EP3612721B1 - Procédé de construction d'anneaux à aubes pour turbomachine radiale - Google Patents

Procédé de construction d'anneaux à aubes pour turbomachine radiale Download PDF

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Publication number
EP3612721B1
EP3612721B1 EP18715806.8A EP18715806A EP3612721B1 EP 3612721 B1 EP3612721 B1 EP 3612721B1 EP 18715806 A EP18715806 A EP 18715806A EP 3612721 B1 EP3612721 B1 EP 3612721B1
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EP
European Patent Office
Prior art keywords
annular body
blades
cylindrical block
teeth
axial section
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Application number
EP18715806.8A
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German (de)
English (en)
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EP3612721A1 (fr
Inventor
Stefano SALGAROLLO
Dario RIZZI
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Exergy International SRL
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Exergy International SRL
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Priority to HRP20211991TT priority Critical patent/HRP20211991T1/hr
Publication of EP3612721A1 publication Critical patent/EP3612721A1/fr
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    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material

Definitions

  • the object of the present invention is a method for the construction of bladed rings for radial turbomachinery, a bladed ring and a bladed disc obtained by means of said method.
  • Radial turbomachinery means a turbomachine in which the flow of fluid with which it exchanges energy is directed in a radial direction for at least a part of the path followed in the turbomachine itself.
  • the radial part of the path is delimited by at least one annular series of blades through which the fluid moves prevalently along a radial direction relative to an axis of rotation of the turbomachine.
  • a "bladed ring” comprises a plurality of blades arranged equally spaced from a central axis and joined to one another by two or more concentric rings axially spaced from one another.
  • the blades extend between two rings with their leading and trailing edges turned radially towards the inside and towards the outside, respectively, (centrifugal radial ring) or vice versa (centripetal radial ring).
  • the aforementioned leading and trailing edges may be parallel or substantially parallel to the central axis or curved (twisted blades).
  • the bladed ring can have either a stator function (it is fixed with respect to a casing of the turbomachine and its blades are stator blades) or a rotor function (i.e. it rotates and its blades are rotor blades and therefore the central axis is the axis of rotation of the turbomachine).
  • a "bladed disc” comprises a plurality of annular series of blades fixed onto a front face of a disc.
  • the series are concentric and each series comprises a plurality of blades arranged at equal distances from a central axis of the disc.
  • the blades extend away from the front face with their leading and trailing edges parallel or substantially parallel to the central axis.
  • the bladed disc further comprises a plurality of reinforcement rings, each connected to all the blades of an annular series at one end of said blades opposite the one connected to the front face of the disc.
  • the bladed disc can also have either a stator function (it is also called a stator plate, it is fixed with respect to a casing of the turbomachine and its blades are stator blades) or a rotor function (it is also called a rotor disc, it rotates together with the turbomachine shaft and its blades are rotor blades and therefore the central axis is the axis of rotation).
  • a stator function it is also called a stator plate, it is fixed with respect to a casing of the turbomachine and its blades are stator blades
  • a rotor function it is also called a rotor disc, it rotates together with the turbomachine shaft and its blades are rotor blades and therefore the central axis is the axis of rotation.
  • a bladed disc can be seen as being formed by a plurality of concentric bladed rings fixed onto a support disc.
  • the present invention applies both to centrifugal radial turbomachines (out-flow) and centripetal radial turbomachines (in-flow).
  • the present invention is applied both to drive turbomachines (turbines) and work turbomachines (compressors).
  • the present invention relates to expansion turbines.
  • the present invention relates to expansion turbines used in plants for the production of electrical and/or mechanical energy (power plants).
  • Published document GB 652 591 illustrates a bladed ring for radial turbines, in which the blades can be made in a single piece with a respective reinforcement ring.
  • Public document US 4,306,833 illustrates a compressor with an impeller provided with a disc having two annular series of blades arranged at a peripheral zone and each on one of the faces of the disc itself.
