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EP3236011B2 - 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
EP3236011B2
EP3236011B2 EP17166817.1A EP17166817A EP3236011B2 EP 3236011 B2 EP3236011 B2 EP 3236011B2 EP 17166817 A EP17166817 A EP 17166817A EP 3236011 B2 EP3236011 B2 EP 3236011B2
Authority
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
Other languages
German (de)
English (en)
Other versions
EP3236011B1 (fr
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
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
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Publication of EP3236011B2 publication Critical patent/EP3236011B2/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—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
    • F01D5/02—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
    • 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
    • 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 rotor known, for example, from US 5,256,035 A known rotor has a rotor base part which has fastening slots for rotor blades arranged one behind the other along a circumferential direction around a rotation axis. 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 held in a form-fitting manner on at least one of the rotor blades at a radially outer edge and in a form-fitting manner on the rotor base part at 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 in the rotor base part, so that a radially outwardly extending overhang of the rotor base part engages around the radially inner edge of the plate segments.
  • the fastening ring is in turn received in a groove which is formed on a blade base of a rotor blade.
  • a radially inwardly extending overhang of the blade base engages around the radially outer edge of the fastening ring, which also secures a plate segment which is arranged adjacent to and in the axial direction next to the fastening ring.
  • the rotor 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.
  • Figures 5A , 5B , 5C and 5D only two sections are shown in each case, looking along the rotation axis 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 a radially inward direction ri.
  • the blade base 31 of a rotor blade 3a or 3b forms an overhang 310 extending radially inwards, i.e. along the radial direction ri pointing towards them.
  • a radially outer edge 43 of a securing plate 4 is encompassed by this overhang 310.
  • Several (at least two) rotor blades 3a and 3b are secured in the axial direction to the rotor base part 2 in the area 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 rotor blade 3a, 3b known from the prior art each forms an overhang 310 for enclosing the radially outer edge 43 of the securing plate 4, which is formed over a total length L along the circumferential direction U as a continuous straight or circular arc-shaped edge 311.
  • the respective overhangs 310 of adjacent edges 311 of a pair of rotor blades 3a and 3b arranged adjacent to one another should thus be aligned with 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 Due to permissible tolerances, it can happen that the individual overhangs 310 of adjacent rotor blades 3a, 3b are radially offset from each other.
  • 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.
  • Figure 5B which offsets one (left) blade 3b radially inwards relative to the adjacent (right) blade 3a.
  • the one overhang 310 of one blade 3b thus projects into an annular gap flow in the circumferential direction U (offset "into wind”).
  • one (left) blade 3b is offset radially outwards from the other (right) blade 3a (out of wind offset).
  • the edge 311 of the overhang 310 of one blade 3b is thus completely offset from the overhang 310 of the other rotor blade 3a is offset radially outwards.
  • 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.
  • undesirable turbulence can occur in the area of adjacent blade bases 31 and thus adjacent overhangs 310.
  • the invention is based on the object of improving a rotor in this respect.
  • a rotor with a specially designed overhang on at least one rotor blade that is positively connected to the rotor base part is proposed.
  • the overhang has two first and second edge sections along its extension in the circumferential direction, each of which is provided at one end of the overhang in relation to the circumferential direction and is each set back in a radially outward direction relative to at least one further third edge section of the overhang that also encompasses the edge of the securing element, such that the blade root and a lower edge of the overhang can be pushed through the gap in the rotor base part if the securing element is not yet or no longer attached.
  • Overhangs with edge sections that adjoin one another and are each set back radially outwards are provided on at least two rotor blades of the rotor that are arranged adjacent to one another along the circumferential direction. In this way, a radially outward-facing recess of a defined minimum length and minimum height is then formed in the area of the adjoining edge sections of two adjacent rotor blades. At the radial recess, an interruption of a circular path of the edges of the individual overhangs that follow one another along the circumferential direction is thus deliberately provided.
  • the overhang of at least one rotor blade in a rotor according to the invention is withdrawn or set back at a lower edge of the overhang in a radially outward direction such that the overhang at a radially inner lower edge does not have a straight or circular 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 extent decreases continuously in the circumferential direction and thus defines a region of the lower edge of the overhang that runs obliquely to the circumferential direction.
  • regions that are radially offset from one another and/or run at an angle to one another are formed on a radially inner lower edge of an overhang.
  • a setback is thus defined from the outset, preferably in the region of adjacent overhangs. This can lead to minimizing or avoiding disruptive turbulence in the region of the securing element, particularly with appropriate dimensioning. Furthermore, this makes it possible to reduce weight and simplify the assembly and/or disassembly of a rotor blade.
  • the latter can be achieved by the at least one recessed edge section being 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 can have a smaller extension in the radially inward direction than an adjacent edge section.
  • the overhang therefore extends less radially inward in the region of the recessed edge section.
