• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Element of a turbomachine axial compressor stator, which is a one-piece unit of outer shape in a cylinder sector radially outer forming an outer ferrule sector (46a) common to several sectors of axial blade stages radial straighteners (481,482483) secured radially externally of said outer ferrule sector and radially inner per stage of an inner platform sector (521,522,523), each inner platform sector stage being radially innerly connected to a first sealing means sector of first sealing means (561, 562, 563) each adapted to sealingly engage said second sealing means connected to a compressor rotor shaft; axial.
    公开号:FR3033602A1
    申请号:FR1552035
    申请日:2015-03-11
    公开日:2016-09-16
    发明作者:Emilie Herny；Jean-Francois Rideau；Moataz Attallah
    申请人:Safran Power Units SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to the field of turbomachines, in particular that of gas turbine engines intended for the propulsion of aircraft. The invention relates to a rectifier or a rectifier element for an axial turbomachine compressor. In known manner, an axial compressor comprises a series of axial stages arranged in series, each comprising a moving impeller (rotor) and a stator paddle (rectifier). Each stage is defined to adapt its operating conditions to those of the stages upstream and downstream. The upstream is where originates the flow of gas flowing downstream into the compressor.
    [0002] The moving blade (rotor) typically comprises a circular disk on which blades (fins) are fixed and rotates in front of the fixed blade (of the straightener). The span of the fins varies along the flow to compensate for variations in the density of the fluid and to maintain at the axial flow rate a more or less constant value. Thus, the rotor, with moving blades, sucks and accelerates the flow of gas by deviating from the axis of the motor, the stator that follows, straightens the flow to the axis and slows down by transforming a part its speed under pressure, and so on alternately, from floors to floors.
    [0003] The rectifier stages are manufactured in the manner of unitary rings by conventional methods using fusible materials. The lead times for obtaining these parts are often long and the processes are often expensive. Typically, the manufacturing is done by foundry. Each floor then requires to invest in a specific mold because the size of the blades is different from one floor to another.
    [0004] In addition, the materials commonly used are high-density materials, of the iron-based or nickel-based type. However, these alloys are not necessarily justified in view of the temperature levels and stresses intended to be applied to the rectifiers, operating turbomachine. Moreover, the aforementioned drawbacks can be considered all the more troublesome if the parts concerned are parts of prototyping and development. It is in this context, and at least to overcome some of these drawbacks, that here is proposed a rectifier element, for an axial turbomachine compressor, this rectifier element, which extends around an axis. , being characterized in that it is in the form of a one-piece assembly of external shape, generally, in a cylinder sector forming, radially externally, an outer ring sector 15 common to several axial stage sectors (that is, that is to say, axially staggered) integral radial straightener vanes: radially outermost of said outer ferrule sector, and, radially inner, per stage, of an inner platform sector, each platform sector stage. wherein the inner means is radially inwardly connected to a sector of first sealing means adapted to seal said second sealing means to said gas. A priori and in practice, these second sealing means will be connected to a rotor shaft of the axial compressor via connecting support walls bearing these second sealing means. By convention, we will call "radial" in the present description which is radial to the aforementioned axis (of the compressor) and axial which extends along this axis. In order to promote consideration of the above-mentioned problems of high density, iron-based or nickel-based materials, and foundry fabrications, it is advisable that the material constituting the rectifier element includes an aluminum-based alloy adapted for use in an additive manufacturing process, such as powder-bed laser melting. The A2OXTM alloy (based on Al-4 (YoCu) from the manufacturer "Aeromet 5 International PLC" is in particular concerned here for its qualities of dimensional stability and its mechanical properties up to 300 ° C. An aspect also taken into account concerns the final assembly of the compressor, with its various successive stages of stators and rotors, as part of an optimized manufacturing of these rectifier elements, which is why the aforementioned rectifier element is provided: is in the form of a one-piece assembly of externally hemi-cylindrical outer shape, and comprises three axial stages of sectors of radial straightening vanes integral with each said stage of an inner (individual) platform sector. sectorized, it will be possible to obtain: - both one or more axial sections of a rectifier each comprising several rectifier elements of the aforementioned type, gathered circumferentially the compressor axis, thereby forming a generally cylindrical outer shape assembly; a turbomachine axial compressor rectifier as such, comprising a plurality of such axial sections joined axially along said axis; . And with all or some of the foregoing considerations, it will furthermore be possible to propose an axial turbomachine compressor, comprising: a rectifier of the aforementioned type, or a plurality of rectifier elements 30 joined together circumferentially, and 3033602 4-a set rotor extending about said axis and comprising a series of axially aligned rotor wheels, each wheel comprising a disk carrying an annular row of radial rotor blades, each row being mounted between two successive stages of radial straightening vanes.