  • the blades of each series extend in a respective annular chamber.
  • the disc with the blades can be realised through die casting.
  • a ring is applied against each end of the blades of a series, to eliminate leaks due to the formation of vortexes at said ends.
  • Each ring is fixed to the impeller through screws inserted in bosses fashioned on the impeller.
  • Public document US 6,508,631 illustrates a radial flow pump.
  • the pump comprises a rotor and a plurality of blades arranged in concentric rings and extending from a first face of the rotor in a substantially parallel direction to a central axis of rotation.
  • the rotor and the blades may be formed by a single block of material.
  • a support ring that reduces deflection due to the centrifugal force may be arranged around the blades.
  • Public document US-2011/041334 discloses a process for manufacturing a single-piece blisk.
  • the Applicant perceived the need to improve the known methods for the construction of bladed rings for radial turbomachinery, in particular with a similar structure to those illustrated in the previous documents WO 2014/064567 and WO 2015/140711 , so as to speed up their production and reduce costs, while ensuring high quality such as to guarantee the reliability and efficiency of the turbomachinery in which they are installed.
  • the Applicant has noted that in the solutions that envisage the realisation of rotor bladed rings by direct joining between the blades and the support rings, as in WO 2014/064567 , it is more difficult to separate the stresses due to the centrifugal force from those due to the weight of the blades.
  • the Applicant has noted that the internal circumferential stresses due to centrifugal force have their points of maximum concentration at the connecting zones with the blades, in particular at the outlet edges thereof. These zones of maximum concentration of the stresses are structurally dangerous.
  • the Applicant has found that the above-indicated and other objectives can be attained by realising blades of a ring from the blank, i.e. by removal of material from a starting block, in which the blades are sketched by dividing a cylindrical block in half through a wavy circumferential cut.
  • the present invention relates to a method for the construction of bladed rings for radial turbomachines, comprising:
  • the adjective “axial” means a definition of a direction running parallel to a central axis of the bladed ring or axis of rotation "X-X” of the turbomachine.
  • the adjective “radial” is meant as a definition of a direction directed in radius-fashion perpendicularly from the central axis of the bladed ring or axis of rotation "X-X” of the turbomachine.
  • the adjective “circumferential” is meant as a definition of directions tangential to circumferences coaxial to the central axis of the bladed ring or the axis of rotation "X-X” of the turbomachine.
  • the leading edge faces radially towards the inside (centrifugal radial turbomachine) or towards the outside (centripetal radial turbomachine) and the trailing edge faces radially towards the outside (centrifugal radial turbomachine) or towards the inside (centripetal radial turbomachine).
  • Cylindrical block means a ring-shaped element comprising a single piece and not formed by various parts. Such cylindrical block may be a stand-alone element or may be part of a more complex element, such as a rotor disc that has on a face thereof one or more cylindrical blocks integrated into the rotor disc.
  • Wild circumferential cut means a cut that passes through the thickness of the wall that defines the cylindrical body and that extends all around the cylindrical body along a wavy trajectory. The cut, therefore, identifies two plurality of teeth being complementary or counter-shaped to each other. A midline of said wavy trajectory is a circle coaxial to the central axis. Once completed, the wavy circumferential cut is necessarily a through cut so as to be able to divide the first annular body from the second annular body but it can be performed in various steps and possibly also with different methods.
  • the Applicant has verified that the present invention allows the realisation times of a radial bladed ring to be considerably reduced.
  • the method allows the outline of the blades to be sketched (first plurality of teeth and second plurality of teeth) simultaneously on both annular bodies by making a single cut (wavy circumferential cut).
  • the present invention allows the process necessary for obtaining blades to be simplified.
  • the space around each tooth necessary for processing it in order to define the aerodynamic profile is much larger than the available space if all the blades were realised on a single annular body.
