• 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:
    The present invention relates to a turbomachine comprising an annular heat exchanger (1), formed by an assembly of independent tubes assembled by holding means, and having a cylindrical cavity opening on the one hand on the outlet of the turbine, the tube assembly being housed in said cavity. The heat exchanger (1) is constituted by a first annular beam (5) and at least a second annular beam (6), coaxial with said first annular beam. An annular closure structure (8) defining an outer annular cavity in which the gases from said first bundle of tubes open to be deflected on a bottom towards an inner annular cavity, coaxial with the outer annular cavity, The invention also relates to an exchanger for such a turbomachine and a turbogenerator using such a turbomachine
    公开号:FR3059363A1
    申请号:FR1661539
    申请日:2016-11-25
    公开日:2018-06-01
    发明作者:Damien Fauvet
    申请人:Turbotech Ind；
    IPC主号:
    专利说明:

    Field of the invention
    The present invention relates to the field of on-board electrical (or mechanical) energy production from fuels for aeronautical, land, maritime and light mobile units by a system coupling a gas turbine to an alternator (electricity production) or a gas turbine with a power shaft (production of mechanical energy). In the context of the production of electrical energy, more particularly, the invention relates to equipment called range extender (in English "range extender").
    Applications of the “range extender” type are particularly suitable for the electric motorization of motor vehicles, corresponding to a strong trend, which also extends to aeronautical or maritime vehicles. For applications where the mass, volume and / or cost of the batteries are critical, the current performance of the batteries remains insufficient. To fly an electric aircraft with reasonable autonomy, it would be necessary to increase the mass energy of the most efficient batteries available in 2016 by a factor of 10, whereas in the last 20 years, the energy on board the batteries n 'increased only by a factor of 2.5.
    To remedy this situation, range extenders have been developed which make it possible to supply the power just needed in cruising mode - or even to deactivate the operation of the range extender when the power supplied by the batteries is sufficient, and to provide a increased power in transient phases (acceleration, high load, take-off and climb of an electric aircraft, ...).
    Different technologies have been implemented:
    - fuel cells whose reliability is not sufficient to date, whose price is very high and whose lifespan is short
    - back-up by photovoltaic cells (for example on the Solar Impulse 2 demonstrator (trademark)), a technology which remains too bulky and whose mass power is very low
    - internal combustion engine, or Wankel (trade name) driving a generator, which remains too bulky, and with poor performance.
    The most promising range extender solutions are based on the coupling of a microturbine equipped with a heat exchanger with an alternator (electric generator)
    State of the art
    It is known to use high power alternators which are connected to a line of shaft driven in rotation to supply electrical energy. The shaft line can for example be directly driven by a heat engine. The shaft line can also be driven by the high-speed circulation of a fluid, for example steam or gas. This circulation can in particular be obtained by heating the fluid, for example by using thermal energy or nuclear energy.
    To start the rotation of the shaft line, it is known to use the alternator in engine mode by supplying it from a static starting frequency converter and an excitation system. The excitation system and the converter are supplied by a first and a second dedicated transformer.
    By way of example, European patent EP1761736 discloses a microturbine motor coupled to an electric generator, comprising:
    a compressor providing a compressed air flow;
    - a recuperator receiving the compressed air flow from the compressor and heating the compressed air flow with the heat of an exhaust gas flow;
    - a combustion device receiving the heated flow of compressed air from the recuperator, mixing the flow of compressed air with fuel, and burning the mixture of fuel and compressed air to create the flow of exhaust gas;
    - At least one turbine receiving the flow of exhaust gas from the combustion device and rotating in response to the flow of exhaust gas, the rotation of the at least one turbine driving the compressor; and an electric generator generating electricity in response to the rotation of the at least one turbine;
    - the exhaust gas flowing from the at least one turbine to the recuperator used to heat the flow of compressed air;
    the recuperator including a plurality of cells, and the flow of compressed air flowing in the internal space of the cells through the inlet manifold pipes, then through the matrix lamellae, then through the outlet manifold pipes before flowing to the combustion device, and the flow of exhaust gas flowing through the recuperator and between the cells against the current with respect to the flow of compressed air passing through the matrix lamellae in the cells .