    [0005] As indicated above, the obtaining of a turbomachine axial compressor, or a section of this compressor, can be favorably achieved with the following steps: along the axis which will be that of the compressor, transversely to this axis and between the successive stages of sector (s) 10 of radial straightening vanes, engaging a first portion of the annular rows of radial vanes of the rotor assembly, then mounting around another part of said annular rows of radial blades not so engaged, another cylinder sector of at least one other rectifier element, and so on until the outer shroud completely surrounds said blades. The assembly will be more modular. Time and cost savings are expected. As regards the manufacture of the rectifier element, it is furthermore proposed that it be carried out by an additive manufacturing process, favorably a laser melting / SLM process based on the melting of a metal powder. . Such a manufacturing process also known as "Laser Fusion on Powder Bed" makes it possible to obtain parts in a direct manufacturing mode, which does not require the use of any foundry mold and which makes it possible to obtain a part requiring a minimum of machining operations. In this respect, the possible heat and / or final surface treatments are independent of the additive manufacturing process, but depend on the material. One can not a priori free oneself from it. In connection with this process, it is also expected that said metal powder will be obtained after atomization EIGA (Ar / Electrode Induction-Melting Gas Atomization). This atomization technique is specific for obtaining reactive alloy powder (such as aluminum alloys). Other details, characteristics and advantages of the solutions presented here will become apparent on reading the description which follows, given by way of nonlimiting example with reference to the accompanying drawings, in which: FIG. 1 schematically shows in longitudinal local section; (Axis 19 below) an internal part of a prior art aerospace turbomachine, at a compressor, which can be a high pressure compressor; FIGS. 2, 3 are two diagrammatic perspective views, from two different angles, of a semicylindrical rectifier element for an axial turbomachine compressor; FIG. 4 shows in perspective, with an exploded view, part of one of said 15 rectifier elements between the blades of which have been different rows of rotating radial vanes of a rotor assembly to achieve the expected compressor. FIG. 1 shows a conventional compressor 10 of an aircraft turbine engine, which may be a jet engine or an airplane turboprop, as disclosed in FR2997128. The compressor 10 comprises rectifying vanes 12 between which rotor wheels 14 are mounted. Each wheel 14 comprises a disc 17 carrying an annular row of substantially radial vanes, the discs of the wheels 14 being fixed to each other by support walls 16 of 25 link, which can be annular. The walls 16 may be substantially cylindrical. All the discs of the wheels 14, and therefore the support walls 16 of connection, are further connected to a shaft 18 connected itself, further downstream, to at least one turbine for their driving in rotation about a central axis 30 19 defining a longitudinal axis of the engine. Thus, the wheels 14 are rotated together, about the axis 19, through the 3033602 6 of the shaft 18 and 16 connecting support walls that transmit the movement. The straightening vanes 12 may be variable-pitch vanes in the first two stages of compression, and vanes fixed in the other 5 stages of compression. Each stator vane, at least those vane fixed in Figure 1, comprises two coaxial annular walls, respectively internal 20 and external 22, between which extend substantially radial vanes 24. The straightening vanes 12 are carried by an outer casing 26 and surround the aforementioned connecting walls 16 of the discs of the wheels 14. The outer wall 22 of each of these vanes 12 may comprise fastening hooks to an outer casing and its inner wall. A ferrule 28 carries an abradable material 30 for cooperating with external annular wipers 32 of the corresponding wall 16 to form a labyrinth type seal. The vein 34 which, for channeling the upstream gas (AV) downstream (AV), extends within the compressor 10 is delimited radially externally by the outer annular wall 22 and, radially interior, by the inner annular wall 20.