  • the stock to be removed in order to achieve the final shape of the blade is small compared to that to be removed in the realisation of the blades from the blank.
  • the present invention allows the waste material deriving from processing to be reduced to a minimum, in particular with respect to the realisation of the blades on two distinct annular bodies (two cylindrical blocks) from the blank and therefore the costs connected with the disposal and/or recycling thereof.
  • the Applicant has also verified that the present invention allows the quantity of the starting material to be reduced and therefore the costs, weight and difficulty of any transport and/or management of the semi-processing starting part(s).
  • the Applicant has also verified that the present invention allows savings to be made on the tools for the rough processing of the blades and machines with lower costs to be used for the roughing step (which is less precise in itself) because their performance is lower in terms of achievable tolerances.
  • the Applicant has also verified that the present invention allows good quality bladed rings and discs to be realised and therefore to ensure the reliability and efficiency of the radial turbomachines in which they are installed.
  • the cylindrical block is a stand-alone element.
  • the cylindrical block is an integral part of a starting disc and is arranged on a front face of said starting disc.
  • the starting disc comprises a plurality of concentric cylindrical blocks arranged on the front face.
  • the first annular body is still part of the starting disc.
  • the cylindrical block may be a stand-alone element and a bladed ring for radial turbomachines can be fashioned therefrom or one or more cylindrical blocks are integral parts of a disc and from the assembly a bladed disc for radial turbomachines bearing one or more bladed rings can be fashioned.
  • cylindrical block or the disc provided with one or more cylindrical blocks is made by moulding, preferably by forging.
  • the cylindrical block before performing the wavy circumferential cut, the cylindrical block is roughed.
  • the roughing is performed by turning.
  • the roughing envisages removing material to define a first axial section, a second axial section and a third axial section. Said axial sections are defined by respective circular portions of the cylindrical block axially flanked.
  • the first axial section defines a base ring.
  • the first axial section also defines a resiliently yielding ring.
  • the first axial section defines a connecting foot placed at a terminal end of the resiliently yielding ring.
  • the third axial section defines a reinforcement ring.
  • the wavy circumferential cut is performed in the second axial section.
  • the second axial section is the one intended to generate the blades.
  • the wavy circumferential cut passes through a wall constituting said cylindrical block.
  • the wavy circumferential cut is performed through abrasive water jet (AWJ).
  • AAWJ abrasive water jet
  • the wavy circumferential cut is performed through laser and/or electro discharge machining - sinker EDM and/or wire cut EDM and/or plasma and/or oxy cutting.
  • the wavy circumferential cut is performed through the mechanical removal of chips.
  • the wavy circumferential cut is performed in one or more steps/phases.
  • the wavy circumferential cut crosses the cylindrical block along radial directions.
  • the wavy circumferential cut in at least some stretches, crosses the cylindrical block along tangent directions to virtual circumferences coaxial to the cylindrical block.
  • the wavy circumferential cut is performed in part through interrupted cuts performed starting from a radially internal surface of the cylindrical block and in part through interrupted cuts performed starting from a radially outer surface of the cylindrical block.
  • Interrupted cut means a cut that penetrates into the material of the cylindrical block without exiting from the opposite side, i.e. it is not a through cut.
  • the wavy circumferential cut has the shape of a square wave.
  • each tooth has, in a front view, a substantially polygonal outline, e.g. substantially quadrilateral, preferably substantially parallelogram shaped.
  • the number of teeth of the first plurality is equal to the number of teeth of the second plurality.
  • the number of teeth of the first plurality is different from the number of teeth of the second plurality.
  • removing material from each of the teeth of the first plurality and of the second plurality comprises: roughing each tooth to define in a front view an outline proximal to that of a blade, preferably but not necessarily substantially polygonal. In other words, starting from the quadrilateral, material is removed to realise an outline, for example but not necessarily a polygon, closer to the definitive outline of the blade.