    Patent EP0746680 describes a gas turbine generator group which comprises a rotary group enclosed in a circumferential recuperator. The rotary group comprises an alternator-rotor situated on a common shaft provided with a turbine wheel and a paddle wheel, supported by thrust bearings with conformable sheets with double test and by a radial bearing with conformable leaves. The circumferential recuperator comprises a plurality of adjacent perforated sheets provided with bosses in order to structurally separate the sheets, the latter being arranged so as to form flow channels. The recuperator also includes collectors and a structure which makes it possible to have a differential pressure between each surface of the sheet. The circumferential recuperator consists of a unitary structure surrounding the rotary group and the combustion device in which the incoming air is heated by the recuperator before entering the combustion device. Due to the intercompatibility and modularity of the components, the air flow path associated with the discharge side of the compressor and the intake side of the turbine is formed during the installation of the rotary unit and the recuperator and by assembly end of the combustion device which forms a terminal enclosure for the intake air of the turbine.
    Also known from US patent US6657332 is a turbogenerator cooling system having a cylindrical heat sink provided with fins generally extending axially on both the inner and outer faces of a loop section. The loop section is full, with the exception of the orifices provided next to the rear end of said section. The generator stator is forced into the heat sink until it comes into contact with the internal fins. The generator rotor is equipped with a small fan to send hot air away from the engine intake port. Cooling air flows along the external fins to the end of the generator. This air flows through the openings in the loop section, passes again between the interior of the loop section and the exterior surface of the stator so as to cool the stator and along a different passage, so as to cool the hollow sleeve of the rotor and the permanent magnet rods as well as the stator.
    Also known is US patent US6983787 exhaust gas a matrix describing a recovery heat exchanger for a gas turbine engine creating a cross-flow counter current around which the hot exhaust gas turbine flows , a distribution tube for directing the air supplied by a compressor into the matrix / counter current and a tube is arranged parallel to the tube intended for evacuating the air from the compressor is heated by the matrix with transverse flow / against - current.
    collector who distributes and
    Disadvantages of the prior art
    In the solutions of the prior art, the structure and the operation of the exchanger are not optimized. The solutions providing for a plate exchanger have a less attractive mass / yield ratio than tube exchangers, because of manufacturing and mechanical strength constraints limiting the reduction in plate thicknesses, in particular.
    In the solutions of the prior art, the fuel injection system by vaporization rods in the combustion chamber and preheating of the combustion chamber of the turbomachine are two separate pieces of equipment, multiplying the fuel supply circuits of the combustion chamber
    In the solutions of the prior art, when the electric generator is air-cooled, the cooling circuit is not at optimum in terms of pressure drops, degrading the overall performance of the entire system
    Solution provided by the invention
    In order to remedy these drawbacks, the invention relates, in its most general sense, to a turbomachine comprising
    - a compressor discharging the compressed gases into a heat exchanger through an annular connection
    - an annular combustion chamber, receiving the gases coming from said exchanger via an annular connection
    - a turbine discharging hot gases from the combustion chamber
    a heat exchanger having an annular shape, formed by an assembly of independent tubes assembled by retaining means, and having a cylindrical cavity opening on the one hand to the outlet of the turbine, the assembly of tubes being housed in said cavity characterized in that said heat exchanger consists of:
    a) at least a first annular bundle formed by a plurality of a first series of rectilinear tubes, each extending between a proximal perforated connection plate and a distal perforated connection plate, said first annular bundle communicating with said annular connection of the compressor
    b) at least one second annular beam, coaxial with said first annular beam, formed by a plurality of a first series of rectilinear tubes, each extending between said proximal perforated connection plate and said distal perforated connection plate,
    - Said second annular bundle communicating with said annular connection of the combustion chamber c) an annular closure structure determining an outer annular cavity into which the gases emanating from said first bundle of tubes to be deflected on a bottom towards an inner annular cavity, coaxial with the outer annular cavity, opening onto the tubes of said second bundle of tubes, the high temperature fluid leaving the turbine passing through said two bundles of tubes.
