EP3236011B1 - Rotor comprenant un porte à faux sur les pales pour un élément de sécurité - Google Patents

Rotor comprenant un porte à faux sur les pales pour un élément de sécurité Download PDF

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Publication number
EP3236011B1
EP3236011B1 EP17166817.1A EP17166817A EP3236011B1 EP 3236011 B1 EP3236011 B1 EP 3236011B1 EP 17166817 A EP17166817 A EP 17166817A EP 3236011 B1 EP3236011 B1 EP 3236011B1
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EP
European Patent Office
Prior art keywords
rotor
overhang
circumferential direction
radially outwardly
blade
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
EP17166817.1A
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German (de)
English (en)
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EP3236011A1 (fr
Inventor
Markus WEINERT
Tobias Leymann
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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Filing date
Publication date
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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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/12—Blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/11—Two-dimensional triangular
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a rotor for an engine, in particular a gas turbine engine according to the preamble of claim 1.
  • EP 2 873 807 A1 and EP 2 860 350 A1 disclose known rotors according to the preamble of claim 1.
  • a generic and example from U.S. 5,256,035 A known rotor has a rotor base part, which has attachment points for rotor blades arranged one behind the other along a circumferential direction about an axis of rotation. The individual rotor blades are each held in a form-fitting manner in an associated fastening groove via a blade root.
  • a one-part or multi-part securing element is provided, which is positively held on at least one of the rotor blades on a radially outer edge and on the rotor base part on a radially inner edge.
  • a multi-part securing element which consists of several plate segments and a fastening ring.
  • a radially inner edge of the individual plate segments is positively received in a groove of the rotor base part, so that a radially outwardly extending overhang of the rotor base part encompasses the radially inner edge of the plate segments.
  • the fastening ring is in turn accommodated in a groove which is formed in each case on a blade base of a rotor blade. In this case, one encompasses itself radially inward extending overhang of the vane base the radially outer edge of the mounting ring over which also secures a plate segment disposed adjacent and axially adjacent the mounting ring.
  • the rotor here comprises a rotor base part in the form of a rotor disk 2 with a plurality of fastening grooves 20 spaced apart from one another along a circumferential direction U.
  • a blade root 32 of a rotor blade 3a, 3b is accommodated in each fastening groove 20.
  • the plurality of blades which are arranged along the circumference of the rotor in a row (for example 20 pieces) are in the Figures 5A , 5B , 5C and 5D only two of them are shown in detail with a view along the axis of rotation of the rotor.
  • Each rotor blade 3a, 3b comprises a blade base 31 from which a blade 30 protrudes radially.
  • the blade root 32 extends from the blade base 31 in the radially inward direction ri.
  • the blade base 31 of a moving blade 3a or 3b in each case forms an overhang 310 which extends radially inward, ie along the radial direction ri pointing towards it.
  • a radially outer edge 43 of a securing plate 4 is surrounded by this overhang 310 .
  • a plurality of (at least two) rotor blades 3a and 3b are secured in the axial direction on the rotor base part 2 in the region of the fastening grooves 20 via this securing plate 4 .
  • the securing plate 4 is connected not only to the rotor blades 3a and 3b, but also to the rotor base part 2.
  • a rotating blade 3a, 3b known from the prior art forms an overhang 310 for encompassing the radially outer edge 43 of the securing plate 4, which over an entire length L along the circumferential direction U is formed as a continuous edge 311 running in a straight line or in the shape of a circular arc .
  • their respective overhangs 310 of adjacent edges 311 should therefore be aligned with one another on a pair of moving blades 3a and 3b arranged adjacent to one another, so that the radially inner lower edges of these edges 311 lie on a circular path around the axis of rotation M of the rotor.
  • Figures 5B and 5C illustrate. Because of the tolerances to be allowed, it is possible for the individual overhangs 310 of mutually adjacent moving blades 3a, 3b to be offset radially with respect to one another.