  • the roughing of each tooth is performed by removing blocks of material.
  • the blocks are removed from the tooth with a quadrilateral section to confer to it the polygonal section.
  • the blocks are removed from the tooth to confer to it an outline that traces the shape of the blade but with stock to be removed in a subsequent finishing step.
  • the roughing of each tooth is performed through abrasive water jet and/or laser and/or mechanical removal of chips and/or electro discharge machining and/or sinker EDM and/or wire cut EDM and/or plasma and/or oxy cutting.
  • removing material from the first plurality and the second plurality comprises: performing a finishing step until the tooth is conferred the aerodynamic outline of the blade.
  • the finishing of each blade is performed through the mechanical removal of chips and/or electrical discharge machining and/or electrochemical machining - ECM.
  • coaxially jointing the first annular body with the second annular body comprises: joining terminal ends of the first blades to the second annular body.
  • each first blade is inserted between two second blades until a terminal end of the first blade is brought against a bottom surface of the second annular body lying between the two second blades.
  • coaxially jointing the first annular body with the second annular body comprises: joining terminal ends of the second blades to the first annular body.
  • each second blade is inserted between two first blades until a terminal end of the second blade is brought against a bottom surface of the first annular body lying between the first two blades.
  • coaxially jointing the first annular body with the second annular body comprises: fixing terminal ends of the first blades to the second annular body.
  • coaxially jointing the first annular body with the second annular body comprises: fixing terminal ends of the second blades to the first annular body.
  • terminal ends of the first blades are fixed to the second annular body and/or the terminal ends of the second blades are fixed to the first annular body through screws and/or pins.
  • a leading edge and/or a trailing edge of said first blade extend parallel or substantially parallel to a central axis of the first annular body.
  • a leading edge and/or a trailing edge of said second blade extend parallel or substantially parallel to a central axis of the second annular body.
  • a leading edge and/or a trailing edge of said first blade have a curved profile (twisted blades).
  • a leading edge and/or a trailing edge of said second blade have a curved profile (twisted blades).
  • the present invention relates to a bladed ring for radial turbomachines realised according to one or more of the aspects listed above and/or according to one or more of the appended claims and/or embodiments illustrated below.
  • the present invention relates to a bladed disc for radial turbomachines comprising one or more bladed rings according to the previous aspect.
  • the bladed rings are realised individually and then joined to a support disc.
  • a starting disc is prepared integrating one or more concentric cylindrical blocks arranged on the front face of the starting disc and realising the bladed ring(s) from said one or more concentric cylindrical blocks.
  • the present invention relates to a radial turbomachine comprising at least one bladed ring and/or a bladed disc according to the preceding aspect.
  • the bladed ring is a rotor ring.
  • the bladed ring is a stator ring.
  • the radial turbomachine is a centrifugal or centripetal radial turbine, preferably with a single rotor disc or with two counter-rotating rotor discs.
  • reference numeral 1 denotes in its entirety a radial turbomachine.
  • the radial turbomachine 1 illustrated in figure 1 is an expansion turbine of a radial centrifugal type (out-flow) with a single rotor 2.
  • the turbine 1 can be used in the sector of plants for generation of electrical energy of the Rankine cycle type, either organic Rankine Cycle (ORC) or water vapour, or even other types of cycles with different work fluids.
  • ORC organic Rankine Cycle
  • the turbine 1 comprises a fixed casing 3 in which the rotor 2 is housed so as to be able to rotate.
  • the rotor 2 is rigidly connected to a shaft 4 which extends along a central axis "X-X" (which coincides with an axis of rotation of the shaft 4 and of the rotor 2) and is supported in the fixed casing 3 by appropriate bearings 5.
  • the rotor 2 comprises a rotor disc 6 connected to the aforementioned shaft 4 and provided with a front face 7 and an opposite rear face 8.
  • the rotor disc 6 is of the overhung type, i.e. it is connected in a cantilever fashion to an end of the shaft 4.
  • the front face 7 of the rotor disc 6 bears in a cantilever fashion a plurality of rotor bladed rings 9 that are concentric and coaxial to the central axis "X-X".
