EP3015652A1 - Aube mobile de turbine - Google Patents

Aube mobile de turbine Download PDF

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Publication number
EP3015652A1
EP3015652A1 EP14190587.7A EP14190587A EP3015652A1 EP 3015652 A1 EP3015652 A1 EP 3015652A1 EP 14190587 A EP14190587 A EP 14190587A EP 3015652 A1 EP3015652 A1 EP 3015652A1
Authority
EP
European Patent Office
Prior art keywords
blade
end faces
support
flank
groove
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.)
Withdrawn
Application number
EP14190587.7A
Other languages
German (de)
English (en)
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
Priority to EP14190587.7A priority Critical patent/EP3015652A1/fr
Priority to US15/519,698 priority patent/US10781703B2/en
Priority to PCT/EP2015/074435 priority patent/WO2016066511A1/fr
Priority to EP15787931.3A priority patent/EP3183430B1/fr
Publication of EP3015652A1 publication Critical patent/EP3015652A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/30—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 blade for a turbine, in which along an imaginary blade longitudinal axis of the blade from bottom to top of a blade root for attachment of the blade to 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 is formed and in which the support flanks pass over concave fillets in the transition region or free flanks.
  • the blade described above is well known in the art and is particularly used in gas turbines.
  • the latter has either 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 blade.
  • the retaining grooves are shaped accordingly to the end contour of the blade root of the blade, so that overall a positive connection between the blade and rotor is present, which holds the blade safely on the rotor during normal operation of a blade having the blade, regardless of the forces acting on the blade centrifugal forces ,
  • the object of the invention is therefore to provide a blade whose use in a blade carrier extends the life of the blade carrier.
  • the object directed to the invention is achieved by a blade according to claim 1.
  • a groove adjacent to one of the two end faces is arranged whose extension along the side surfaces is smaller than that of the support flank and which reduces the bearing surface of the support flank compared to the relevant support flank without adjacent thereto groove.
  • the invention is based on the finding that the centrifugal force load in the blade carrier caused by the blade 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 or compressor - 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 helpful in prolonging the service life of the blade carrier, for example a rotor disk, to reduce the stresses occurring there.
  • the blade root along the Tragflankenerstreckung (Of the 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 by arranging a groove adjacent to at least one of the two end faces in the area of the concave rounding.
  • the arrangement of the groove in the region of the concave rounding of the present at this point supporting 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.
  • each side surface of the blade root has at least two supporting 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 blade root and the corresponding retaining groove of the blade carrier, the largest mechanical Load under centrifugal force is to learn. 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.
  • blade in which the blade comprises a suction side wall and a pressure 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 the one of the two recesses on the upstream end face adjacent and at the same time provided on the suction 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 pressure 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 blade experiences a torque, which torque must be absorbed and compensated by the material of the blade carrier surrounding the retaining.
  • the invention relates to a blade for a thermal turbomachine, in which along an imaginary blade longitudinal axis of the blade from bottom to top - exactly a blade root for attachment of the blade to a rotor of the turbine a transition region and an adjoining aerodynamically curved blade follows, said blade root having two opposite planar end faces and two opposite, 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 in which the support flanks pass over concave fillets in the transition region or to the free flanks.
  • FIG. 1 shows in perspective view a blade 10.
  • the illustrated blade 10 is a turbine blade. However, this is not meant to be limiting since the blade can also be configured as a compressor blade.
  • the 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 a trailing edge 22, which are connected to each other via a suction side wall 21 and a pressure 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 blade assembly 40 - comprising a rotatable in normal use blade carrier 42, on its outer circumference evenly distributed along the circumference a plurality of retaining grooves 48 are provided, and in which the blade 10 is arranged - lower mechanical loads, which prolongs the life of the blade carrier 42.
  • FIG. 2 shows a section of the blade assembly 40, in which a blade carrier 42 is formed as a rotor disk which 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 for blades is shown, in which a blade 10 is inserted. 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 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 blade 10.
  • the two flat end faces 26, 28 are opposite to a 100% normalized distance A, wherein the longitudinal extent of the groove 38th a length L, measured from the end face 26, at which the groove 38 adjoins, does not exceed an amount of 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)
EP14190587.7A 2014-10-28 2014-10-28 Aube mobile de turbine Withdrawn EP3015652A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP14190587.7A EP3015652A1 (fr) 2014-10-28 2014-10-28 Aube mobile de turbine
US15/519,698 US10781703B2 (en) 2014-10-28 2015-10-22 Turbine rotor blade
PCT/EP2015/074435 WO2016066511A1 (fr) 2014-10-28 2015-10-22 Aube mobile de turbine
EP15787931.3A EP3183430B1 (fr) 2014-10-28 2015-10-22 Aube mobile de turbine

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP3015652A1 true EP3015652A1 (fr) 2016-05-04

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 After (1)

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

Country Status (3)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220251959A1 (en) * 2019-05-24 2022-08-11 MTU Aero Engines AG Rotor blade with blade root contour having a straight portion provided in a concave contour portion

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11203944B2 (en) * 2019-09-05 2021-12-21 Raytheon Technologies Corporation Flared fan hub slot

Citations (7)

* 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
US6146099A (en) * 1997-04-24 2000-11-14 United Technologies Corporation Frangible fan blade
US20080063529A1 (en) * 2006-09-13 2008-03-13 General Electric Company Undercut fillet radius for blade dovetails
DE102009025814A1 (de) * 2008-05-28 2009-12-03 General Electric Co. Unterschneidung an einer Verdichterrotorschaufel
EP2546465A1 (fr) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Pied d'aube, aube, disque de rotor et ensemble de turbomachine associés
EP2626516A1 (fr) * 2012-02-10 2013-08-14 General Electric Company Agencement de turbine et procédé pour modifier une fréquence de résonance
US20130224036A1 (en) * 2012-02-27 2013-08-29 Solar Turbines Incorporated Turbine engine rotor blade groove

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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

Patent Citations (7)

* 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
US6146099A (en) * 1997-04-24 2000-11-14 United Technologies Corporation Frangible fan blade
US20080063529A1 (en) * 2006-09-13 2008-03-13 General Electric Company Undercut fillet radius for blade dovetails
DE102009025814A1 (de) * 2008-05-28 2009-12-03 General Electric Co. Unterschneidung an einer Verdichterrotorschaufel
EP2546465A1 (fr) * 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Pied d'aube, aube, disque de rotor et ensemble de turbomachine associés
EP2626516A1 (fr) * 2012-02-10 2013-08-14 General Electric Company Agencement de turbine et procédé pour modifier une fréquence de résonance
US20130224036A1 (en) * 2012-02-27 2013-08-29 Solar Turbines Incorporated Turbine engine rotor blade groove

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220251959A1 (en) * 2019-05-24 2022-08-11 MTU Aero Engines AG Rotor blade with blade root contour having a straight portion provided in a concave contour portion
US11753950B2 (en) * 2019-05-24 2023-09-12 MTU Aero Engines AG Rotor blade with blade root contour having a straight portion provided in a concave contour portion

Also Published As

Publication number Publication date
EP3183430B1 (fr) 2019-03-20
US20170241275A1 (en) 2017-08-24
US10781703B2 (en) 2020-09-22
WO2016066511A1 (fr) 2016-05-06
EP3183430A1 (fr) 2017-06-28

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