• 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:
    Ignition torch (10) for a rocket engine, comprising a body (20) in which is arranged a combustion chamber (21) and an ejection tube (40) for the evacuation of combustion gases leaving the chamber of combustion combustion. The body (20) of the torch is configured to allow the supply of fuel and oxidant combustion chamber via fuel supply and oxidant respectively supply ducts. The ignition torch (10) further comprises an oxidant reinjection duct (60) configured to allow oxidant injection substantially at the outlet of the ejection tube (40).
    公开号:FR3042543A1
    申请号:FR1559765
    申请日:2015-10-14
    公开日:2017-04-21
    发明作者:Cras Jean-Luc Le；Laurent Gomet；Louise Lesaunier；Jean-Claude Bourdais；Carlos Cruz
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION The invention relates to an ignition torch for a rocket engine.
    STATE OF THE PRIOR ART
    Rocket engines generally work by causing the meeting and combustion of two propellants, often oxygen and hydrogen, in a combustion chamber: it is the burnt gases generated by this combustion and escaping at very high speed out of the combustion chamber, usually via a diverging or a nozzle, which, by reaction, produce thrust propelling the rocket.
    Such combustion, once started, self-maintains as propellant supply is maintained. However, starting such a motor, using large volumes of propellants, requires a large amount of energy to initiate combustion, a quantity of energy that a single candle could provide. Thus, the rocket engines are equipped with ignition torches to initiate the combustion reaction in the combustion chamber of the engine and thus allow the engine to start.
    These ignition torches can be used in particular at the launch of the rocket (or spacecraft) or during different phases of flight.
    Among the ignition torches, pyrotechnic ignition torches and internal combustion chamber ignition torches are known. The latter, unlike pyrotechnic ignition torches, are reusable and therefore allow a possible restart of the engine in flight.
    Such an ignition torch consists mainly of a small combustion chamber fed with propellants and provided with a candle capable of igniting the small quantity of propellant introduced into the chamber: the combustion gases thus generated are then ejected towards the chamber. combustion engine and are sufficiently energetic to initiate combustion and start the engine.
    However, depending on the mode of operation (also called 'engine speed') desired for the engine, the expected performance of the ignition torch vary.
    The different engine speeds are distinguished from each other in particular by the temperature of the gases produced by the ignition torch and injected into the engine to allow it to start, or by the flow of gas at the output of the ignition torch. The engine speeds are generally characterized by their RM mixing ratio, that is to say the ratio (by mass) of the relative amounts of oxidant and fuel injected into the torch. When the mixing ratio RM is relatively high, namely greater than 1.5, the temperature of the gases produced by the ignition torch is generally very high, which often makes it difficult to ensure the mechanical strength of the torch. ignition during a sufficient number of engine ignitions.
    There are in particular: - low pressure ignition torches, fed with propellants pressurized at the low pressure of the tanks: unfortunately, they are found deficient when a back pressure is present in the combustion chamber, it is ie especially on the ground and at low altitude. In addition, they give off relatively little energy and can therefore potentially fail to start the engine and require several attempts before the actual engine start; and high pressure ignition torches, in which the propellants are stored in high pressure pressurized tanks. However, these are heavy and therefore very expensive.
    These different torches therefore pose either reliability problems or problems of complexity and consequently, price, weight and bulk.
    In particular, none of these torches is a simple and reliable solution to achieve a high mixing ratio exploitable ignition torch.
    PRESENTATION OF THE INVENTION
    Also, the object of the invention is to provide an ignition torch for a rocket engine, comprising a body in which is arranged a combustion chamber, and an ejection tube for the evacuation of combustion gases leaving the combustion chamber. combustion chamber ; the body being configured to allow the supply of fuel and oxidant to the combustion chamber via a fuel supply pipe and an oxidant supply pipe, respectively; Ignition torch which is reliable, relatively simple, and can be used especially for a high mixing ratio, inducing in particular very high temperatures for the gas ejected by the ignition torch.