  • at least one of the first and second radially outwardly recessed edge sections is provided at an end of the overhang lying in the circumferential direction. In this way, a defined recess is provided via the recessed edge section in the region where two adjacent rotor blades adjoin one another with their blade bases.
  • At least one of the first and second radially outwardly recessed edge sections forms a region on the radially inner lower edge of the overhang, which is at least partially inclined to the circumferential direction.
  • the recessed edge section can therefore not only be designed to step back to an adjacent edge section of the overhang, but can also form a recess that continuously increases or decreases in size in the circumferential direction, at least in sections.
  • the at least one radially outwardly recessed edge section extends with a length along the circumferential direction of the rotor that corresponds to at least three times, in one variant at least four times, a height with which the radially outwardly recessed edge section is (at least) recessed relative to an adjacent edge section of the overhang.
  • the at least one edge section which is set back radially outwards is set back by at least a height of 0.5 mm, in particular by at least a height of 0.8 mm or 1 mm, relative to an adjacent edge section of the rotor blade overhang.
  • a recess is thus formed in the recessed edge section which, when two adjacent rotor blades are nominally aligned, has a maximum depth of at least 0.5 mm, 0.8 mm or 1 mm.
  • 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 direction relative 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 along the circumferential direction and spaced apart from one another, but are each set back radially outward relative to at least one third edge section of the rotor blade overhang.
  • the two recessed edge sections can be recessed to different degrees and/or extend along the circumferential direction with different lengths.
  • the overhang of a rotor blade can thus be designed asymmetrically with respect to a radial direction. This enables, for example, a direction-of-rotation optimized design of a recess formed by two edge sections of two adjacent rotor blades that are adjacent to one another and each recessed radially outwards.
  • first and second radially outwardly recessed edge sections of a rotor blade are provided at 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 section of a (first) rotor blade overhang and a first edge section of another (second) rotor blade overhang thus adjoin one another in the case of adjacent rotor blades and adjacent blade bases.
  • At least one of the first and second edge sections that are set back radially outwards is set back relative to the adjacent third edge section of the rotor blade overhang by at least the sum of the shape and position tolerances of this third edge section.
  • a set-back first or second edge section thus forms a recess that, when two adjacent rotor blades are nominally aligned, has a maximum (radial) depth of at least the sum of the shape and position tolerances of the third edge section.
  • the shape and position tolerances are used to specify 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 rotor blade of the rotor.
  • a recess defined in the area of the blade bases of two adjacent rotor blades is, for example, elliptical, trapezoidal or triangular in a view along the axis of rotation.
  • Overhangs with adjacent edge sections that are each set back radially outwards can be provided on each pair of adjacent rotor blades along the circumferential direction of the rotor, so that a radially outward-facing recess of a defined minimum length and minimum height is formed along the circumferential direction in the area of adjacent edge sections of two adjacent rotor blades.
  • the formation of a recess is therefore not limited to individual pairs of rotor blades, but is provided throughout every area of two adjacent rotor blades.
  • At least one of the first and second radially outwardly recessed edge sections can be produced, for example, by mechanical material removal. This includes production by a machining manufacturing process, such as grinding or milling. In such a variant, material can therefore be removed in a targeted manner, for example ground off, from the overhang of a rotor blade base in order to ensure that a radially inner lower edge of the overhang no longer has a straight line.
  • an edge section that is set back radially outwards can be produced by thermal material removal.
  • the production takes place by means of erosion.
  • the (thermal) material removal on the overhang to produce a set-back edge section takes place in one operation with the production of certain functional areas on a rotor blade.
  • a functional area such as a damper pocket or a blade base area provided with at least one recess to reduce weight, to be produced on a rotor blade in the area of the blade base by erosion.
  • the overhang of a rotor blade can then also be machined accordingly in order to provide an edge section that is recessed radially outwards.
  • the at least one securing element can be provided for the axial securing of at least two rotor blades.
  • a securing element preferably in the form of a plate, is then encompassed at one (radially outer) edge by the overhangs of at least two rotor blades.
  • the Figure 6 illustrates schematically and in cross-section 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 inlet direction E by means of a fan F.
  • This fan F is driven by a shaft which is set in rotation by a turbine TT.
  • the turbine TT is connected to a compressor V which, for example, has 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 on the one hand and to a bypass channel B on the other hand to generate 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 for this purpose.
  • the turbine TT uses the energy released during combustion to drive the fan F, which then generates the required thrust using the air fed into the bypass channel 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 out.
  • the outlet A usually has a thrust nozzle.
  • At least one rotor comes into contact with the Figures 5A to 5D
  • the configuration shown is used.
  • the rotor is arranged and mounted so that it can rotate around the central axis or rotation axis M, that the individual the circumferential direction U for axially securing the rotor blades 3a, 3b, securing plates 4 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 area of the blade roots 32 of the individual rotor blades 3a, 3b between the rotor and a guide vane arrangement 6.
  • the flow arising in this annular space 5 can - as explained in the introduction - be undesirably swirled in a configuration of the overhangs 310 of the blade bases 31 used to connect the rotor blades 3a, 3b and a securing element 4 if individual overhangs 310 are offset from one another due to tolerances. Then individual overhangs 31 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 outwards for this purpose (see Figures 5B and 5C ).
