• 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 propellant supply system (100) comprising: - a tank (10) having an inlet (11) and a delivery (12); - a liquid propellant feed line connected to the intake (11); ) of the reservoir (10), - a propellant discharge line connecting a discharge (12) of the reservoir (10) to an igniter (40), characterized in that said reservoir (10) has an internal volume filled with spheres of storage (20) of heat, said storage spheres (20) being adapted to store heat, and transmit it to a fluid passing through said tank (10), so as to vaporize a liquid propellant passing through said tank (10).
    公开号:FR3037618A1
    申请号:FR1501275
    申请日:2015-06-18
    公开日:2016-12-23
    发明作者:Davide Duri
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to the field of cryotechnic engine supply systems, and more specifically to the supply of gaseous propellant to an ignition system of such a cryogenic engine. STATE OF THE ART Cryogenic engine ignition systems must be supplied with gaseous propellants for their operation, the gaseous propellant flow rate must be controlled in order to ensure ignition. The liquid propellant used to supply the ignition system is typically withdrawn from the propellant stage tank of the associated engine for the duration of the ignition sequence. This sample is taken at the pressure of the tank, and the propellant is then vaporized to supply the ignition system. However, this vaporization of the propellant is complex to achieve, and can have a negative impact on the performance of the system in particular because of the thermal inertia of the supply circuit which can prevent the complete vaporization of the propellant. Several solutions are currently proposed to improve ignition performance: 25 - so-called "passive" solutions, in which propellant is stored under high pressure in a set of bottles, said bottles being associated with a filling circuit control and relaxation, or in which the propellant is vaporized by convective exchange with the walls of the igniter supply circuit. 30 - So-called "active" solutions, in which the propellant is vaporized via heating carried out by autogenous heat sources fed by propellant tanks. However, these different solutions each have disadvantages that are very disadvantageous. Passive systems using cylinders for the high pressure storage of propellants have disadvantages in terms of mass.
    [0002] Furthermore, the passive systems operating by heat exchange are very complex to dimension especially due to the low coefficient of exchange forced convection and film flow. Active systems performing a heating of the propellant require heat exchangers and an associated combustion chamber, which are also penalizing in terms of mass. In addition, for active systems, not only an independent igniter is required, which again raises the same issues, but the combustion of transient phases is also very difficult to control.
    [0003] PRESENTATION OF THE INVENTION The present invention aims at responding at least in part to these problems, and thus proposes a propellant feeding system of an igniter, comprising - a reservoir having an inlet and a discharge, - a line of liquid propellant feed connected to the tank inlet, - a propellant delivery line connecting a discharge of the tank to an igniter, characterized in that said tank has an internal volume filled with heat storage spheres, said spheres of storage being adapted to store heat, and transmit it to a fluid passing through said tank, so as to vaporize a liquid propellant passing through said tank.
    [0004] The internal volume is typically defined by peripheral walls of the reservoir, an upstream plate and a downstream plate, one of the upstream and downstream plates being subjected to a pushing force towards the other of the upstream and downstream plates so as to compact the storage spheres contained in the internal volume. Said storage spheres are for example made of polyamides and / or polytetrafluoroethylene. The system may further include a system for injecting hot gas into the tank, thereby storing heat energy in the storage spheres.
    [0005] Said hot gas is, for example, Helium. The invention also relates to a method for vaporizing a propellant supplying an igniter, in which - it stores heat in a set of storage spheres 15 contained in a reservoir, - a propellant igniter is supplied via said reservoir, so that the propellant reaching the igniter passes through the tank beforehand, and is vaporized by heat exchange with the storage spheres.
    [0006] Said storage spheres are typically held compressed in the internal volume of the reservoir, between two plates arranged in the reservoir and subjected to a thrust force. The two plates are pierced, and thus each have holes allowing the passage of fluid within the reservoir, while ensuring the maintenance 25 of the storage spheres in the internal volume. The holes formed in the plates thus have a diameter smaller than that of the storage spheres. According to a particular embodiment, heat is stored in the storage spheres by injecting a hot gas into the reservoir, for example Helium.
    [0007] Other features, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended figures, in which: FIG. 1 schematically represents a system according to one aspect of the invention; - Figure 2 schematically illustrates a method according to one aspect of the invention.
    [0008] DETAILED DESCRIPTION FIG. 1 schematically represents an exemplary propellant supply system 100 according to one aspect of the invention.
    [0009] The system 100 as illustrated comprises a reservoir 10 comprising an inlet 11 and a discharge 12, and delimited by walls. The discharge 12 of the tank 10 is typically provided with a filter 5.