  • the fixed casing 3 comprises a front wall 10, located opposite the front face 7 of the rotor disc 6, and a rear wall 11, located opposite the rear face 8 of the rotor disc 6.
  • the front wall 10 has an opening defining an axial inlet 12 for a work fluid.
  • the axial inlet 12 is located at the central axis "X-X" and is circular and concentric to the same axis "X-X”.
  • the fixed casing 3 further has a transit volute 13 of the work fluid located in a radially peripheral position external to the rotor 2 and in fluid communication with an outlet, not illustrated, from the fixed casing 3.
  • stator bladed rings 14 that are concentric and coaxial to the central axis "X-X".
  • the stator bladed rings 14 extend inside the casing 3 towards the rotor disc 6 and are radially alternated with the rotor bladed rings 9 to define a radial path of expansion of the work fluid which enters through the axial inlet 12 and expands moving radially away towards the periphery of the rotor disc 2 up to entering into the transit volute 13 and then exiting from the fixed casing 3 through said outlet, not illustrated.
  • the rotor bladed rings 9 and the stator bladed rings 14 are structurally similar to one another.
  • the structure of the rotor disc 6 is described below, as is an example of a method for the construction of the bladed rings 9 of the rotor disc 6. The same method can also be used for realising the stator rings 14.
  • such method is used to build bladed rings and discs (stator and/or rotor) for radial turbomachines.
  • the bladed ring 9 comprises a first support ring 15 or base ring intended to be anchored to the front face 7 of the rotor disc 6.
  • the base ring 15 has a first annular central body 16, which in the above-mentioned section is rectangular or square, from which an annular anchoring appendage 17 extends axially on one side and comprises a resiliently yielding ring 18 which terminates with a connecting foot 19.
  • the resiliently yielding ring 18 is directly connected to the base ring 15 and the connecting foot 19 is positioned at an end of the resiliently yielding ring 18 opposite the first annular central body 16.
  • the resiliently yielding ring 18 enables a radial deformation thereof when subjected to loads (centrifugal force, temperature) of the turbomachine when operating.
  • the connecting foot 19 is configured for stably engaging in an appropriate seating, not illustrated, fashioned in the rotor disc 6.
  • the bladed ring 9 comprises a second support ring 20 or reinforcement ring.
  • Figure 2 illustrates the section, in an axial plane, of the reinforcement ring 20.
  • the second support ring 20 has a second annular body 21, which in the above-mentioned section is rectangular or square.
  • the bladed ring 9 comprises a plurality of blades 22', 22" with an aerodynamic profile that extend between the base ring and the reinforcement ring 15, 20.
  • the base ring and the reinforcement ring 15, 20 are coaxial and axially spaced from one another.
  • Each blade 22', 22" of the illustrated example has a leading edge 23 and a trailing edge 24 parallel to the central axis "X-X" of the bladed ring 9.
  • the illustrated turbomachine 1 is a centrifugal radial turbine in which the work fluid moves radially towards the outside, the leading edge 23 of each blade 22', 22" radially faces towards the inside, i.e. towards said central axis "X-X", and the trailing edge 24 faces radially towards the outside.
  • the blades 22', 22" are arranged equally spaced from the central axis "X-X" and circumferentially spaced by a constant pitch from one another.
  • Each blade 22', 22" has a first axial end and a second axial end that are opposite and respectively connected to the base ring 15 and to the reinforcement ring 20.
  • the method according to the present invention for the realisation of the bladed ring 9 envisages starting from a cylindrical block "M” made of forged metal which in figure 3 is illustrated as a stand-alone element. A half-section of the cylindrical block "M”, sectioned by the radial plane IV of figure 3 , is illustrated in figure 4 in broken lines.
  • the cylindrical block "M” is first subjected to rough turning through which material is removed until a first axial section 25, a second axial section 26 and a third axial section 27 are defined.
  • the axial sections 25, 26, 27 are defined by respective circular portions of the cylindrical block "M” axially flanked and forming a single body ( figure 4 ).
  • the first axial section 25 defines the base ring 15, which in this step may be practically already finished, and the resiliently yielding ring 18 with the connecting foot 19.
  • the blades 22', 22" will be fashioned from the second axial section 26, as will be described in detail in the following.
  • the third axial section 27 defines the reinforcement ring 20.
  • the rough turning can be followed by finish turning.