    According to an advantageous embodiment, said annular connection of the compressor comprises at least one cylindrical bellows.
    According to another embodiment, said annular connection of the combustion chamber comprises at least one cylindrical bellows.
    According to another embodiment, said annular connection between the first bundle of tubes and said annular closure structure comprises at least one cylindrical bellows.
    According to another embodiment, said annular connection between said annular closure structure and the second bundle of tubes comprises at least one cylindrical bellows.
    Advantageously, said bellows are constituted by a system of tight connections and axially deformable allowing free thermal expansion of the tubes of the first and / or second annular sections of the heat exchanger.
    According to a particular variant, the turbomachine according to the invention comprises a fuel supply system for the combustion chamber consisting of at least one fuel vaporization rod partially surrounded by a heating sleeve.
    Preferably, that said vaporization rods each incorporate at least one metal filament connected to an electrical supply during the start-up phases to ensure the rise in temperature of the fuel until the vaporization of the latter inside the vaporization rods .
    According to a first application, the axis of the turbine directly drives a power shaft.
    According to a second application, the axis of the turbine directly drives an electric generator.
    The invention also relates to a turbogenerator comprising a turbomachine and an electric generator characterized in that the axis of the turbine directly drives an electric generator.
    Preferably, the turbogenerator according to the invention comprises an air cooling circuit of the fixed and mobile elements of said electric generator.
    Advantageously, said cooling circuit is composed of two parallel circuits, one for cooling the fixed parts, the other the mobile parts, with an independent flow calibration system for each air circuit.
    The invention also relates to a heat exchanger having an annular shape, formed by an assembly of independent tubes assembled by retaining means, and having a cylindrical cavity opening on the one hand to the outlet of the turbine, the assembly of tubes being housed in said cavity characterized in that it consists of:
    a) at least a first annular bundle formed by a plurality of a first series of rectilinear tubes, each extending between a proximal perforated connection plate and a distal perforated connection plate, said first annular bundle communicating with said annular connection of the compressor
    b) at least one second annular beam, coaxial with said first annular beam, formed by a plurality of a first series of rectilinear tubes, each extending between said proximal perforated connection plate and said distal perforated connection plate,
    - said second annular bundle communicating with said annular connection of the combustion chamber
    c) an annular closure structure defining an outer annular cavity into which the gases from said first bundle of tubes open to be deflected on a bottom in the direction of an inner annular cavity, coaxial with the outer annular cavity, opening on the tubes of said second bundle of tubes the high temperature fluid leaving the turbine passing through said two bundles of tubes.
    Detailed description of a nonlimiting example of embodiment
    The invention will be better understood on reading the description which follows, concerning a nonlimiting example of embodiment illustrated by the appended drawings where:
    - Figure 1 shows a sectional view of a turbomachine according to the invention
    - Figure 2 shows a perspective view of an example of the annular closure structure
    - Figure 3 shows a detailed view, in section, of an example of a fuel supply rod
    - Figure 4 shows a detailed view, in section, of an example cooling of the fixed and mobile parts of the generator.
    Context of the invention
    The present invention relates to different possible implementations, for the production of a turbogenerator or for the production of a turbomachine for driving a power shaft.
    The examples below do not limit the invention to a particular application, and certain embodiments can be implemented either in combination on the same equipment, or independently on an equipment. In particular, the invention relates to the general objective of optimizing a turbomachine, from an improvement in the efficiency resulting from an improved exchanger, as well as an optimization of the start-up phase by a supply rod improved, and also the optimization of the cooling of the fixed and mobile parts of the generator, when the turbomachine drives a generator.