    [0006] FIGS. 2, 3 show two elements, respectively 36, 38, of a rectifier 40 for an axial turbomachine compressor. The rectifier 40 is intended to replace the marked rectifier portion 42 in FIG. 1. Each rectifier element 36, 38 extends around a same axis 44 which will become the axis 19, compressor mounted. And each of these rectifier elements 36, 38 is in the form of an integral one-piece assembly in cylinder sector, generally. Each of these cylinder sectors forms, radially externally, an outer ferrule sector, respectively 46a, 46b and 2, which are common to several axial stage sectors of radial straightening vanes, respectively and successively, 481,482,483 and 501, 502, 503 These radial rectifier vanes are integral, radially externally, with the outer ferrule sector, respectively 46a, 46b FIGS. 2 and 3, and, radially internally, per stage, with an internal platform sector, respectively, and successively, 521,522,523 and 541,542,543. It will be understood that with reference to FIG. 1 and for the angular sector concerned, the outer shell, for example 46a, may be substituted for the relevant part of the outer wall 22, while the internal platform sectors 521, 522, 523 may be substituted for the relevant parts of the internal walls 20, and axial stage sectors of radial straightening vanes 481,482,483 to the stator vanes 24 concerned. In addition, each of these inner platform sector stages, 521,522,523 and 541,542,543, is radially inwardly connected to a sector of first sealing means, respectively and successively 561,562,563 and 581,582,583 each adapted to engage sealingly. the first and second sealing means 561, 562, 563 and 581, 582, 583 may each comprise an abradable structure, for example based on the gas, of the second sealing means of a rotor shaft of the axial compressor, such as the outer annular wipers 32 of FIG. honeycomb. And the connection between each inner platform sector stage and one of the sectors of the first sealing means, such as 561, 581, 582, can be achieved by a generally radial ring sector wall (here more or less frustoconical). , such as the wall 593 between the parts 523 and 563 FIG. 2. Applied in particular to a high-pressure turbine engine compressor, as illustrated in FIG. 1 where the compressor 10 is axially interposed between a low-pressure compressor, upstream, and a chamber Downstream, the material constituting this compressor 10 will be favorably an aluminum-based alloy adapted to a temperature withstand up to 300 ° C. The A2OXTM alloy from the manufacturer "Aeromet International PLC" is thus recommended, all the more so if, as recommended, the compressor elements, such as 36.38, are manufactured by laser melting (Selective Laser Melting / SLM), as known in itself, the A2OXTM alloy is based on Al-4% Cu. Details concerning him are available in the thesis submitted in September 2011 at the School of Engineering of the University of Birmingham, by Mr. PHILIP BALE entitled "FEEDING PROPERTIES OF THE HIGHLY GRAIN REFINED A2OX ALLOY (properties of the very fine grain alloy A20X) and accessible via the link: http://etheses.bham.ac.uk/3327/1/Bale 12 MRes.pdf Its chemical composition (in% weight) is a priori the following: Ag B Cu Fe Mg Si Ti V Al 0.70 1.33 4.07 0.02 0.07 0.26 0.05 3.17 0.04 90.29 SLM laser melting is a process that enables the rapid fabrication of prototypes and semi-finished parts from a CAD model. This process consists in densifying locally, with a CO2 or Nd-YAG laser beam, a material presented in the form of a powder, here based on metal, the thermal contribution of this beam in the infrared is used to melt the powder according to a scanning algorithm generated by the CAM software. to achieve the fusion of matter under the effect of the laser beam. The difference between the two lasers lies mainly in the wavelength: the CO2 laser typically has a wavelength of 10.6 μm whereas that of the Nd-YAG laser is 1.06 μm. The power of the laser is generally between 50 and 500 W. The method can use a machine having two platforms powered by an interdependent piston system. One of the 30 platforms may comprise a bench filled with metal powder, the other then serves as a support for the manufacture of the piece.
    [0007] 3033602 9 The part is manufactured layer by layer by means of the laser that reproduces the CAD drawing. The powder can be fed layer by layer by means of a scraper which transfers a controlled amount and thickness from one platform to the other.
    [0008] The manufacturing solution can then be favorably as follows: a) Prepare a 3D CAD file of the rectifier (in three dimensions whose design has been computer assisted) with a structure of associated supports to support the part during its construction. This support structure is generated by specific software. B) use the powder-bed laser melting machine to construct the part, which will comprise two half-shells in the example of FIGS. c) once the part is built, the supports must be removed. A heat treatment type T6 (dissolution, quenching, tempering) will favorably follow the manufacture by direct laser melting, in order to obtain the desired mechanical strength. d) the components are then subjected to a final finishing treatment, of sandblasting or vibratory type, and preferably a resumption of finishing machining. It will be noted that the embodiment in two half-shells will make it possible to optimize the design time of the elements 36, 38, while at the same time allowing a module fabrication, preferably by laser melting, and a transverse placement of the elements of rotor as detailed below. The powder used in the laser melting process will be favorably obtained after atomization EIGA (Electrode Induction- Melting Gas Atomization / Electrode Atomization and Induction Melting, under gaseous atmosphere). This atomization technique is specific for obtaining reactive alloy powder, such as aluminum alloys, including A2OXTM. To optimize firstly the laser melting of each modular rectifier element, it is furthermore recommended that each of them: be a monobloc assembly of externally hemi-cylindrical outer shape, like the two elements 36, 38, and - comprises, as illustrated in FIGS. 2.3, three axial stages of sectors 5 of integral radial straightener vanes, on each floor, of a said internal platform sector, such as 521, 522, 523. -quesquels that rectifier elements 36,38 is a one-piece assembly of outer shape in cylinder sector, overall, it will be easy to achieve: 10 - an axial rectifier section comprising several such elements 36,38 circumferentially assembled around said axis 44, to form a set of outer shape of revolution, generally cylindrical, - or a complete rectifier 40 axial compressor turbomachine hine, comprising several axial sections united axially along said axis.