  • the Figures 5B and 5C show an example of an offset g of the two rotor blades 3a and 3b in the area of their overhangs 310.
  • the one (left) moving blade 3b is offset radially inwards compared to the adjacent (right) moving blade 3a.
  • one overhang 310 of one rotor blade 3b thus protrudes into an annular gap flow in the circumferential direction U (offset “into the wind”).
  • one (left) rotor blade 3b is offset radially outwards relative to the other (right) rotor blade 3a (offset “out of the wind”).
  • the edge 311 of the overhang 310 of one rotor blade 3b is thus completely offset radially outwards relative to the overhang 310 of the other rotor blade 3a.
  • An offset g that can be observed in practice for both cases is only in the range of 0.2 mm to 0.4 mm for a rotor.
  • undesired turbulence can occur in the area of adjoining blade bases 31 and thus adjoining overhangs 310 .
  • the object of the invention is to improve a rotor in this regard.
  • a rotor is proposed with a specially designed overhang on at least one moving blade which is positively connected to the rotor base part.
  • the overhang has two, first and second, edge sections along its extent in the circumferential direction, which are each provided at one end of the overhang, based on the circumferential direction, and each opposite at least one further, third edge section of the overhang, which also encompasses the edge of the securing element are set back in a radially outward direction in such a way that the blade root and a lower edge of the overhang can be pushed through the gap in the rotor base part when the securing element is not yet or no longer attached.
  • the overhang of at least one rotor blade in a rotor according to the invention is set back or set back at a lower edge of the overhang in the radially outward direction such that the overhang at a radially inner lower edge does not have a straight line or arc-shaped course along the circumferential direction.
  • This includes in particular the formation of an edge section with a radial offset to an adjacent edge section of the same overhang as well as the formation of an edge section whose radial extension in the circumferential direction steadily decreases and thus defines an area of the lower edge of the overhang that runs obliquely to the circumferential direction.
  • regions are thus formed, for example, which are offset radially with respect to one another and/or run at an angle with respect to one another.
  • a recess is thus defined from the outset, preferably in the area of adjacent overhangs. This can lead to the minimization or avoidance of disruptive turbulence in the area of the securing element, particularly with appropriate dimensioning. Furthermore, a weight reduction can be achieved in this way, as well as a simplification in the assembly and/or disassembly of a rotor blade.
  • the at least one recessed edge section can be designed and arranged along the circumferential direction in such a way that at least part of the overhang can be pushed through the fastening groove in the axial direction when the securing element is not yet or no longer fixed to the rotor base part.
  • At least one of the first and second radially outwardly recessed edge sections may have a smaller extension in the radially inward direction than an adjacent edge section.
  • the overhang thus extends radially inward to a lesser extent in the region of the recessed edge section.
  • At least one of the first and second radially outwardly recessed edge portions is provided at a circumferential end of the overhang in one embodiment. In this way, a defined recess is provided via the recessed edge section in that area at which two mutually adjacent moving blades abut with their blade bases.
  • At least one of the first and second radially outwardly recessed edge sections forms an area on the radially inner lower edge of the overhang, which runs at least partially inclined with respect to the circumferential direction. Consequently, the recessed edge section can not only be set back in stages to an adjoining edge section of the overhang, but also form a setback that is continuously increasing or decreasing at least in sections in the circumferential direction.
  • one exemplary embodiment provides that the at least one edge section that is recessed radially outwards extends along the circumferential direction of the rotor with a length that corresponds to at least three times, in one variant at least four times, a height of the height that is recessed radially outwards Edge portion relative to an adjacent edge portion of the overhang (at least) is withdrawn.
  • the at least one edge section that is set back radially outwards is set back by at least a height of 0.5 mm, in particular at least by a height of 0.8 mm or 1 mm, compared to an adjoining edge section of the rotor blade overhang.
  • a recess is thus formed over the recessed edge section, which has a maximum depth of at least 0.5 mm, 0.8 mm or 1 mm when two adjacent moving blades are nominally aligned.
