les flancs libres par l'intermédiaire d'arrondis concaves (36). L'invention vise à fournir une aube mobile de turbine dont l'utilisation dans un support d'aube prolonge la durée de vie du support d'aube mobile de turbine. À cet effet, une gorge (38), adjacente à l'une des deux faces frontales (26, 28) et dont l'étendue le long de la face latérale (30 ou 32) est inférieure à celle du flanc d'appui (34), est ménagée dans au moins un arrondi concave (36).
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 true EP3183430A1 (fr) 2017-06-28
EP3183430B1 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

Also Published As

Publication number Publication date
EP3183430B1 (fr) 2019-03-20
US10781703B2 (en) 2020-09-22
WO2016066511A1 (fr) 2016-05-06
US20170241275A1 (en) 2017-08-24
EP3015652A1 (fr) 2016-05-04

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