• 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:
    A rocket-propelled vehicle includes an adjustable voltage AC generator adapted to be connected to a power generating turbine shaft and adapted to convert rotational motion into electrical energy, the AC voltage generator adjustable being designed to produce a desired voltage regardless of the variation in the rotational speed of the power generating turbine shaft, an AC electric motor pump being designed to pump at least either fuel or fuel. oxidant to a vehicle combustion chamber propelled by a rocket, and an AC bus connecting the adjustable voltage AC generator to each AC electric motor pump.
    公开号:FR3019593A1
    申请号:FR1552777
    申请日:2015-04-01
    公开日:2015-10-09
    发明作者:Richard A Himmelmann
    申请人:Hamilton Sundstrand Corp；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION 1. Field This description relates to systems using electric motors, more specifically AC electric motors used in a vehicle. 2. Description of the Prior Art Vehicles propelled by a rocket may include fuel and oxidizer pumps that are mechanically linked to an electricity generating turbine that is powered by the exhaust gases from the engine. a separate combustion chamber not associated with the main combustion chamber of the rocket. The pumps can be mechanically connected to the power generation turbine through a gear train. In this case, the speed of each pump is proportional to the speed of the power generation turbine which is variable, so the speed of each pump is regulated by changing the rotational speed of the power generation turbine. With this type of mechanical power transmission architecture, the rotational speed of the pumps can not be controlled independently. In addition, the mechanical system that connects the pumps to the power generation turbine is heavy and requires the pumps to be located near the power generation turbine. In some situations, the oxidizer pump and the fuel pump may be mounted on the same rotational shaft as the power generation turbine. This architecture does not have the complexity of the rocket motor turbopump architecture described previously, however the efficiencies of the pumps and the power generation turbine are reduced, as each component is forced to operate at the same rotation speed.
    [0002] It would be possible to feed AC powered pumps by electric drive with an AC-DC-CA conversion system that is designed to regulate the speed of each pump regardless of the speed of the power generation turbine, however, such a system would add a significant weight to the vehicle propelled by a rocket and would not necessarily be beneficial compared to a mechanical system.
    [0003] These conventional methods and systems have generally been considered satisfactory for their intended purpose. However, there is still a need in the art for a system allowing the efficient use of electric motor pumps in a rocket propelled vehicle. This description proposes a solution for this problem. SUMMARY A system for powering a pump in a rocket-propelled vehicle includes an adjustable voltage AC generator that is adapted to be connected to an electricity generating turbine shaft and that is designed to convert the rotation energy into electrical energy. The adjustable voltage AC generator is designed to produce a desired voltage regardless of the rotational speed variation of the generating turbine shaft. An AC electric motor pump is designed to pump at least one fuel or oxidant to a vehicle combustion chamber propelled by a rocket. An AC electric bus connects the adjustable voltage AC generator to the AC electric motor that drives the pump. In some embodiments, the system may further include a power generation turbine operably connected to the adjustable voltage AC generator and configured to convert the exhaust gas energy into rotational motion of a shaft. of electricity generation turbine. The system may further include a controller configured to control the adjustable voltage AC generator to produce the desired voltage. The controller may have a feedback system for determining a flow of fluid or a pump speed of the AC electric motor, and may modify the voltage of the adjustable voltage AC generator to obtain a pump speed or a fluid flow rate. desired. In some embodiments, the system may further include an electric AC fuel pump and an AC electric oxidant pump and a corresponding adjustable voltage generator for each pump. Each controllable generator may be coaxially disposed on the power generating turbine shaft or geared to the shaft, or by any other suitable means. In some embodiments, the fuel pump may be disposed near a fuel tank. The oxidizer pump may be disposed near a fuel tank or in any other suitable manner. In some embodiments, one of the pumps may be coaxially disposed on, or geared to, the power generating turbine shaft or the adjustable voltage AC generator so that the pump is mechanically driven. and that the other pump is electrically driven by the adjustable voltage AC generator. In at least one aspect of this disclosure, a method includes controlling an output voltage of an adjustable voltage generator attached to a power generation turbine of a rocket powered vehicle that is adapted to convert power from a power source. the rotational exhaust gas energy of a power generating turbine shaft and allowing the adjustable voltage generator to power an AC electric motor pump in a rocket propelled vehicle. The AC electric motor pump may be any suitable electric motor pump (eg, an induction motor and / or any other suitable electric motor pump that is designed to tolerate slippage). The method may further include determining a pump speed or a fluid flow rate of at least one of oxidant and fuel. In some embodiments, the method further includes increasing the output voltage if the pump speed or fluid flow rate is determined to be lower than a speed and / or if the output voltage is decreased if it is determined that the pump speed or the fluid flow rate is greater than a desired speed. The method may further include operating the adjustable voltage AC generator to obtain a constant voltage in response to a change in the power generation turbine shaft speed. In some embodiments, the method may further include multiple electric motor pumps of the vehicle propelled by a rocket independently of one another. The method may further include regulating the speed of the electric vehicle AC motor pump powered by a rocket regardless of the speed of the power generating turbine shaft.