    Description of the exchanger
    FIG. 1 represents a perspective view of the turbomachine, comprising an exchanger (1), a compressor (2), a combustion chamber (3) and a turbine (4). A conical deflector (11) coaxial with the exchanger (1) circulates the hot gases from the turbine (4) towards a discharge outlet (12) after having passed through the exchanger (2), passing through two cassettes (5, 6) between the tubes.
    The parts formed by the compressor (2), the
    bedroom of combustion (3) and the turbine (4) are known of Man of trade, and conform to the state of knowledge in matter of turbomachinery. The exchanger (2) consists by an exchanger at
    tubes, comprising two coaxial annular cassettes (5, 6).
    The outer cassette (5) consists of an assembly of parallel tubes, made of a metal alloy resistant to high temperatures, for example refractory stainless steel 347.
    By way of example, this external cassette (5) consists of 2000 tubes with a length of 300 millimeters, an inner section of 2.8 millimeters and an outer section of 3 millimeters. The tubes are held in known manner by spacers to define passages for the hot gases from the turbine.
    The tubes form a sleeve with an outside radius of 158 millimeters and an inside radius of 128 millimeters.
    The inner cassette (6) consists of 2000 tubes with a length of 300 millimeters, an inner section of 2.8 millimeters and an outer section of 3 millimeters.
    The tubes form a sleeve with an outside radius of 123 millimeters and an inner radius of 67 millimeters.
    The two cassettes (5, 6) are coaxial and embedded one inside the other.
    These two cassettes (5, 6) are joined, at the opposite end to the compressor (1), by an annular closure structure (8).
    Each of the cassettes (5, 6) has, at each end, a front sealing plate pierced for the passage of the tubes, and ensuring the constant spacing of the tubes. The tubes are brazed or welded to ensure sealing at their connection with the front plates.
    This closure structure (8) consists of two nested coaxial parts, having the general shape of a rum baba mold, made of refractory stainless steel 347 with a thickness of 2 millimeters.
    The external external part corresponding to the external cassette (5) and corresponding to the internal section (6).
    (9) has an exterior section of the interior interior section of the cassette
    The outer inner part corresponding to the outer cassette (5) and corresponding to the inner section (6).
    (10) has an inner section of the outer inner section of the cassette
    Each of the parts (9, 10) has a symmetry of revolution along the axis of the turbomachine, with a constant longitudinal section.
    The closing structure (8) deflects the gases from the outer cassette (5) towards the tubes constituting the inner cassette (6).
    This solution ensures a double passage of the gases in the exchanger (1), which significantly increases its thermal efficiency for a space requirement, and in particular a given length.
    Description of the thermal expansion bellows
    In order to allow relative longitudinal displacement:
    - between the outer cassette (5) and the inner cassette (6)
    - between the outer cassette (5) and the frame of the turbomachine between the inner cassette (6) and the frame of the turbomachine
    The connection between the cassettes (5, 6) and the closing structure (8) and / or the annular supply of the combustion chamber (3) and / or the annular outlet of the compressor (2) is ensured by deformable zones .
    These deformable zones are for example formed by metal bellows formed by corrugated sheets of refractory stainless steel 347.
    Different combinations can be implemented. Of the four pairs of annular connection zones (13 to 16; 23 to 26), it is desirable that three be equipped with a deformable annular connection. Optionally, it is sufficient to equip two zones with a deformable connection, when the outer cassette (5) has a temperature which does not cause significant expansion.
    In the example described in Figure 2, the closure structure has an annular shape defining an outer annular cavity (50) into which the gases from the first bundle of tubes open to be deflected on a bottom (51) towards a inner annular cavity (52), coaxial with the outer annular cavity (50), opening onto the tubes of said second bundle of tubes.
    The outer tubular wall of the closure structure has an expansion bellows (53, 54).