  • the overhang of a rotor blade of the rotor can have two edge sections, namely a first and a second edge section, which are each set back in a radially outward-pointing direction compared to at least one further third edge section of the overhang, which also encompasses the edge of the securing element.
  • the first edge section and the second edge section are thus spatially separated from one another and spaced apart from one another along the circumferential direction, but each is set back radially outwards relative to at least a third edge section of the moving blade overhang.
  • the two recessed edge sections can be recessed to different extents and/or can extend along the circumferential direction with different lengths from one another.
  • the overhang of a moving blade can thus be configured asymmetrically with respect to a radial direction. This enables, for example, a configuration of a recess that is optimized in terms of the direction of rotation, which is formed by two edge sections of two adjacent rotor blades that are adjacent to one another and are each set back radially outwards.
  • first and second edge sections of a rotor blade which are set back radially outwards, are provided on ends of the associated overhang (and a blade base of the associated rotor blade) that are spaced apart from one another along the circumferential direction.
  • a second edge portion of one (first) blade overhang and a first edge portion of another (second) blade overhang thus adjoin adjacent blades and blade bases.
  • overhangs can be provided on at least two moving blades of the rotor which are arranged adjacent to one another along the circumferential direction, with edge sections which adjoin one another and are each set back radially outwards.
  • a radially outwardly directed recess of a defined minimum length and minimum height is then formed in the region of the border sections of two adjacent rotor blades that adjoin one another.
  • an interruption of a circular course of the edges of the individual overhangs that follow one another along the circumferential direction is thus provided in a targeted manner.
  • At least one of the first and second radially outwardly recessed edge portions is opposite the adjacent third edge portion of the rotor blade overhang is reduced by at least the sum of the shape and position tolerances of this third edge section.
  • a recess is thus formed via a recessed first or second edge section, which has a maximum (radial) depth of at least the sum of the shape and position tolerances of the third edge section when two adjacent moving blades are nominally aligned.
  • a nominal position of the third edge section with respect to the associated fastening groove and/or with respect to an overhang of an adjacent moving blade of the rotor is predetermined via the shape and position tolerances.
  • a recess defined in the area of the blade bases of two adjacent moving blades is elliptical, trapezoidal or triangular in a view along the axis of rotation, for example.
  • overhangs with adjacent edge sections that are set back radially outward can be provided on each pair of moving blades arranged adjacent to one another, so that along the circumferential direction in the area of adjoining edge sections of two adjacent moving blades there is a radially outwardly directed recess of a defined minimum length and minimum height is formed.
  • the formation of a recess is therefore not limited to individual pairs of moving blades, but is provided continuously in each area of two adjacent moving blades.
  • At least one of the first and second edge sections set back radially outwards can be produced, for example, by mechanical material removal. This includes production by means of a machining manufacturing process, such as grinding or milling. In such a variant, material can consequently be removed in a targeted manner on the overhang of a rotor blade base, for example ground off, in order to achieve that a radially inner lower edge of the overhang no longer has a straight course.
  • an edge section set back radially outwards can be produced by thermal material removal.
  • the production takes place by means of eroding.
  • the (thermal) removal of material on the overhang to produce a recessed edge section in takes place in one operation with the production of specific functional areas on a rotor blade.
  • a functional area such as a damper pocket or a blade base area provided with at least one cutout to reduce weight, to be produced on a moving blade in the area of the blade base by eroding.
  • the overhang of a rotor blade can then also be processed accordingly in order to provide an edge section that is set back radially outwards.
  • the at least one securing element can be provided for axially securing at least two rotor blades.
  • a preferably plate-shaped securing element is surrounded at a (radially outer) edge by the overhangs of at least two rotor blades.
  • FIG. 12 illustrates, schematically and in a sectional view, a (gas turbine) engine T, in which the individual engine components are arranged one behind the other along a central axis or axis of rotation M.
  • a fan F At an inlet or intake E of the engine T, air is sucked in along an entry direction E by means of a fan F.
