EP3123001B1 - Pièce de révolution pour un rotor de turbomachine, rotor de turbomachine, module de turbomachine et turbomachine associés - Google Patents

Pièce de révolution pour un rotor de turbomachine, rotor de turbomachine, module de turbomachine et turbomachine associés Download PDF

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Publication number
EP3123001B1
EP3123001B1 EP15715335.4A EP15715335A EP3123001B1 EP 3123001 B1 EP3123001 B1 EP 3123001B1 EP 15715335 A EP15715335 A EP 15715335A EP 3123001 B1 EP3123001 B1 EP 3123001B1
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EP
European Patent Office
Prior art keywords
series
flank
tooth
grooves
blades
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
EP15715335.4A
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German (de)
English (en)
French (fr)
Other versions
EP3123001A1 (fr
Inventor
Nicolas TRAPPIER
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.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3123001A1 publication Critical patent/EP3123001A1/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
    • 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
    • F05D2250/70—Shape
    • F05D2250/72—Shape symmetric
    • 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
    • F05D2250/73—Shape asymmetric

Definitions

  • the present invention relates to a part of revolution for a turbomachine rotor, and in particular a part comprising at its periphery an annular row of teeth which define between them grooves housing rotor blade feet.
  • This type of part is for example a rotor disc.
  • the state of the art includes documents EP-A2-2 549 061 , FR-A-485,943 , US-A-4,093,399 , US-A-2,920,864 , US-A1-2007 / 020102 and US-A-5,474,421 .
  • a turbomachine rotor disk comprises at its periphery an annular row of stitched grooves in which rotor blade roots are fitted.
  • Each blade usually has a blade connected by a platform to a foot.
  • This foot comprises two parts, a radially internal part called bulb and a radially external part called stilt.
  • the bulb of the foot is connected by its stilt to the platform of dawn.
  • the foot of a dawn may have a shape of fir or dovetail.
  • its bulb In the case of a dovetail dawn foot, its bulb includes a lobe and, in the case of a fir dawn foot, its bulb comprises two or three lobes. Each lobe is connected to another lobe or to the stilt of the foot by a neck, that is to say a part of smaller section or thickness.
  • This type of stapled disc can be used in a compressor or turbomachine turbine.
  • pine tree fasteners are used for relatively loaded turbines, that is to say for turbines at high speed or with a large section of vein, because there are more important constraints because of the centrifugal force more important.
  • the absolute criteria are respected but not the hierarchy of rupture because either the section is sufficient in the bulb 16 but not in the tooth 22, or the section is sufficient in the tooth 22 but not in the bulb 16.
  • a solution to this problem would be to increase the size of the sections in the necks 12, 14 of the bulbs 16 while increasing the size of the necks in the teeth 22.
  • the width or total circumferential dimension of the fastener is directly dictated by the shape of the vein as well as the number of blades 10. Modify the vein would cause losses of efficiency of the turbine, which would lead to losses of engine performance.
  • the present invention provides a simple, effective and economical solution to this problem.
  • the invention relates to a piece of revolution, such as a disk, for a turbomachine rotor, having an axis of revolution and having at its periphery an annular row of teeth which define between them grooves for housing the feet of the blades of the blades.
  • each tooth having a first lateral flank having at least two projecting portions of a blade root, separated from each other by a recessed portion, and a second lateral flank comprising at least two projecting portions of an adjacent blade root, separated from each other by a recessed portion, said at least two projections of the first side being located on circumferences centered on the axis of revolution of the revolution piece, and said at least two projecting portions of the second flank being located on circumferences centered on said axis of revolution, such that each tooth has, over substantially its entire length dimension udinale, a defect of symmetry with respect to a substantially radial median longitudinal plane, at least one of said circumferences of the protruding portions of the second flank of each tooth being located between the circumferences of the protruding portions of the first flank, and radially offset from these circumferences .
  • a substantially radial median longitudinal plane of an element (such as a tooth or a groove) of a part of revolution, a plane extending along a longitudinal axis of the element and that passes substantially in the middle of this element.
  • This plane has a substantially radial orientation with respect to a longitudinal axis or revolution of the part.
  • the longitudinal axis of the element can be substantially parallel to the longitudinal axis or revolution of the piece. In this case, the aforementioned plane extends along the longitudinal axis of the part.
  • each tooth of the rotor revolution piece such as a disk
  • each tooth of the rotor part is not symmetrical with respect to a substantially radial median longitudinal plane.
  • the invention makes it possible to design a turbine that is much more charged than in the prior art. It also allows the mounting and retention of blades having similar feet (fir) but having dimensional differences.