    [0010] The inlet 11 of the tank 10 is connected to a liquid propellant tank 30 via an propellant inlet valve 1. The outlet 12 of the tank 12 is connected to an igniter 40 via an ignition valve 2.
    [0011] The reservoir 10 defines an internal volume of which at least a portion is filled with storage spheres 20. The storage spheres 20 are for example made of polyamides and / or polytetrafluoroethylene (PTFE). PTFE is particularly interesting because of its mass / heat transfer capacity ratio, and because of its chemical compatibility with propellants commonly used. In the embodiment shown, the internal volume filled with storage spheres 20 is defined by the peripheral walls of the tank 307618 on the one hand, by an upstream plate 21 and by a downstream plate 22. In the illustrated example, the downstream plate 22 is fixed, while the upstream plate 21 is coupled to a spring 23 which exerts a thrust force 5 on the upstream plate 21 tending to move it towards the downstream plate 22. In a variant, it is the downstream plate 22 which may be coupled to a spring tending to push it towards the upstream plate 21 while the latter is fixed, or the two upstream and downstream plates 21 may each be coupled to a spring tending to push them towards each other. other.
    [0012] The two upstream and downstream plates 21 21 are pierced, and thus each have holes allowing the passage of fluid within the reservoir 10, while ensuring the maintenance of the storage spheres 20 in the internal volume of the reservoir 10. The holes arranged in the upstream and downstream plates 21 and 21 have a diameter smaller than that of the storage spheres 20. The storage spheres 20 are thus compacted in the internal volume, between the two upstream and downstream plates 21 21. The internal volume of the reservoir 10 filled with storage spheres 20 is configured so that a fluid from the inlet 11 to the discharge 12 of the reservoir 10 necessarily passes through the internal volume of the reservoir 10. The storage spheres 20 are configured from in order to store heat, and thus to transfer it to a fluid which passes through the internal volume of the tank 10. They are first heated, so as to store the energy desired. Thus, when opening the propellant intake valve 1 and the ignition valve 2, the liquid propellant from the liquid propellant tank 30 reaches the tank 10 via its inlet 11, then passes through the internal volume of the tank filled with storage spheres 20, before 3037618 6 out through the discharge 12 of the tank and reach the igniter 40. During the passage of liquid propellant within the internal volume of the tank 5 10 filled storage spheres 20, the latter perform a heat transfer to the liquid propellant, and thus transfer the stored heat energy storage spheres 20 to the propellant. The storage spheres 20 are calibrated so that the heat energy stored therein is sufficient to vaporize the liquid propellant as it passes through the tank 10, so that the igniter 40 is energized. in gaseous propellant. The system 100 may also include a hot gas injection system in the tank 10, so as to charge or recharge the storage spheres 20 with heat energy. In the embodiment illustrated in FIG. 1, the inlet 11 of the tank 10 is thus connected to a hot gas tank 50 via a heating valve 3. The delivery 12 of the tank 10 is then also connected to a line leakage via a leakage valve 4, through which the hot gas is rejected after passing through the tank 10.
    [0013] The hot gas contained in the hot gas tank 50 is, for example, helium. The latter can then be rejected in the gaseous atmosphere of the liquid propellant tank 30, as shown in FIG.
    [0014] The hot gas injection system is used, for example, following operation of the igniter 40 in order to reload the storage spheres 20 for subsequent ignition.
    [0015] FIG. 2 diagrammatically represents the method that can be implemented using the system shown in FIG. 1. In a first step E1, heat is stored in a set of storage spheres 20 contained in a reservoir. 10. Then, once the desired heat energy has been stored in the storage spheres, it is possible during a second step E2 to supply a propellant igniter 40 via said tank 10, the propellant being taken from a propellant tank 10. liquid 30, so that the propellant reaching the igniter 40 passes through the tank 10 beforehand, and is vaporized by heat exchange with the storage spheres 20. Following this second step E2, it is possible to third step E3 1 5 reload the storage spheres, injecting a hot gas such as Helium into the tank. The use of storage spheres 20 is particularly advantageous, particularly because of the very large exchange surface they create. In addition, the use of storage spheres 20 gives considerable flexibility in the calibration of the system, in particular by influencing the number of storage spheres 20 and their dimensions, which in particular makes it possible to modify the storage and retrieval capacity. energy storage spheres 20, as well as the properties of the flow and the pressure losses generated by the storage spheres 20.
    [0016] Furthermore, such a system 100 has a reduced mass compared to conventional passive or active systems.
    [0017] In addition, the heat exchanger formed by the storage spheres 20 also makes it possible to homogenize the flow passing through the reservoir 10.