  • This fan F is driven by a shaft, which is rotated by a turbine TT.
  • the turbine TT is connected to a compressor V, which has, for example, a low-pressure compressor 11 and a high-pressure compressor 12, and possibly also a medium-pressure compressor.
  • the fan F supplies air to the compressor V and, on the other hand, to a bypass channel B for generating the thrust.
  • the air conveyed via the compressor V finally reaches a combustion chamber section BK, in which the drive energy for driving the turbine TT is generated.
  • the turbine TT has a high-pressure turbine 13 , a medium-pressure turbine 14 and a low-pressure turbine 15 .
  • the Turbine TT operates via the The energy released during combustion turns on the fan F, in order to then generate the required thrust via the air conveyed into the bypass duct B.
  • the air leaves the bypass channel B in the area of an outlet A at the end of the engine T, where the exhaust gases from the turbine TT flow to the outside.
  • the outlet A usually has a thrust nozzle.
  • At least one rotor comes with the introduction in connection with the Figures 5A to 5D configuration shown for use.
  • the rotor is arranged and rotatably mounted about the central axis or axis of rotation M in such a way that the individual securing plates 4 provided along the circumferential direction U for axially securing the rotor blades 3a, 3b are arranged on a downstream end face of the rotor 2.
  • the individual securing elements 4 thus face an annular space 5 which is formed in the region of the blade roots 32 of the individual moving blades 3a, 3b between the rotor and a guide blade arrangement 6.
  • the flow arising in this annular space 5 can be undesirably swirled in a configuration of the overhangs 310 of the blade bases 31 used for the connection between the rotor blades 3a, 3b and a securing element 4 if individual overhangs 310 are offset from one another due to tolerances. Individual overhangs 31 then protrude completely into the flow path defined in a circular ring around the axis of rotation along the securing plates 4 or are set back radially outward for this purpose (cf Figures 5B and 5C ).
  • an overhang 310 which is provided for a form-fitting connection with a radially outer edge 43 of a multipart or one-part securing element, such as a securing plate 4, is formed with an edge section of defined geometry and size that is set back in the radially outer direction ra.
  • At least one defined radial recess is provided from the outset, which influences the flow as little as possible, but in any case in a foreseeable manner.
  • a plurality of recesses distributed along the circumferential direction U are preferably provided, in particular on each pair of blade bases 31 arranged adjacent to one another.
  • an overhang 310 of a blade base 31 of each rotor blade 3a, 3b fixed to the rotor base part 2 has two edge sections 311a and 311c set back radially outwards. These two radially recessed edge sections 311a and 311c have a smaller extension in the radially inward direction ri than a third edge section 311b formed between them.
  • the length of the third edge section 311b along the circumferential direction U can be at least twice the shape and position tolerances of a gap between the axial securing elements 4 and/or at least half of a minimum width d of a blade neck 320 of the blade root 32 inserted into the associated fastening groove 20 Rotor blade 3a or 3b (cf. the individual representation of a rotor blade 3a of Figure 1D ).
  • the length of the third edge section 311b along the circumferential direction U is less than 60%, optionally less than 50% or even less than 35% of the total length L of an overhang 310 along the circumferential direction U.
  • a recessed edge section 311a or 311c is provided at the ends of an overhang 310 that are spaced apart from one another along the circumferential direction U.
  • the edge sections 311a and 311c extend with different lengths a1 and a2 in the circumferential direction U.
  • Both recessed edge sections 311a and 311c also form an area of the lower edge of the overhang 310 that runs inclined to the circumferential direction U.
  • each recessed edge section 311a, 311c runs obliquely outwards towards the respective end, so that a radial extension of the respective recessed edge section 311a or 311c towards the respective lateral edge of the overhang 310 steadily decreases.
  • the individual edge sections 311a and 311c are each set back up to a height b1 or b2 compared to the central edge section 311b.
  • this height b1 or b2 is greater than 0.8 mm and is approximately 1 mm.