    [0004] These and other features of the systems and methods of the present disclosure will become more readily apparent to those skilled in the art from the following detailed description taken in conjunction with the drawings.
    [0005] BRIEF DESCRIPTION OF THE DRAWINGS In order for those of ordinary skill in the art to understand how to use the devices and methods of subject description without undue experimentation, embodiments will be described in detail hereinafter with reference to to certain figures, among which: FIG. 1 is a partial perspective view of an embodiment of a system according to this description; Figure 2 is a schematic view of an embodiment of a system according to this description; Figure 3 is a schematic view of a portion of an embodiment of a vehicle propelled by a rocket according to this description; and FIG. 4 is a partial perspective view of an embodiment of a system according to this description, showing a pump disposed coaxially with a generator and another electrically connected to the generator. DETAILED DESCRIPTION Referring now to FIGS. drawings where identical reference numbers identify features or similar structural aspects of the subject description. For the purpose of explanation and illustration, and without limitation, an exemplary embodiment of a system 100 according to the description appears in FIG. 1. A systematic view of a system 100 appears in FIG. appears in a vehicle propelled by a rocket 300 in FIG. 3. The systems and methods described herein can be used to regulate the supply of fuel and / or oxidant into a rocket engine regardless of the turbine speed.
    [0006] Referring to FIGS. 1 and 2, it will be seen that in at least one aspect of this disclosure a system 100 includes an adjustable voltage AC generator 103 which is adapted to be connected to a production turbine shaft 102 electricity generating turbine 101, and is adapted to convert rotational energy into electrical energy. The adjustable voltage AC generator 103 may be any suitable controllable voltage generator adapted to change the output voltage for a given rotational speed of the adjustable voltage AC generator 103. US Pat. No. 7,385,322 to Himmelmann discloses for example, a suitable type of AC generator with adjustable voltage. Non-limiting examples of adjustable voltage AC generators include: 1) a wound inductor machine where the excitation current (applied to the main stage rotor) can be increased or decreased to vary the amount of magnetic flux interacting with the main floor stator; 2) an induction generator that can increase or decrease the frequency of the excitation field (thus changing the slip rate), which then changes the magnetic flux on the rotor, thereby changing the main stage output voltage ; 3) a permanent magnet machine whose rotor can be removed from the stator, which modifies the effective stacking length of the machine, which modifies the rotor flux rate responsive to the stator, by modifying the output voltage; 4) a permanent magnet machine in which a metal sheath can be introduced partially or completely between the rotor and the stator (a magnetic flap) by effectively short-circuiting the magnetic flux on the rotor, which modifies the amount of flux interacting with the rotor; the stator, by altering the output voltage of the machine; 5) a permanent magnet machine which can have a rotor with two parts, split axially so that one half of the rotor can be rotated relative to the other, which cancels part of the magnetic flux interacting with the stator, this which modifies the output voltage; and 6) a permanent magnet machine that can incorporate regulating windings in the stator that can cause saturation or that can redirect the magnetic flux away from the main stator coils, thereby changing the main stator output voltage .