    Similarly, the partition wall has a bellows (55)
    Description of the feed rod
    FIG. 3 represents a detailed view of an exemplary embodiment of the spray rod (30). It receives the fuel in liquid form, and comprises a fuel supply duct (32) and downstream a heating sleeve (31) ensuring the vaporization of the fuel. This heating sleeve (31) includes an electrical resistance.
    It can also include a nickel coil embedded in an envelope of silicon nitride.
    The outlet of the spray cane (30) can be multiplied to form several injection nozzles. Each of the nozzles can optionally include a heating sleeve.
    Description of the generator air cooling circuit.
    Figure 4 describes a sectional view of the electric generator, comprising in a known manner a stator (40) and a rotor (41).
    The stator (40) has radial fins at its periphery, crossed by a flow of fresh air (42). Optionally, the stator yoke can also include longitudinal holes to ensure fresh air passages.
    A second air flow (43) passes through the air gap formed between the stator (40) and the rotor (41).
    Optionally, the rotor (41) may have twisted teeth, of helical shape, ensuring the forcing of the air flow circulating in the air gap.
    The outlet of these two streams (42, 43) is produced by a front plate (44) located upstream or downstream of the rotor, and having calibrated orifices to balance the flow rate of the two streams (42, 43).
    The flows (42, 43) penetrate on one side of the rotor (41) and exit on the other side of the rotor (41) to maximize cooling.
    权利要求:
    Claims (13)
    [1]
    Claims
    1 - Turbomachine including
    - a compressor (2) discharging the compressed gases into a heat exchanger (1) by an annular connection
    - an annular combustion chamber (3), receiving the gases coming from said exchanger via an annular connection
    - a turbine (4) discharging the hot gases from the combustion chamber (3)
    - A heat exchanger (1) having an annular shape, formed by an assembly of independent tubes assembled by holding means, and having a cylindrical cavity opening on the one hand on the outlet of the turbine, the assembly of tubes being housed in said cavity characterized in that said heat exchanger (1) consists of:
    a) at least one first annular bundle (5) formed by a plurality of a first series of rectilinear tubes, each extending between a proximal perforated connection plate and a distal perforated connection plate,
    - said first annular beam (5) communicating with said annular connection of the compressor
    b) at least one second annular bundle (6), coaxial with said first annular bundle, formed by a plurality of a first series of straight tubes, each extending between said proximal perforated connecting plate and said distal perforated connecting plate,
    - said second beam annular (6) communicating with said fitting ring finger of bedroom of combustion vs) a structure of closing of ring shape
    (8) determining an outer annular cavity into which the gases emanating from said first bundle of tubes are to be deflected on a bottom in the direction of an inner annular cavity, coaxial with the outer annular cavity, opening onto the tubes of said second bundle of tubes the high temperature fluid leaving the turbine passing through said two bundles of tubes.
    [2]
    2 - Turbomachine according to claim 1 characterized in that said annular connection of the compressor comprises at least one cylindrical bellows (53 to 55).
    [3]
    3 - Turbomachine according to claim 1 characterized in that said annular connection of the combustion chamber comprises at least one cylindrical bellows.
    [4]
    4 - Turbomachine according to claim 1 characterized in that said annular connection between the first bundle of tubes and said annular closure structure comprises at least one cylindrical bellows.
    [5]
    5 - Turbomachine according to claim 1 characterized in that said annular connection between said annular closure structure and the second bundle of tubes comprises at least one cylindrical bellows.
    [6]
    6 - Turbomachine according to any one of claims 2 to 5 characterized in that said bellows are constituted by a system of tight connections and axially deformable allowing to make free the thermal expansions of the tubes of the first and second annular sections of the heat exchanger .
    [7]
    7 - Turbomachine according to claim 1 characterized in that it comprises a fuel supply system of the combustion chamber consisting of at least one fuel vaporization rod partially surrounded by a heating sleeve.