  • the extent in the circumferential direction U of the respective recessed edge section 311a, 311c is in turn measured as a—preferably integer—multiple of this height b1 or b2.
  • a length a1, a2 corresponds to at least three times a height b1 or b2 of the respective recessed edge section 311a, 311c.
  • the heights b1 and b2 of the recessed edge sections 311a and 311c are dimensioned such that in the region of mutually adjacent moving blades 3a, 3b and so that adjoining blade bases 31 are formed by two recessed edge sections 311c and 311a running obliquely towards one another in each case a radial recess 33 in the course of the lower edges of a plurality of securing plates 4 following one another in the circumferential direction U.
  • This radial recess 33 is dimensioned via the recessed edge sections 311c and 311a of the individual rotor blades 3a and 3b such that even with a tolerance-related maximum radial offset g of two rotor blades 3a and 3b, a radial depth of the respective recess 33 is greater than the offset g and preferably corresponds to a multiple of the offset g. A (relevant) influence on the flow due to the offset g is thus excluded or minimal (cf Figure 1B ).
  • the recessed edge sections 311a and 311c still provide a sufficient extension of the overhang 310 in the radially inner direction ri, so that there is also a groove 3100 in the area of a recessed edge section 311a or 311c for the surrounded radially outer edge 43 of the securing plate 4.
  • the radially inner edge 42 of a securing plate 4 is accommodated in a groove 2100 of the rotor base part 2, which is formed by an overhang 210 projecting in the radially outer direction ra.
  • the securing plate 4 ensures that the individual rotor blades 3a, 3b are secured axially on the rotor base part 2 in the region of their respective blade root 32, which is at least partially covered by a securing plate 4 (cf figure 3 ).
  • the overhang 310 blocks the blade root 32 from being pushed through a fastening groove 20 .
  • the overhang 310 cannot be pushed over the webs 22 of the rotor base part 2 lying opposite one another and bordered laterally by a fastening groove 20 .
  • the radial would have to be here Extension of the blade root 32 and thus the length of a blade neck 320 are increased, so that a lower edge of the overhang 310 consistently runs radially further outwards than the end of the webs 22. But this would be accompanied by an increase in the weight of a moving blade 3a, 3b.
  • the additional assembly advantage can be realized in the embodiment variant of a solution according to the invention without a weight disadvantage.
  • Illustrated variant is the shape of the recessed edge portions 311a and 311c compared to the variant of FIG Figures 1A to 1C varies.
  • An overhang 310 on a blade base 31 is profiled so that the two edge sections 311a and 311b of a rotor blade 3a or 3b, which are spaced apart from one another along the circumferential direction U, are in the radially outer direction ra opposite the middle, third edge section 311b of the overhang 310 of the respective rotor blade 3a or 3a 3b are designed to be set back radially.
  • the individual recessed edge sections 311a and 311c each have areas of constant radial extension along the circumferential direction U.
  • each of the recessed edge portions 311a, 311c of a blade Figures 2A and 2 B at least one area in which a height of the respective recessed edge section 311a, 311c does not decrease in the circumferential direction U or in the opposite direction thereto.
  • a machining manufacturing process or thermal material removal can be provided for the production of the reduced edge sections 311a, 311c on a rotor blade 3a or 3b.
  • the withdrawn edge portions 311a and 311c in the embodiment of Figures 1A to 1C can be made comparatively easily by grinding.
  • a profiled version corresponding to the variant of Figures 2A and 2 B can be produced, for example, by eroding.
  • the recessed edge sections 311a and 311c can be produced in one operation with (not shown here) Damper pockets or other functional areas are made on the blades 3a, 3b, which are usually also made by eroding.
  • the locking plate 4 has a central region 40 lying between the radially inner and radially outer edges 42 and 43 . From the figure 4 shows in particular how a radially outer edge 43 of the locking plate 4 is received in the groove 3100 of the blade base 31 of a moving blade 3b and encompassed by the radially inwardly extending overhang 310, while the central region 40 extends outside of the groove 3100 along the blade root 32 extends.