    [0009] It will thus be understood that, gathered around the common axis 44, the two elements 36, 38 can indifferently define an axial section of a rectifier or a complete rectifier 40. For this purpose, it is envisaged that, if we consider the example of the two rectifier hemi-cylindrical elements 36, 38, here generally identical, each outer shell sector 46a, 46b has substantially in the section plane P of each half-cylinder passing through the axis 44, lateral flanges, respectively 47a, 47b, 49a, 49b adapted to be arranged face to face in pairs, in this plane P, and to receive through them fastening means reciprocals, such as that schematized in FIG. 3 (bolt) which must engage in the two orifices through which the two vertical axes illustrated in FIGS. At axial ends, each outer ferrule sector, 46a, 46b, furthermore has, substantially perpendicularly to the plane of section P, transverse flanges, respectively 53a, 53b, 55a, 55b. These transverse flanges are adapted to be disposed opposite other structures, such as transverse flanges of another coaxially arranged strut section and which could be identical to the section 40, assuming that it is considered that the mark 40 corresponds to a rectifier section. Like the lateral flanges, each transverse flange is adapted to receive through it fastening means, such as that shown schematically in FIG. 3 (bolt) which must engage with the orifice through which the axis 3. With regard to the turbomachine axial compressor 60, it can be shown as diagrammed in part in FIG. 4 where the rectifier 40 comprises four stages of radial stator vanes (here 61, 63, 65, 67), the along the axis 44.
    [0010] Thus, this compressor may comprise: either several rectifier elements, such as 36, 38, thus joined circumferentially end to end around the axis 44, to form the above-mentioned assembly of generally cylindrical outer shape, or the aforementioned complete rectifier 40 and a rotor assembly 62 extending about said axis 44 for rotation about it, and thus comprising a series of axially aligned rotor wheels 64, 66, 68, each wheel, such as that 64, comprising a disk 70 carrying a annular row of radial rotor blades 72, each row being mounted between two successive stages of radial straightening vanes.
    [0011] It will be understood that, overall, this rotor assembly 62 can be made as shown in FIG. 1, the axis 19 then replacing the axis 44. Now concerning the mounting of such an axial turbomachine compressor, or of a compressor section, it is recommended to proceed as follows: - along said axis (44), in the successive free spaces established between the stages of sector (s) of radial straightening vanes 61,63,65,67 figure 4, engage, transversely to this axis, a first portion of the various annular rows of radial vanes 72 of the rotor assembly, and then mount, around another part of said annular rows of these same radial rotor vanes, not so engaged, another sector of 3033602 12 cylinder of at least one other rectifier element, and so on until the outer shell, such 46a-46b, completely surrounds all said blades. It will have been understood that, if the compressor 40 comprises only the two half-shells 36, 38, the first step will make it possible to engage up to the immediate vicinity of the inner surface of the outer wall 46b of the first half. shell the radial vanes 72 of the rotor assembly about half the diameter of the ring which they define at their outer periphery, the second step of engaging the other half in the same interspaces, such as 76a, 76b figure 2, on the other two half-shell. 15
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Element of a rectifier for an axial turbomachine compressor, the rectifier element extending around an axis (44) and being characterized in that it is in the form of an integral one-piece assembly in a cylinder sector generally forming, radially outwardly, an outer ferrule sector (46a, 46b) common to a plurality of axial stage sectors of radially outer radial vanes (481, 462, 483, 501, 502, 503) integral with said ferrule sector. an internal platform sector (521522,523; 541,542,543), each inner platform sector stage being radially inwardly connected to a sector of first sealing means; (561, 562, 563; 581, 582, 583) each adapted to seal said gas of the second sealing means (32).