    This objective is achieved by virtue of the fact that the ignition torch also comprises an oxidant reinjection duct configured to allow an injection of oxidant substantially at the outlet of the ejection tube.
    This oxidant injection at the outlet of the ejection tube allows the ignition torch to produce a combustion of the fuel in two stages:
    Indeed, it allows first a first combustion or main combustion, which is that which occurs in the combustion chamber, fed by the fuel supply channels and oxidant.
    But thanks to the injection (or 'reinjection' since it is a second injection) of oxidant at the outlet of the ejection tube through the oxidant reinjection pipe, the ignition torch allows more than takes place a second combustion at the outlet of the ejection tube, this second combustion to raise very strongly the temperature of the gas ejected by the ejection tube of the torch. By way of example, it is possible to feed the combustion chamber with fuel and oxidant so that the temperature in the chamber is about 500 to 600 K at the end of the first combustion; and then, injecting at the outlet of the ejection tube an amount of oxidant which, at the end of the second combustion, the temperature of the outlet gases is raised to 3600 K.
    Also advantageously, the structure of the ignition torch makes it possible to maintain the body of the torch at a relatively low temperature, without it being overloaded thermally or mechanically; conversely, the second combustion which occurs at the outlet of the ejection tube makes it possible to greatly increase the temperature of the gases ejected by the torch and therefore to greatly increase the capacity of the latter to cause ignition of the propellants in the combustion chamber and start the rocket engine. Advantageously, the ignition torch according to the invention can therefore operate at a high mixing ratio, without the torch being damaged, since only the end of the ejection tube is brought to a very high temperature.
    Preferably, the flow rates of fuel and oxidant in the supply channels of the ignition torch are chosen such that the first combustion is at a relatively low temperature, so as not to expose the body of the torch. ignition at high temperatures which could damage it.
    The ignition torch can be realized in different ways.
    In one embodiment, the body is made in one piece integrally formed. The ejection tube may optionally also be manufactured in the same room as the integrally formed body. The manufacture of the ignition torch can be done for example by an additive method of the 3D printing type.
    The ignition torch may optionally be provided to be operated at several operating points (several mixing ratios).
    To vary the mixing ratio, it is possible, for example, to provide that the torch allows the continuous regulation of fuel feed rates, and / or oxidant, and / or the oxidant reinjection rate.
    For this purpose, in one embodiment the ignition torch further comprises a fuel supply control valve and / or an oxidant supply control valve in the combustion chamber and / or a control valve. of oxidant reinjection, adapted (s) for regulating a respectively fuel feed rate in the combustion chamber, an oxidant feed rate in the combustion chamber, and / or an oxidant injection flow rate in the oxidant reinjection duct.
    The valves indicated above make it possible to vary, possibly in real time during the flight, the mixing ratio, and therefore the flow rate and the temperature of the gases discharged by the ignition torch.
    These valves are naturally controlled by suitable control means, for example an electronic control unit (ECU).
    To act on the fuel or oxidant feed rates, and / or the oxidant feed rate, rather than using one or more control valves, one or more platens with calibrated passage section may be used. Such a plate is a part, normally substantially flat, pierced with one or more passages; the section of this or these passages is determined with precision, so that the flow of fluid which will pass through the plate will be known in advance, as a function of the pressure conditions upstream and downstream of the plate.
    Advantageously, the use of one or more plates controlling the flow rates of fuel or oxidant and / or oxidant reinjection can simultaneously adjust the mixing ratio and control the cooling of the ejection tube.
    Also, in one embodiment, the ignition torch further includes a calibrated passage section fuel supply plate disposed on the fuel supply conduit, and / or a sectional oxidizer feed platen. calibrated passageway disposed on the oxidant supply duct, and / or an oxidizing reinjection platen with a calibrated passage section disposed on the oxidant reinjection duct.
    In one embodiment, at least one of the plates is removable. This allows, simply by replacing the platinum considered by another platen having a different passage section, to change the operation and performance of the ignition torch.