    [8]
    8 - Turbomachine according to the preceding claim characterized in that said vaporization rods each integrate at least one metal filament connected to an electrical supply during the starting phases to ensure the rise in temperature of the fuel until the vaporization of the latter at inside the spray canes.
    directly characterized a
    Turbomachine according to the axis of the power shaft.
    claim 1 the turbine drives
    [9]
    10 - Turbomachine according to characterized in that the axis of directly an electric generator.
    claim 1 the turbine drives
    [10]
    11 - Turbogenerator comprising a turbomachine according to claim 1 and an electric generator characterized in that the axis of the turbine directly drives an electric generator.
    [11]
    12 - Turbogenerator according to the preceding claim characterized in that it comprises an air cooling circuit of the fixed and mobile elements of said electric generator.
    [12]
    13 - Turbogenerator according to the preceding claim characterized in that said cooling circuit is composed of two parallel circuits, one for cooling the fixed parts, the other the mobile parts, with an independent flow calibration system for each circuits d 'air.
    [13]
    14 - Heat exchanger having an annular shape, formed by an assembly of independent tubes assembled by retaining means, and having a cylindrical cavity opening on the one hand to the outlet of the turbine, the assembly of tubes being housed in said cavity characterized in that it consists of:
    a) at least a first annular bundle formed by a plurality of a first series of rectilinear tubes, each extending between a proximal perforated connection plate and a distal perforated connection plate, said first annular bundle communicating with said annular connection of the compressor
    b) at least one second annular beam, coaxial with said first annular beam, formed by a plurality of a first series of rectilinear tubes, each extending between said proximal perforated connection plate and said distal perforated connection plate,
    - said second annular bundle communicating with said annular connection of the combustion chamber
    c) an annular closure structure defining an outer annular cavity into which the gases from said first bundle of tubes open to be deflected on a bottom in the direction of an inner annular cavity, coaxial with the outer annular cavity, opening on the tubes of said second bundle of tubes
    5 the high temperature fluid leaving the turbine passing through said two bundles of tubes.
    1/2
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    同族专利:
    公开号 | 公开日
    WO2018096233A1|2018-05-31|
    FR3059363B1|2019-04-05|
    CA3044563A1|2018-05-31|
    EP3545176A1|2019-10-02|
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    CN110268139A|2019-09-20|
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    法律状态:
    2017-11-17| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-01| PLSC| Publication of the preliminary search report|Effective date: 20180601 |
    2018-11-26| PLFP| Fee payment|Year of fee payment: 3 |
    2019-09-20| TP| Transmission of property|Owner name: TURBOTECH, FR Effective date: 20190813 |
    2019-11-27| PLFP| Fee payment|Year of fee payment: 4 |
    2020-11-25| PLFP| Fee payment|Year of fee payment: 5 |
    2021-11-17| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661539A|FR3059363B1|2016-11-25|2016-11-25|TURBOMACHINE, IN PARTICULAR TURBOGENERATOR AND EXCHANGER FOR SUCH A TURBOMACHINE|
    FR1661539|2016-11-25|FR1661539A| FR3059363B1|2016-11-25|2016-11-25|TURBOMACHINE, IN PARTICULAR TURBOGENERATOR AND EXCHANGER FOR SUCH A TURBOMACHINE|
    CN201780080215.0A| CN110268139A|2016-11-25|2017-11-09|Turbogenerator especially turbogenerator and the exchanger for turbogenerator|
    PCT/FR2017/053060| WO2018096233A1|2016-11-25|2017-11-09|Turbine engine, in particular a turbine generator and exchanger for such a turbine engine|
    CA3044563A| CA3044563A1|2016-11-25|2017-11-09|Turbine engine, in particular a turbine generator and exchanger for such a turbine engine|
    EP17800920.5A| EP3545176A1|2016-11-25|2017-11-09|Turbine engine, in particular a turbine generator and exchanger for such a turbine engine|
    US16/463,157| US20190277199A1|2016-11-25|2017-11-09|Turbo engine, in particular turbo generator and exchanger for such turbo engine|
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