  • the stilts may here have close radial dimensions. Making bindings at different heights is penalizing for larger stilts because it is a mass addition and must be compensated by a larger attachment. Therefore, it is particularly advantageous to limit the offset to have the gains on the enlargement of the disc teeth without having too much penalty on the weighting of the blades with the largest stilts.
  • Each groove of the part may have, over substantially its entire longitudinal dimension, a symmetry with respect to a substantially radial median longitudinal plane.
  • the circumference of at least one of said projecting portions of the second sidewall substantially passes through a recessed portion of the first sidewall.
  • the circumferences of two adjacent projecting portions of the second side of each tooth may pass substantially respectively by two recessed portions of the first side of this tooth.
  • the grooves may have different depths or radial dimensions.
  • the grooves comprise a first series of identical grooves regularly distributed around the axis of revolution of the part, and a second series of grooves identical to each other, different from the grooves of the first series and evenly distributed around the axis. revolution of the workpiece, each groove of the first series being located between two grooves of the second series, and each groove of the second series being located between two grooves of the first series.
  • the present invention also relates to a turbomachine rotor, comprising an annular piece as described above and an annular row of vanes each comprising a blade connected to a fir-tree foot which is fitted into a groove of the part, each foot having a radially outer stub and a radially inner bulb, characterized in that the blade array comprises a first series of blades having stilts of radial dimension D5 and a second series of blades having stilts of radial dimension D6 greater than D5, each blade of the first series being located between two blades of the second series, and each blade of the second series being located between two blades of the first series.
  • the present invention also relates to a turbomachine module, such as a compressor or a turbine, comprising at least one annular piece or at least one rotor as described above.
  • a turbomachine module such as a compressor or a turbine, comprising at least one annular piece or at least one rotor as described above.
  • the present invention finally relates to a turbomachine, comprising at least one annular piece or at least one rotor as described above.
  • Figures 1 and 2 represent a rotor wheel 26 of a turbomachine, this wheel comprising a disk 24 carrying at its periphery an annular row of blades 10.
  • Each blade 10 comprises a blade 28 connected by a platform 30 to a foot 32 which is fitted into a groove 34 of the periphery of the disc 24.
  • the disc 24 comprises at its periphery an annular row of teeth 22 which define between them the grooves 34 for receiving the feet. 32
  • the number of grooves 34 or teeth 22 of the disc 24 is equal to the number of blades 10 it can wear.
  • the grooves 34 are obtained by broaching the outer periphery of the disc 24 and here have an orientation substantially parallel to the longitudinal or revolution axis A of the disc 24.
  • the blade roots 32 here have a double-lobed fir shape 36.
  • a blade root 32 comprises a radially outer stalk 38 and a radially inner bulb 16 which is connected by the stilt 38 to the platform of the blade. dawn 10.
  • Each blade root 32 comprises two necks 12, 14 (or parts of smaller thickness or section), a lower neck 12 between the two lobes 36 of the bulb 16, and an upper neck 14 between the upper lobe and the stilt 38
  • Each foot 32 has a symmetry with respect to a substantially radial median longitudinal plane P1.
  • Each tooth 22 of the disk 24 comprises two lateral flanks 40 which are shaped to cooperate with the feet 32 of adjacent blades 10 and to retain them radially in the grooves 34.
  • Each flank 40 of a tooth 22 here comprises two bearing surfaces 42, respectively upper and lower.
  • the upper span 42 forms a bearing face of a lateral face of the upper lobe of a blade root
  • the lower bearing surface 42 forms a bearing face of a lateral face of the lower lobe of this foot of dawn.
  • the staves 42 of a flank 40 are formed by protruding parts which extend over substantially the entire longitudinal dimension of the tooth 22, as can be seen in FIG. figure 1 .
  • the spans 42 of a flank 40 are separated from each other by a recessed portion which also extends over substantially the entire longitudinal dimension of the tooth 22.
  • each tooth 22 has a symmetry with respect to a substantially radial median longitudinal plane P2. Due to this symmetry, the recessed portions of the flanks 40 of the same tooth 22 are located substantially on a same circumference C1 centered on the axis A. These recessed portions define an upper neck 20 of the tooth 22.
  • the tooth 22 comprises a lower neck 18 between its lower surfaces 42 and the bottoms of the grooves 34.
  • each tooth 22 'of the disc 24' has, over substantially its entire longitudinal dimension, a defect of symmetry with respect to the substantially radial median longitudinal plane P2.
  • each tooth 22 ' comprises two lateral flanks 40', 40 "which are shaped to cooperate with the feet 32 of adjacent blades 10 ', 10" and to retain them radially in the grooves 34', 34 ".
  • Each flank 40 ', 40 "of a tooth 22' comprises two bearing surfaces 42, respectively upper and lower,