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

Claims (13)

  1. Rotor pour un mécanisme d'entraînement (T), comprenant
    - une partie de base de rotor (2), qui présente des rainures de fixation (20) pour des aubes mobiles (3a, 3b) agencées les unes derrière les autres le long d'une direction périphérique (U) autour d'un axe de rotation (M),
    - plusieurs aubes mobiles (3a, 3b) maintenues chacune par complémentarité de forme dans une rainure de fixation (20) correspondante par l'intermédiaire d'un pied d'aube (32) et
    - au moins un élément de blocage (4) pour le blocage axial, par rapport à l'axe de rotation (M), d'au moins l'une des aubes mobiles (3a, 3b) sur la partie de base de rotor (2),
    l'au moins un élément de blocage (4) présentant deux bords (42, 43) espacés radialement l'un de l'autre, par l'intermédiaire desquels l'élément de blocage (4) est maintenu par complémentarité de forme d'une part sur la partie de base de rotor (2) et d'autre part sur l'au moins une aube mobile (3a, 3b) et, pour la complémentarité de forme avec l'aube mobile (3a, 3b), l'un des bords (43) de l'élément de blocage (4) étant entouré, au moins dans une zone, par un surplomb (310) de l'aube mobile (3a, 3b), qui s'étend à cet effet radialement vers l'intérieur par rapport à l'axe de rotation (M), au-delà de l'un des bords (43) de l'élément de blocage (4) et le long de la direction périphérique (U),
    une rainure de fixation (20) définissant à chaque fois un espace entre deux entretoises (22) de la partie de base de rotor (2), et
    le surplomb (310) présentant, le long de son extension dans la direction périphérique (U), au moins une section de bord (311a, 311c) entourant le bord (43) de l'élément de blocage (4), qui est en retrait dans une direction (ra) dirigée radialement vers l'extérieur sur un bord inférieur du surplomb (310) situé radialement vers l'intérieur par rapport à au moins une autre section de bord (311b) du surplomb (310) entourant également le bord (43) de l'élément de blocage (4),
    caractérisé en ce que
    le surplomb (310) présente deux, première et deuxième, sections de bord (311a, 311c) qui sont prévues chacune, par rapport à la direction périphérique (U), à une extrémité du surplomb (310) et qui sont chacune en retrait par rapport à au moins une autre, troisième section de bord (311b) du surplomb (310), entourant également le bord (43) de l'élément de blocage (4), dans une direction (ra) orientée radialement vers l'extérieur, de telle sorte que le pied d'aube (32) et un bord inférieur du surplomb (310) peuvent être glissés à travers l'espace dans la partie de base de rotor (2) lorsque l'élément de blocage (4) n'est pas encore ou n'est plus monté.
  2. Rotor selon la revendication 1, caractérisé en ce qu'au moins l'une des première et deuxième sections de bord en retrait radialement vers l'extérieur (311a, 311c) présente une extension réduite dans la direction (ri) orientée radialement vers l'intérieur.
  3. Rotor selon la revendication 1 ou 2, caractérisé en ce qu'au moins l'une des première et deuxième sections de bord en retrait radialement vers l'extérieur (311a, 311c) forme une zone sur le bord inférieur radialement intérieur qui s'étend au moins partiellement de manière inclinée vers la direction périphérique (U).
  4. Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce qu'au moins l'une des première et deuxième sections de bord en retrait radialement vers l'extérieur (311a, 311c) s'étend le long de la direction périphérique (U) avec une longueur (a1, a2) qui correspond au moins au triple d'une hauteur (b1, b2) avec laquelle la section de bord en retrait radialement vers l'extérieur (311a, 311c) est en retrait maximal par rapport à la troisième section de bord adjacente (311b) du surplomb (310).
  5. Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce qu'au moins l'une des première et deuxième sections de bord en retrait radialement vers l'extérieur (311a, 311c) est en retrait par rapport à la troisième section de bord adjacente (311b) du surplomb (310) d'au moins une hauteur (b1, b2) de 0,5 mm, notamment d'au moins une hauteur (b1, b2) de 0,8 mm ou 1 mm.