    [0007] The system 100 may further include at least one power generation turbine 101 designed to convert the exhaust energy into the rotational energy of an electricity generating turbine shaft 102 through the power turbine blades. turbine. With reference also to FIG. 3, it can be seen that the electricity generating turbine 101 can be connected to its own turbine combustion chamber 6 and / or can be connected to an exhaust from the chamber The adjustable voltage AC generator 103 may be configured to produce a desired voltage regardless of the rotational speed variation of the power generating turbine shaft 102. In this regard, the generator 103 can produce a desired voltage even if the speed of the steam generating turbine 101 changes due to fluctuations in the flow of the exhaust gas and / or for other reasons. The system 100 further comprises an AC electric motor pump 105 designed to pump fuel and / or oxidant to at least one combustion chamber 6, 13 (see Fig. 3) of the vehicle powered by a rocket 300, and an AC bus 107 connecting the adjustable AC generator 103 to each of the AC 105 electric motor pumps. The electric motor pump 105 may be any suitable electric motor pump, designed to operate with an alternating current ( eg an induction motor and / or any suitable electric motor designed to tolerate slippage). The AC bus 107 may correspond to any suitable connection for powering the AC electric motor pump 105 (eg a three-phase connection). The speed of the AC electric motor pump 105 may be followed and / or limited by a pump controller 109 which is connected during operation to the pump 105 and / or with at least one of the sensors (eg a sensor a flow sensor, a speed sensor) disposed there through any suitable circuit, hardware and / or software. The system 100 may further include a generator controller 111 configured to regulate the adjustable voltage AC generator 103 to produce the desired voltage. The generator controller 111 may have any appropriate back-control system and / or be configured to communicate with the pump controller 109 so that the generator controller can determine a fluid flow or a speed of the AC electric motor pump 105 The generator controller 111 is further adapted to alter the voltage of the adjustable voltage AC generator 103 to obtain a desired pump speed and / or fluid flow rate.
    [0008] The generator controller I 1 1 may be adapted to modify the output voltage in accordance with a predefined algorithm implemented through any suitable circuit, hardware or software, or through another suitable program. If, for example, the generator controller 111 or the pump controller 109 determines that the fluid flow rate is insufficient, then the generator controller 111 can modify the adjustable voltage AC generator 103 to produce a greater voltage and vice versa. The generator controller 111 may also be connected to the turbine 101 to determine a change in the rotational speed of the turbine 101, so that the generator controller 11 may change the output voltage causing the generator 103 to maintain output at constant / desired voltage and / or anticipating the fluctuations of the turbine 101.
    [0009] Referring to FIG. 2, it can be seen that a master controller 113 can be included in the system 100 so that the master controller 113 includes both the pump controller 109 and the generator controller 111 set. implemented in the form of software modules. Referring further to FIG. 3, the system 100 appears independently in a rocket powered vehicle 300. The vehicle 300 may further include both an electric fuel pump CA 3 and a pump AC electric oxidizer 4 and an adjustable voltage AC generator 103 for each pump. Each adjustable voltage AC generator 103 may be disposed coaxially on the power generating turbine shaft 102 or in any other suitable manner. For example, the generators can also be connected to the turbine by means of a gearbox, or chains, belts, friction drives, etc. The fuel pump 3 may be disposed near a fuel tank opposite, and not near the turbine 101, as the fuel pump 3 no longer needs to be mechanically linked to the turbine 101. The oxidizer pump 4 can also or otherwise be disposed near an oxidant reservoir in a similar manner for similar reasons.
    [0010] According to another embodiment, as shown in FIG. 4, a pump 205 (for example an impeller) can be disposed on the turbine shaft 202 of a turbine 201 along at least one generator 103. second pump (eg a pump with an electric motor 105) can be close to its reservoir. In such an embodiment, varying the speed of the turbine 201 can regulate the speed of the pump 205, while the adjustable voltage AC generator 103 can vary the speed of the electric motor pump 105 independently The speed of the turbine 201. This allows a system where the two pumps 105, 205 can have a variable speed independently, while they need only to carry the mass and complexity of a generator 103 and An electric motor for the electric motor pump 105. As shown in FIG. 4, the pump controller 109 may also be designed to also receive signals from a first pressure sensor 204 and / or a second sensor. pressure device 206 for determining a pressure of a fluid flow produced by the pumps 105, 205 (e.g., fuel pressure and / or oxidant pressure) In some embodiments, as shown in FIG. the co The generator controller 111 may be configured to generate different voltages to operate the fuel pump 3 and the oxidizer pump 4 independently of each other at different and / or identical speeds (e.g. one pump can be maintained at a constant speed while the other is changed at a variable speed).
    [0011] In some embodiments, the generator 103 may be configured to allow the inclusion of an active and / or passive rectifier that can siphon a portion of the electrical power from the electric turbopump system, thereby allowing it to be used for feed other vehicle equipment. In at least one aspect of this disclosure, a method includes regulating an output voltage of an adjustable voltage generator 103 attached to a power generation turbine 101 of a rocket powered vehicle 300 that is designed for converting exhaust energy into rotational energy of an electricity generating turbine shaft 102, and allowing the regulated voltage to power an AC electric motor pump 105 disposed in the vehicle powered by a 300 rocket.