  • the cylindrical block "M” has the reinforcement ring 20 practically already finished, the second axial section with a radial thickness slightly less than the radial thickness of the first 25 and third 27 axial section, the base ring 15 also practically already finished, the resiliently yielding ring 18 and the connecting foot 19.
  • the second axial section 26 has a radial thickness slightly less than the first 25 and the third 27 axial section adjacent thereto, respective steps are defined both on a radially internal surface and on a radially outer surface of the semi-processed cylindrical block "M".
  • the lower thickness of the second axial section 26 allows less material to be cut and furthermore to have less material removed during the blade finishing step, according to what is described below.
  • a wavy circumferential cut 28 is performed, which extends along the entire circumference of said second axial section 26.
  • the cut is performed through abrasive water jet (AWJ) and has, seen on a radially outer surface of the axial section 26, a square wave outline with peaks and troughs arranged at the mentioned steps.
  • the cut can be performed through laser or mechanical removal of chips (or also sinker EDM, wire cut EDM, plasma, oxy cutting).
  • the wavy circumferential cut 28 extends in a zig-zag fashion between the two steps. Peaks and troughs of the wavy cut are defined by circumferential stretches of the cut parallel to the two steps and connected to each other by axial stretches parallel to each other.
  • the wavy circumferential cut 28 passes through the wall of the second axial section 26 of the cylindrical block "M".
  • the aforementioned axial stretches of the cut extend along directions “T” and in tangent planes to virtual circumferences coaxial to the cylindrical block "M", as illustrated in figure 5 .
  • the aforementioned stretches of the cut parallel to the two steps extend in substantially perpendicular planes to the central axis "X-X” or slightly inclined with respect to a perpendicular plane to said central axis "X-X".
  • the through cuts belonging to the wavy circumferential cut 28 delimit in the thickness of the second axial section 26 shapes that resemble quadrilaterals. More precisely, each of said shapes is delimited by the radially outer surface of the second axial section 26, by the radially internal surface of the second axial section 26 and by two of the directions "T" tangent to virtual circumferences coaxial to the cylindrical block "M".
  • the wavy circumferential cut 28 therefore defines a first plurality of teeth 29 and a second plurality of teeth 30 meshing in one another and each having a parallelepiped outline with a substantially quadrilateral section.
  • each of the axial stretches of the wavy circumferential cut 28 is formed through a first cut performed starting from a radially outer surface of the second axial section 26 along a first direction "T1". Such first cut penetrates about half way into the thickness of the second axial section 26 (interrupted cut).
  • Each of the axial stretches of the wavy circumferential cut 28 is completed by performing a second cut in a radially internal surface of the second axial section 26 along a second direction "T2".
  • Such second cut penetrates about half way into the thickness of the second axial section 26 (interrupted cut) until it connects with the first cut.
  • each of the circumferential stretches of the wavy cut is formed through a first cut performed starting from the radially outer surface of the second axial section 26 and through a second cut performed in the radially internal surface of said second axial section 26.
  • the teeth 29, 30 may also have different outlines.
  • the cuts may be performed on radial planes.
  • the wavy circumferential cut 28 further divides the cylindrical block "M" into a first annular body 31 provided with the first plurality of teeth 29 and into a second annular body 32 provided with the second plurality of teeth 29.
  • the first annular body 31 and the second annular body 32 are separated from one another by distancing them axially as illustrated in figure 7 .
  • the first annular body 31 therefore comprises the base ring 15 with the first plurality of teeth 29 and the resiliently yielding ring 18 with the connecting foot 19.
  • the second annular body 32 comprises the reinforcement ring 20 with the second plurality of teeth 30.
  • the first annular body 31 and the second annular body 32 may be processed separately.
  • Each tooth 29 of the first plurality is processed by removing material to confer to said tooth 29 the outline with the aerodynamic profile of a first blade 22'.
  • Each tooth 30 of the second plurality is processed by removing material to confer to said tooth 30 the outline with the aerodynamic profile of a second blade 22".