  • the upper bearing surface 42 forms a bearing surface of a lateral face of the upper lobe of a blade root, and the bottom span 42 forms a bearing face of a side face of the lower lobe of the blade root.
  • the bearing surfaces 42 of a tooth flank 40 ', 40 are formed by projecting portions which extend over substantially the entire longitudinal dimension of the tooth, as can be seen in FIG. figure 1 .
  • the bearing surfaces 42 of a flank 40 ', 40 are separated from each other by a recessed portion which also extends over substantially the entire longitudinal dimension of the tooth.
  • the lower bearing surface 42 of a flank 40 40 is separated from the bottom of the corresponding groove 34 ', 34" by another recessed portion which also extends over substantially the entire longitudinal dimension of the tooth.
  • the projecting upper portions of the flanks 40 ', 40 "of the same tooth 22' are not located on the same circumference. This is also the case of their lower projecting parts, their upper recessed parts and their lower recessed parts.
  • the upper projecting portion of a first flank 40 "(here the left flank of the tooth 22 ') is located on a circumference C3 which has a diameter greater than that of the circumference C4 passing by the upper projecting portion of the second flank 40 "(the right flank of the tooth 22 ').
  • This circumference C4 has a diameter greater than that of the circumference C5 passing through the upper recessed portion of the first flank 40 ", which itself has a diameter greater than that of the circumference C6 passing through the upper recessed portion of the second flank.
  • 40 ' This circumference C6 has a diameter greater than that of the circumference C7 passing through the lower projecting portion of the first flank 40', which itself has a diameter greater than that of the circumference C8 passing through the lower projecting portion of the second flank 40 '.
  • This circumference C8 substantially passes through the lower hollow portion of the first flank 40 ", and has a diameter greater than that of the circumference C9 passing through the lower recessed portion of the second flank 40 '.
  • the radial offset between the recessed portions of the flanks of each tooth makes it possible to increase the width of the teeth at these recessed portions and thus to improve the mechanical strength of the teeth.
  • the grooves 34 ', 34 "of the disc 24' are not all identical.
  • the disc 24 comprises grooves 34" of depth or radial dimension D1, and grooves 34 'of depth or radial dimension D2 which is greater than D1.
  • the grooves 34 ' are evenly distributed around the longitudinal axis of the disc 24' and each groove 34 'is situated between two grooves 34 "Similarly, the grooves 34" are evenly distributed around the longitudinal axis of the disc 24' and each groove 34 "is located between two grooves 34 '.
  • each groove 34 ', 34 "of the disk 24' has, over substantially its entire longitudinal dimension, a symmetry with respect to its substantially radial median longitudinal plane P1.
  • vanes 10 ', 10 "which together with the disc 24' form a rotor wheel are also not all identical.
  • the wheel comprises vanes 10 'whose feet each have a radial dimension D3, and vanes 10" whose feet each have a radial dimension D4 which is greater than D3.
  • the blades 10 ' are regularly distributed around the longitudinal axis of the disk 24' and each blade 10 'is situated between two blades 10 ".
  • the blades 10" are regularly distributed around the longitudinal axis of the disk 24' and each blade 10 "is located between two blades 10 '.
  • the bulbs 16 'of the blades 10' are substantially identical to those of the blades 10 '', the feet of the blades 10 'therefore differ from the feet of the blades 10 "by their stilts 38', 38", and in particular by the radial dimension of their stilts 38 ', 38 ".
  • the stilts 38 'of the blades 10' have a radial dimension D5 less than that D6 of the stilts 38 "of the blades 10".
  • the figure 5 represents an alternative embodiment of the invention which is similar to the embodiment of the figure 4 .
  • the foregoing description of the figure 4 applies to the figure 5 to the extent that it is not contradicted by the following.
  • the projecting portions of one of the flanks 40 ', 40 "of each tooth are substantially circumferentially aligned with the recessed portions of the other side of this tooth, and their recessed portions are also substantially circumferentially aligned with the projecting portions of the other sidewall.
  • the upper projecting portion of the second flank 40 ' is located on a circumference passing through the upper recessed portion of the first flank 40.
  • the lower projecting portion of the first flange 40 is located on a circumference passing through a recessed portion of the first flank 40".
  • the lower projecting portion of the second flank 40 ' is located on a circumference passing through the lower recessed portion of the first flank 40 ".
  • each tooth to have a relatively constant width or circumferential dimension over its entire radial extent, which is advantageous in terms of mechanical strength of the teeth.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15715335.4A 2014-03-24 2015-03-11 Pièce de révolution pour un rotor de turbomachine, rotor de turbomachine, module de turbomachine et turbomachine associés Active EP3123001B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1452474A FR3018849B1 (fr) 2014-03-24 2014-03-24 Piece de revolution pour un rotor de turbomachine
PCT/FR2015/050601 WO2015145016A1 (fr) 2014-03-24 2015-03-11 Piece de revolution pour un rotor de turbomachine, rotor de turbomachine, module de turbomachine et turbomachine associés