  • an overhang 310 which is provided for a positive connection with a radially outer edge 43 of a multi-part or one-part securing element, such as a securing plate 4, is designed 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 predictably.
  • several recesses distributed along the circumferential direction U are 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 radially outwardly recessed edge sections 311a and 311c. 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 of a rotor blade 3a or 3b inserted into the associated fastening groove 20 (cf. the individual illustration of a rotor blade 3a of the Figure 1D ).
  • the length of the third edge portion 311b along the circumferential direction U amounts to less than 60%, possibly 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 each of 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 a region of the lower edge of the overhang 310 that runs at an angle to the circumferential direction U.
  • Each recessed edge section 311a, 311c runs from the middle, third edge section 311b at an angle outwards towards the respective end, so that a radial extension of the respective recessed edge section 311a or 311c decreases steadily towards the respective lateral edge of the overhang 310.
  • the individual edge sections 311a and 311c are each set back up to a height b1 or b2 relative to the middle edge section 311b.
  • This height b1 or b2 is in the present case greater than 0.8 mm and amounts to approximately 1 mm.
  • the extension in the circumferential direction U of the respective set-back 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 set-back edge section 311a, 311c.
  • This radial recess 33 is dimensioned over 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. This means that a (relevant) flow influence due to the offset g is excluded or minimal (compare Figure 1B ).
  • the recessed edge sections 311a and 311c of course still provide a sufficient extension of the overhang 310 in the radially inner direction ri, so that a groove 3100 for the encompassed radially outer edge 43 of the securing plate 4 is also present in the region of a recessed edge section 311a or 311c.
  • the radially inner edge 42 of a securing plate 4 is in a groove 2100 of the rotor base part 2, which is formed by a projection 210 protruding in the radially outer direction ra.
  • the securing plate 4 ensures that the individual rotor blades 3a, 3b are axially secured to 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 (see also Figure 3 ).
  • the recessed edge sections 311a and 311c also ensure that the overhang 310 extends further radially inwards with the edge section 311b lying between them along the circumferential direction U only in the area in which the fastening groove 20 is located.
  • the edge section 311b which projects further radially inwards is thus dimensioned such that the blade root 32 can be pushed in the axial direction through the fastening groove 20 and the gap defined thereby between two webs 22 of the rotor base part 2 if the securing plate 4 is not yet or no longer attached. This is possible with an overhang of constant radial extension in accordance with the Figure 5D not possible.
  • the blade root 32 is blocked from being pushed through a fastening groove 20 by the overhang 310.
  • the overhang 310 cannot be pushed over the opposing webs 22 of the rotor base part 2, which laterally border a fastening groove 20.
  • the radial extent of the blade root 32 and thus the length of a blade neck 320 would have to be increased so that a lower edge of the overhang 310 runs radially further out than the end of the webs 22.
  • this would entail an increase in the weight of a rotor blade 3a, 3b.
  • the additional assembly advantage can be achieved in the illustrated embodiment of a solution according to the invention without a weight disadvantage.
  • each of the recessed edge sections 311a, 311c of a rotor blade of the Figures 2A and 2B at least one region in which a height of the respective recessed edge portion 311a, 311c does not decrease in the circumferential direction U or opposite thereto.
  • this ensures that a recess 33 defined in the area of the blade bases 31 of two adjacent blades 3a, 3b in the view along the axis of rotation of the Figure 2 is trapezoidal, while the recess 33 in the variant of the Figures 1A to 1C is triangular. If the lower edges of the recessed edge sections 311a, 311c are more rounded, an elliptical recess can also be formed in a possible further development.
  • a machining process or thermal material removal may be used to produce the recessed edge sections 311a, 311c on a rotor blade 3a or 3b.
  • the recessed edge sections 311a and 311c in the embodiment of the Figures 1A to 1C can be produced relatively easily by grinding.
  • a profiled version according to the variant of the Figures 2A and 2B can be produced, for example, by erosion.
  • the production of the recessed edge sections 311a and 311c can be carried out in one operation with damper pockets (not shown here) or other functional areas on the rotor blades 3a, 3b, which are usually also produced by erosion.
  • the design of the securing plate 4 is shown separately.
  • the securing plate 4 has a central region 40 located between the radially inner and radially outer edges 42 and 43. From the Figure 4 It is particularly evident how a radially outer edge 43 of the securing plate 4 is received in the groove 3100 of the blade base 31 of a rotor blade 3b and is encompassed by the radially inwardly extending overhang 310, while the central region 40 extends outside the groove 3100 along the blade root 32.

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

Claims (12)

  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, et
    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.
  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 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).
  10. Rotor selon l'une quelconque des revendications précédentes, 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.
  11. 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.
  12. 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 EP3236011B2 (fr)

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DE102016107315.6A DE102016107315A1 (de) 2016-04-20 2016-04-20 Rotor mit Überhang an Laufschaufeln für ein Sicherungselement

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US10526904B2 (en) 2020-01-07
DE102016107315A1 (de) 2017-10-26
US20170306771A1 (en) 2017-10-26
EP3236011B1 (fr) 2022-08-31
EP3236011A1 (fr) 2017-10-25

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