    [0002]
    The rectifier element (36, 38) according to claim 1, the constituent material of which comprises an aluminum-based alloy adapted for use in an additive manufacturing of said element, such as a fusion-based fabrication of a metal powder (SLM). 20
    [0003]
    3. Rectifier element according to claim 1 or 2, which: is a one-piece assembly of generally hemi-cylindrical outer shape, and comprises three axial stages of sectors of radial rectifying blades (481, 482, 483, 50, 502, 503) integral to each stage. of said inner platform sector (521, 522, 523, 541, 542, 543).
    [0004]
    4. Axial section of a rectifier comprising a plurality of rectifier elements (36,38) according to one of claims 1 to 3, circumferentially assembled about said axis, to form a generally cylindrical outer shape assembly. 3033602 14
    [0005]
    5. Rectifier for a turbomachine axial compressor, comprising a plurality of axial sections according to claim 4 joined axially along said axis.
    [0006]
    6. A turbomachine axial compressor, comprising: - a rectifier (40) according to claim 5, or several rectifier elements according to one of claims 1 to 3, gathered circumferentially about said axis, to form a generally cylindrical outer shape assembly and a rotor assembly (60) extending about said axis for rotation about and including a plurality of axially aligned rotor wheels (64,66,68), each wheel including a disk (70) bearing an annular array radial rotor blades (72), each row being mounted between two successive stages of radial straightening vanes (481, 482, 483, 501, 502, 503).
    [0007]
    7. A method of mounting the axial turbine engine compressor according to claim 6, or a turbomachine axial compressor section according to claim 4, the method comprising as steps: transverse to said axis, engage between the successive stages of sector (s). ) of radial straightening vanes (481, 482, 483, 501, 502, 503), a first part of the annular rows of the radial vanes (72) of the rotor assembly, - mounting, around another part of said annular rows of radial vanes of rotor not so engaged, another cylinder sector of at least one other rectifier element, and so on until the outer shell (46a, 46b) completely surrounds said blades (481, 482, 483; 501, 502, 503; 72).
    [0008]
    8. A method of manufacturing the rectifier element according to one of claims 1 to 3, by additive manufacturing.
    [0009]
    The method of claim 8, wherein said additive manufacturing comprises laser melting (SLM) based on melting of a metal powder. 3033602 15
    [0010]
    10. The method of claim 8 or 9, wherein said at least one metal powder is obtained after atomization EIGA (atomization by Ar gas electrode / Electrode Induction-Melting Gas Atomization). 5
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    同族专利:
    公开号 | 公开日
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    WO2016142631A1|2016-09-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB1263639A|1970-07-20|1972-02-16|Rolls Royce|Stator vane assembly for a fluid flow machine|
    EP1811131A2|2006-01-24|2007-07-25|Snecma|Set of fixed sectorised diffuser inserts for a turbomachine compressor|
    EP2204547A1|2008-12-29|2010-07-07|Techspace aero|Assembly for stator stage of a turbomachine, comprising an external annular shroud and at least one stator vane|
    US20120003086A1|2010-06-30|2012-01-05|Honeywell International Inc.|Turbine nozzles and methods of manufacturing the same|
    FR2997128A1|2012-10-24|2014-04-25|Snecma|Guide vane e.g. fixed guide vane for e.g. turbojet engine, of aircraft, has annular hook engaged on cylindrical edge of internal wall, and annular rib co-operating with support face of wall to prevent hook from being disengaged from wall|
    FR3004214A1|2013-04-08|2014-10-10|Snecma|STAGE TURBOMACHINE RECTIFIER|
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    CN109904437A|2019-02-22|2019-06-18|上海交通大学|Increasing material manufacturing aluminium-air cell anode material and preparation method thereof|
    DE102020108781A1|2020-03-30|2021-09-30|AM Metals GmbH|High-strength aluminum alloys for structural applications that can be processed using additive manufacturing|
    法律状态:
    2016-03-02| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-16| PLSC| Publication of the preliminary search report|Effective date: 20160916 |
    2017-02-10| PLFP| Fee payment|Year of fee payment: 3 |
    2017-08-04| CD| Change of name or company name|Owner name: SAFRAN POWER UNITS, FR Effective date: 20170703 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2019-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552035A|FR3033602B1|2015-03-11|2015-03-11|REALIZATION OF SEMI-MONOBLOCK RECTIFIER STAGES, BY ADDITIVE MANUFACTURE|FR1552035A| FR3033602B1|2015-03-11|2015-03-11|REALIZATION OF SEMI-MONOBLOCK RECTIFIER STAGES, BY ADDITIVE MANUFACTURE|
    PCT/FR2016/050546| WO2016142631A1|2015-03-11|2016-03-10|Production of half-stages of monobloc stator guides by additive manufacturing|
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