Publications (2)

Publication Number Publication Date
EP3123001A1 EP3123001A1 (fr) 2017-02-01
EP3123001B1 true EP3123001B1 (fr) 2018-02-28

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EP15715335.4A Active EP3123001B1 (fr) 2014-03-24 2015-03-11 Pièce de révolution pour un rotor de turbomachine, rotor de turbomachine, module de turbomachine et turbomachine associés

Country Status (9)

Country Link
US (1) US10436043B2 (enrdf_load_stackoverflow)
EP (1) EP3123001B1 (enrdf_load_stackoverflow)
JP (1) JP6554482B2 (enrdf_load_stackoverflow)
CN (1) CN106460530B (enrdf_load_stackoverflow)
BR (1) BR112016021652B1 (enrdf_load_stackoverflow)
CA (1) CA2943461C (enrdf_load_stackoverflow)
FR (1) FR3018849B1 (enrdf_load_stackoverflow)
RU (1) RU2674859C2 (enrdf_load_stackoverflow)
WO (1) WO2015145016A1 (enrdf_load_stackoverflow)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3293362B1 (en) * 2015-08-21 2020-07-22 Mitsubishi Heavy Industries Compressor Corporation Steam turbine
FR3080437B1 (fr) * 2018-04-24 2020-04-17 Safran Aircraft Engines Systeme d'injection pour une chambre annulaire de combustion de turbomachine
EP3569820A1 (en) * 2018-05-16 2019-11-20 General Electric Technology GmbH Dovetail slot for use with rotor assemblies
FR3096744B1 (fr) * 2019-06-03 2022-01-14 Safran Aircraft Engines Ensemble de support et de guidage d’un arbre d’entrainement de turbomachine d’aeronef
CN116658455A (zh) * 2023-04-28 2023-08-29 西安航天动力研究所 一种局部进气冲击式涡轮转子及组装方法

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Also Published As

Publication number Publication date
JP6554482B2 (ja) 2019-07-31
US10436043B2 (en) 2019-10-08
RU2016140852A3 (enrdf_load_stackoverflow) 2018-10-18
CA2943461C (fr) 2022-03-22
EP3123001A1 (fr) 2017-02-01
FR3018849B1 (fr) 2018-03-16
JP2017519143A (ja) 2017-07-13
FR3018849A1 (fr) 2015-09-25
US20170122117A1 (en) 2017-05-04
CA2943461A1 (fr) 2015-10-01
RU2674859C2 (ru) 2018-12-13
BR112016021652B1 (pt) 2022-06-28
CN106460530A (zh) 2017-02-22
CN106460530B (zh) 2018-06-12
RU2016140852A (ru) 2018-04-24
BR112016021652A2 (enrdf_load_stackoverflow) 2017-08-15
WO2015145016A1 (fr) 2015-10-01

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