  • the available space between the teeth 29, 30 of each annular body 31, 32 is sufficient for processing the teeth 29, 30 easily and quickly, in particular since a small amount of stock is to be removed.
  • each tooth 29, 30 is first roughed by cutting and removing, through AWJ or through laser (or by sinker EDM, wire cut EDM, plasma, oxy cutting), blocks of material for defining, in a front view of the tooth 29, 30, a substantially polygonal outline that virtually contains the aerodynamic outline of the blade 22', 22" that it is to form ( figures 8 and 9 ).
  • the roughing of the blades is performed through electrodes with a rigid frame (hollow electrode) having the most appropriate shape.
  • Figure 8A shows the removal of material through a hollow electrode 100 so as to have a roughed shape of the blades 22 that traces the final shape of the blades but with a stock 101 to be removed later in the finishing step.
  • Such hollow electrode 100 is better illustrated in figure 8B and comprises a support foot 102 configured to be coupled to electrical discharge machining EDM equipment.
  • a frame extends from the support foot 102 and is defined by a frame made of wire-shaped or rod-shaped elements.
  • the frame comprises two curved rods 103, 104 and a rectilinear rod 105.
  • the frame delimits/surrounds, together with the support foot 102, a window/opening/passage 106 which, seen from the front, is substantially rectangular but which lies on a curved surface, the one in which the two curved rods 103, 104 lie.
  • the support foot 102 therefore delimits a side of the window 106.
  • the roughing of the blades is performed through wire or rigid electrodes but not closed in a frame.
  • the electrode has a single wire-shaped or rod-shaped element with an outline like one 104 of the curved rods of figure 8A (without the other curved rod 103 and without the rectilinear rod 105) or comprises one 104 of the curved rods and the rectilinear rod 105 of figure 8A but not the second curved rod 103.
  • each tooth is finished by removing further material until it is conferred the aerodynamic outline of the blade 22', 22" ( figures 8 and 9 , broken lines).
  • the finishing of each blade 22', 22" can be performed through the mechanical removal of chips and/or EDM. In the latter case, one or more electrodes counter-shaped to the aerodynamic outline of the blade 22', 22" to be obtained can be used.
  • Bottom surfaces 33', 33" placed between adjacent blades 22', 22" respectively of the first annular body 31 and of the second annular body 32 and head surfaces of the blades 22', 22", where the stock is present, are subjected to finishing, e.g. through EDM, milling, ECM.
  • holes 34 are performed ( figure 10 ), threaded or not, configured to receive connecting elements, such as screws or pins not illustrated.
  • the holes 34 in the first annular body 31 and in the second annular body 32 pass axially through the first support ring 15 and the second support ring 20, respectively.
  • a terminal end, in particular the head surface, of each blade 22', 22" is finished and processed to perform a hole 35 ( figure 10 ), threaded or not, configured to receive the aforementioned connecting elements.
  • the first annular body 31 and the second annular body 32 are positioned coaxially (the central axes "X-X", “Y-Y” coincide) opposite one another and moved towards each other by advancement along the central axes "X-X", "Y-Y” (arrows F1 and F2 in figure 10 ) so as to insert the first blades 22' between the second blades 22".
  • Head surfaces of the first blades 22' are approached or brought against the bottom surfaces 33" of the second annular body 32 and head surfaces of the second blades 22" are moved towards each other or brought against the bottom surfaces 33' of the first annular body 31 so as to arrange the holes 34 in the bottom surfaces 33', 33" in alignment with the holes 35 on the head surfaces.
  • the insertion and tightening of the screws, not illustrated, in the holes 34, 35 allows the first annular body 31 to be jointed coaxially with the second annular body 32.
  • the bladed rotor disc 6 of figure 1 is obtained by mounting a plurality of bladed rings realised as described above on the front face 7 of said rotor disc 6 through the engagement of the connecting feet 19 in appropriate seatings, not illustrated in detail.
  • the concentric bladed rings are realised in part as integrating parts of the bladed disc 6.
  • each cylindrical block "M1, M2" is an integral part of a starting disc “D” and is arranged on a front face of said starting disc “D”.
  • the wavy circumferential cut 28', 28" performed in every cylindrical block “M1, M2" determines the separation of the second annular bodies 32', 32" from the starting disc “M1, M2" while the first annular bodies 31', 31" remain integrated into the disc.
  • the connecting foot 19 is absent because the first annular bodies 31', 31" are conceived as integrated parts in the starting disc "D".