    [0018] The proposed system and method therefore make it possible to exploit a ball exchanger for the vaporization and homogenization of a cryogenic fluid, particularly in the context of space applications.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. A propellant supply system (100) comprising: - a tank (10) having an inlet (11) and a delivery (12); - a liquid propellant feed line connected to the intake (11); ) of the reservoir (10), - a propellant discharge line connecting a discharge (12) of the reservoir (10) to an igniter (40), characterized in that said reservoir (10) has an internal volume filled with spheres of storage (20) of heat, said storage spheres (20) being adapted to store heat, and transmit it to a fluid passing through said tank (10), so as to vaporize a liquid propellant passing through said tank (10).
    [0002]
    2. System (100) according to claim 1, wherein the internal volume is defined by peripheral walls of the reservoir (10), an upstream plate (21) and a downstream plate (22), one of the upstream plates (21). ) and downstream (22) being subjected to a pushing force towards the other of the upstream (21) and downstream (22) plates so as to compact the storage spheres (20) contained in the internal volume, said plates (21, 22) being pierced, and thus each having holes each having a diameter smaller than that of the storage spheres (20).
    [0003]
    3. System (100) according to one of claims 1 or 2, wherein said storage spheres (20) are made of polyamides and / or polytetrafluoroethylene.
    [0004]
    4. System (100) according to one of claims 1 to 3, further comprising a hot gas injection system (50, 3) in the tank (10), so as to store heat energy in the storage spheres (20). 3037618 10
    [0005]
    The system (100) of claim 4, wherein said hot gas is Helium.
    [0006]
    6. A method of vaporizing a liquid propellant feeding an igniter (40), wherein - (E1) is stored heat in a set of storage spheres (20) contained in a reservoir (10), - (E2) an igniter (40) is fed with propellant via said reservoir (10), so that the propellant reaching the igniter (40) passes through the reservoir (10) beforehand, and is vaporized by heat exchange with the storage spheres (20).
    [0007]
    7. A method according to claim 6, wherein said storage spheres (20) are held compressed in the internal volume of the reservoir (10) between two plates (21, 22) disposed in the reservoir (10) and subjected to a pushing force.
    [0008]
    8. A method according to one of claims 6 or 7, wherein (E3) heat is stored in the storage spheres (20) by injecting a hot gas into the reservoir (10).
    [0009]
    The process of claim 8, wherein said hot gas is Helium.
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    同族专利:
    公开号 | 公开日
    US20180170582A1|2018-06-21|
    EP3311070B1|2021-12-01|
    JP2018519489A|2018-07-19|
    WO2016203138A1|2016-12-22|
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR328147A|1902-11-20|1904-01-20|Farjas Henri|New steam superheater|
    US5014507A|1989-12-14|1991-05-14|Sundstrand Corporation|Direct drive gaseous hydrogen turbo actuator|
    EP1351016A2|2002-04-02|2003-10-08|Masami Nomura|Superheated steam generator|
    EP1591719A1|2003-01-28|2005-11-02|Izumi Information Co. Ltd.|Superheated steam producing device|
    US4013396A|1975-08-25|1977-03-22|Tenney William L|Fuel aerosolization apparatus and method|CN109339981B|2018-12-10|2021-03-09|上海宇航系统工程研究所|Pressurization system for cold helium in coal oil tank of carrier rocket|
    CN109595468B|2018-12-24|2020-05-15|西安交通大学|Cold helium supercharging and cooling conveying system of low-temperature carrier rocket|
    CN110954794A|2019-12-11|2020-04-03|中国科学院力学研究所|Liquid propellant constant-pressure discharge characteristic parameter measuring device|
    法律状态:
    2016-06-10| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-23| PLSC| Publication of the preliminary search report|Effective date: 20161223 |
    2017-06-28| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-25| PLFP| Fee payment|Year of fee payment: 4 |
    2020-06-25| PLFP| Fee payment|Year of fee payment: 6 |
    2021-06-22| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
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    FR1501275A|FR3037618B1|2015-06-18|2015-06-18|ERGOL FEEDING SYSTEM OF AN IGNITER|FR1501275A| FR3037618B1|2015-06-18|2015-06-18|ERGOL FEEDING SYSTEM OF AN IGNITER|
    RU2018101663A| RU2018101663A|2015-06-18|2016-06-09|SYSTEM FOR SUPPLY OF FUEL TO THE IGNITER|
    EP16734433.2A| EP3311070B1|2015-06-18|2016-06-09|System for supplying an igniter with propellant|
    US15/735,782| US20180170582A1|2015-06-18|2016-06-09|System for supplying an igniter with propellant|
    PCT/FR2016/051380| WO2016203138A1|2015-06-18|2016-06-09|System for supplying an igniter with propellant|
    JP2017565199A| JP2018519489A|2015-06-18|2016-06-09|System for supplying fuel to the igniter|
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