  6. Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce que les deux sections de bord en retrait (311a, 311c) sont en retrait de manière différente et/ou s'étendent le long de la direction périphérique (U) avec des longueurs (a1, a2) différentes l'une de l'autre.
  7. Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce que les première et deuxième sections de bord en retrait radialement vers l'extérieur (311a, 311c) sont prévues à des extrémités du surplomb (310) espacées l'une de l'autre le long de la direction périphérique (U).
  8. Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce que l'une des première et deuxième sections de bord en retrait radialement vers l'extérieur (311a, 311c) est en retrait par rapport à la troisième section de bord adjacente (311b) du surplomb (310) d'au moins la somme des tolérances de forme et de position prédéterminées de cette troisième section de bord (311b), une position nominale de la troisième section de bord (311b) par rapport à la rainure de fixation (20) correspondante et/ou par rapport à un surplomb (310) d'une aube mobile (3b, 3a) voisine du rotor étant prédéterminée par les tolérances de forme et de position.
  9. Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce que, sur au moins deux aubes mobiles (3a, 3b) du rotor, agencées au voisinage l'une à l'autre le long de la direction périphérique (U), des surplombs sont prévus avec des sections de bord (311a, 311c) adjacentes les unes aux autres et chacune en retrait radialement vers l'extérieur, de telle sorte que, dans la zone des sections de bord (311a, 311c) adjacentes les unes aux autres des deux aubes mobiles (3a, 3b) voisines, un renfoncement (33) dirigé radialement vers l'extérieur, ayant une longueur minimale et une hauteur minimale définies, est formé.
  10. Rotor selon la revendication 9, caractérisé en ce que le renfoncement (33) est de forme elliptique, de forme trapézoïdale ou de forme triangulaire lorsqu'il est vu le long de l'axe de rotation (M).
  11. Rotor selon la revendication 9 ou 10, caractérisé en ce que, le long de la direction périphérique (U), sur chaque paire d'aubes mobiles (3a, 3b) agencées au voisinage l'une à l'autre, des surplombs sont prévus avec des sections de bord (311a, 311c) adjacentes les unes aux autres et chacune en retrait radialement vers l'extérieur, de telle sorte que, le long de la direction périphérique (U), dans la zone des sections de bord (311a, 311c) adjacentes les unes aux autres de deux aubes mobiles (3a, 3b) voisines, un renfoncement (33) dirigé radialement vers l'extérieur, ayant une longueur minimale et une hauteur minimale définies, est formé.
  12. Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce que l'au moins une section de bord en retrait radialement vers l'extérieur (311a, 311c) est réalisée par enlèvement de matière mécanique ou thermique.
  13. Rotor selon l'une quelconque des revendications précédentes, caractérisé en ce que l'au moins un élément de blocage (4) est prévu pour le blocage axial d'au moins deux aubes mobiles (3a, 3b) et l'un des bords (43) de l'élément de blocage (4) est ainsi entouré par des surplombs (310) d'au moins deux aubes mobiles (3a, 3b).
EP17166817.1A 2016-04-20 2017-04-18 Rotor comprenant un porte à faux sur les pales pour un élément de sécurité Active EP3236011B1 (fr)

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US10704400B2 (en) * 2018-10-17 2020-07-07 Pratt & Whitney Canada Corp. Rotor assembly with rotor disc lip
US11168615B1 (en) 2020-08-25 2021-11-09 Raytheon Technologies Corporation Double ring axial sealing design
KR102454379B1 (ko) * 2020-09-08 2022-10-14 두산에너빌리티 주식회사 로터 및 이를 포함하는 터보머신

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DE102016107315A1 (de) 2017-10-26
EP3236011A1 (fr) 2017-10-25
US20170306771A1 (en) 2017-10-26
US10526904B2 (en) 2020-01-07

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