    [0012] The method may further include determining a speed of the pump 105 or a fluid flow rate of at least one oxidant or fuel. In some embodiments, the method further includes increasing the output voltage if the pump speed or fluid flow rate is determined to be lower than a speed and / or if the output voltage is decreased if it is determined that the pump speed or the fluid flow rate is greater than a desired speed.
    [0013] The method may further include operating the adjustable voltage AC generator 103 to obtain a constant voltage in response to a change in the speed of the power generating turbine shaft 102. In some embodiments, the The method may further include controlling a plurality of AC 105 electric motor pumps of the vehicle powered by a rocket 300 independently of one another. The method may further include regulating the speed of the AC 103 electric motor pump of the rocket propelled vehicle 300 regardless of the speed of the power generating turbine shaft 102. Embodiments and Methods and systems of the present description, as previously described and appearing among the figures, propose a vehicle propelled by a rocket having superior properties, in particular an adjustable supply of fuel and / or oxidant regardless of the speed of the turbine . The systems and methods described herein can also lead to a rocket engine that can be started and stopped multiple times. While the apparatus and methods of this disclosure have been shown and described with reference to the embodiments, those skilled in the art will readily appreciate that modifications and / or changes can be made without departing from the spirit and scope of the present invention. description in object.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. A pump power system in a rocket-propelled vehicle, comprising: an adjustable voltage AC generator adapted to be connected to an electricity generating turbine shaft configured to convert rotational energy into energy electrical, the adjustable voltage AC generator being designed to produce a desired voltage regardless of the rotational speed variation of the power generation turbine shaft; an AC electric motor pump adapted to pump at least either fuel or an oxidant to a combustion chamber of the vehicle propelled by a rocket; and an AC bus connecting the adjustable voltage AC generator to the AC electric motor pump.
    [0002]
    The system of claim 1, further comprising a controller adapted to regulate the adjustable voltage AC generator to produce the desired voltage.
    [0003]
    The system of claim 2, wherein the controller comprises a feedback control system for determining a fluid flow rate or a speed of the AC electric motor pump and can change the voltage of the adjustable voltage AC generator to obtain a voltage. pump speed or a desired fluid flow rate.
    [0004]
    The system of claim 1, further comprising a power generation turbine operatively connected to the adjustable voltage AC generator and adapted to convert the exhaust gas energy into a rotational movement of a generator. tree of electricity production.
    [0005]
    The system of claim 1, further comprising: both a fuel cell electric pump and an oxidizing AC electric pump; and an adjustable voltage generator for each pump. 20 25 30
    [0006]
    6. System according to claim 5, wherein the fuel pump is arranged next to a fuel tank.
    [0007]
    The system of claim 5, wherein the oxidizer pump is disposed adjacent to an oxidizer reservoir.
    [0008]
    The system of claim 5, wherein one of the pumps is disposed coaxially on the power generating turbine shaft or on the controllable voltage AC generator, or geared to them, so that the pump is mechanically driven, and the other pump is electrically driven by the controllable voltage AC generator.
    [0009]
    A method, comprising: regulating an output voltage of a controllable voltage generator attached to a power generation turbine of a rocket propelled vehicle, which is adapted to convert gas energy rotational energy exhaust from an electricity generating turbine shaft; and allowing the regulated voltage to power an AC electric motor pump disposed in the rocket propelled vehicle.
    [0010]
    The method of claim 9, further comprising determining a pump speed or fluid flow rate of at least one of oxidant and fuel.
    [0011]
    The method of claim 10, further comprising increasing the output voltage if the pump speed or fluid flow is determined as below a desired speed.
    [0012]
    The method of claim 10, further comprising decreasing the output voltage if it is determined that the pump speed or fluid flow rate is greater than a desired speed.
    [0013]
    The method of claim 9, further comprising operating the controllable voltage AC generator to produce a constant voltage in response to a change in the power generation turbine shaft speed.
    [0014]
    The method of claim 9, further comprising regulating multiple AC electric motor pumps of the vehicle propelled by a rocket independently of one another.
    [0015]
    The method of claim 9 further comprising regulating the speed of the AC electric motor pump of the rocket propelled vehicle regardless of the speed of the power generating turbine shaft.
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    法律状态:
    2016-03-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 5 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/243,248|US9166510B1|2014-04-02|2014-04-02|Systems utilizing a controllable voltage AC generator system|
    US14243248|2014-04-02|
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