Landscapes

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

Claims (12)

  1. Procédé de construction d'une couronne aubagée pour turbomachine radiale, comprenant :
    la préparation d'au moins un bloc cylindrique (M ; M1, M2) ;
    la fabrication dans le bloc cylindrique (M ; M1, M2) d'une découpe circonférentielle ondulée (28, 28', 28") définissant une première pluralité de dents (29) et une seconde pluralité de dents (30) s'engrenant l'une dans l'autre ; la découpe circonférentielle ondulée (28, 28', 28") partageant le bloc cylindrique (M ; M1, M2) en un premier corps annulaire (31 ; 31', 31") pourvu de la première pluralité de dents (29) et en un second corps annulaire (32 ; 32', 32") pourvu de la seconde pluralité de dents (30) ;
    la séparation du premier corps annulaire (31 ; 31', 31") du second corps annulaire (32 ; 32', 32") ;
    l'élimination de matière de chacune des dents (29) de la première pluralité pour conférer à ladite dent (29) le contour d'au moins une première aube (22') ayant un profil aérodynamique ;
    l'élimination de matière de chacune des dents (30) de la seconde pluralité pour conférer à ladite dent (30) le contour d'au moins une seconde aube (22") ayant un profil aérodynamique ;
    la jonction de manière coaxiale du premier corps annulaire (31 ; 31', 31") au second corps annulaire (32 ; 32', 32") par l'insertion des premières aubes (22') entre les secondes aubes (22").
  2. Procédé selon la revendication 1, sur une surface radialement externe du bloc cylindrique (M ; M1, M2), la découpe circonférentielle ondulée (28, 28', 28") ayant la forme d'une onde carrée.
  3. Procédé selon la revendication 1 ou 2, la découpe circonférentielle ondulée (28, 28', 28") passant à travers le bloc cylindrique (M ; M1, M2) le long des sens radiaux ou des sens tangents aux circonférences virtuelles coaxiales par rapport audit bloc cylindrique (M ; M1, M2).
  4. Procédé selon la revendication 1, 2 ou 3, chaque dent (29, 30) présentant un contour sensiblement polygonal en une vue de face.
  5. Procédé selon l'une des revendications précédentes 1 à 4, comprenant, avant la fabrication de la découpe circonférentielle ondulée (28 ; 28', 28"), le dégrossissage du bloc cylindrique (M ; M1, M2) par élimination de matière pour définir une première section axiale (25), une seconde section axiale (26), une troisième section axiale (27), la première section axiale (25) définissant un anneau de base (15), la troisième section axiale (27) définissant un anneau de renforcement (20), la découpe circonférentielle ondulée (28 ; 28', 28") étant fabriquée dans la seconde section axiale (26).
  6. Procédé selon l'une des revendications précédentes 1 à 5, l'élimination de matière de chacune des dents (29, 30) de la première pluralité et de la seconde pluralité comprenant : le dégrossissage de chaque dent (29, 30) et ensuite la réalisation d'une finition pour donner à la dent (29, 30) le contour aérodynamique de l'aube (22', 22").
  7. Procédé selon la revendication précédente, le dégrossissage de chaque dent (29, 30) étant réalisé en retirant des blocs de matière.
  8. Procédé selon l'une des revendications précédentes 1 à 7, la jonction de manière coaxiale du premier corps annulaire (31 ; 31', 31") au second corps annulaire (32 ; 32', 32") comprenant la fixation d'extrémités terminales des premières aubes (22') au second corps annulaire (32 ; 32', 32") et la fixation d'extrémités terminales des secondes aubes (22") au premier corps annulaire (31 ; 31', 31").
  9. Procédé selon l'une des revendications précédentes 1 à 8, la découpe circonférentielle ondulée (28 ; 28', 28") étant réalisée par jet d'eau abrasif ou laser.
  10. Procédé selon l'une des revendications précédentes 1 à 9, le bloc cylindrique (M ; M1, M2) étant une partie intégrale d'un disque de démarrage (D) et étant disposé sur une face avant dudit disque de démarrage (D), après la séparation, le premier corps annulaire (31 ; 31', 31") faisant encore partie dudit disque (D).
  11. Procédé selon la revendication 10, le disque de démarrage (D) comprenant une pluralité de blocs cylindriques (M1 ; M2) disposés de manière concentrique sur la face avant.
  12. Procédé selon l'une des revendications précédentes de 1 à 9, le bloc cylindrique étant un élément autonome.
EP18715806.8A 2017-03-14 2018-03-12 Procédé de construction d'anneaux à aubes pour turbomachine radiale Active EP3612721B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
HRP20211991TT HRP20211991T1 (hr) 2017-03-14 2018-03-12 Postupak konstrukcije prstenova sa oštricama za radijalne turbostrojeve

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT102017000028266A IT201700028266A1 (it) 2017-03-14 2017-03-14 Metodo per costruire anelli palettati per turbomacchine radiali
PCT/IB2018/051607 WO2018167632A1 (fr) 2017-03-14 2018-03-12 Procédé de construction d'anneaux à aubes pour turbomachine radiale

Publications (2)

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EP3612721A1 EP3612721A1 (fr) 2020-02-26
EP3612721B1 true EP3612721B1 (fr) 2021-10-06

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Country Link
EP (1) EP3612721B1 (fr)
DK (1) DK3612721T3 (fr)
ES (1) ES2901098T3 (fr)
HR (1) HRP20211991T1 (fr)
IT (1) IT201700028266A1 (fr)
LT (1) LT3612721T (fr)
WO (1) WO2018167632A1 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB652591A (en) * 1948-01-27 1951-04-25 Svenska Turbinfab Ab Improved blade ring for radial flow elastic fluid turbines or compressors
FR2929152B1 (fr) * 2008-03-31 2010-04-23 Snecma Procede ameliore de fabrication d'un disque aubage monobloc, avec anneau provisoire de maintien des aubes retire apres une etape de finition par fraisage
ITUA20162126A1 (it) * 2016-03-30 2017-09-30 Exergy Spa Metodo per la costruzione di dischi palettati per turbomacchine radiali e disco palettato ottenuto tramite tale metodo

Also Published As

Publication number Publication date
WO2018167632A1 (fr) 2018-09-20
HRP20211991T1 (hr) 2022-03-18
DK3612721T3 (da) 2022-01-10
EP3612721A1 (fr) 2020-02-26
ES2901098T3 (es) 2022-03-21
LT3612721T (lt) 2021-12-27
IT201700028266A1 (it) 2018-09-14

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