    In one embodiment, the oxidant feed platen and the oxidant reinjection platen form a single platen. This simplifies the structure of the ignition torch.
    A considerable advantage of the ignition torch according to the invention is that its structure makes it possible to reduce the temperature reached by the body of the ignition torch, because of the double combustion indicated above.
    However, additional provisions can be adopted to further reduce the temperature reached by the body and the ejection tube of the ignition torch.
    Thus, in one embodiment, the oxidant reinjection duct is arranged at least in part in a thickness of a wall of the ejection tube.
    The oxidant reinjection duct then serves as a cooling duct for the ejection tube. In particular, a portion of the oxidant reinjection duct may be arranged along the ejection tube, that is to say at a constant distance therefrom. It may for example be separated from the inner duct of the ejection tube by a wall of constant thickness.
    Preferably, the oxidant reinjection duct is made substantially in the thickness of the wall of the ejection tube; it can for example extend in a helix around this tube, on a lathe or on several laps.
    The cooling of the body of the torch can be ensured by the circulation of the fuel and the oxidant in the wall of the body of the torch.
    It can also be provided that the fuel supply conduit and / or the oxidant feed conduit has a baffle formed in the body of the ignition torch. It is considered here that a duct has a baffle when, in a plane passing through a center of the combustion chamber, this duct has at least one elbow (or change of direction, with reference to a direction of circulation of the fluid) angle greater than 90 °, and preferably 120 °.
    Alternatively or additionally, provision may be made for the fuel supply pipe and / or the oxidant feed pipe and / or the oxidant reinjection pipe to comprise a thermal damping portion. By "thermal damping portion" is meant here a portion of conduit which extends into the wall of the body of the torch and in a direction making an angle greater than 45 ° with respect to a radial direction vis-à-vis a center of the combustion chamber. The fluid therefore circulates in the thermal damping portion in a direction making an angle greater than 45 ° with respect to the radial direction: it therefore circulates without coming directly to the combustion chamber. This circulation allows it to exchange heat with the body of the torch and thus to ensure the cooling of it.
    In one embodiment, the fuel supply conduit and / or the oxidant feed conduit covers a large solid angle (for example, at least 2 steradian), relative to a center of the combustion chamber.
    Indeed, to promote heat exchange, the body of the torch is designed so that the exchange surface is maximum, while ensuring, however, that the metal thicknesses are sufficient to ensure the mechanical strength of the torch.
    Fixation
    It is also generally preferable to avoid that the high temperature of the ignition torch is communicated to other parts of the rocket engine.
    Also, in one embodiment, the body has a fastening flange arranged around the ejection tube. Indeed, the temperature of the ejection tube may possibly be lower than that of the body.
    To prevent a temperature increase of this flange, the ignition torch may further comprise a heat insulating passage, arranged radially between an inner duct of the ejection tube and the flange, and fluidically isolated from the reinjection duct. oxidant (that is to say without the possibility of fluid exchange with it). This chamber is preferably in communication with the atmosphere outside the ignition torch. It can be part of the body itself, or the ejection tube, or be arranged at least partly between the two.
    BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood and its advantages will appear better on reading the detailed description which follows, of embodiments shown by way of non-limiting examples. The description refers to the accompanying drawings, in which: - Figure 1 is a schematic sectional view of a rocket engine equipped with an ignition torch in a first embodiment of the invention; FIG. 2 is a schematic perspective view of the ignition torch of FIG. 1; - Figure 3 is a schematic sectional view of the ignition torch of Figure 1; FIG. 3A is a detail view extracted from FIG. 3; and - Figure 4 is a schematic sectional view of an ignition torch in a second embodiment of the invention.
    DETAILED DESCRIPTION OF THE INVENTION
    In the figures, similar or identical elements bear the same numerical reference.
    First embodiment
    With reference to FIG. 1, a rocket motor 100 equipped with an ignition torch 10 according to the invention will now be described.
    The rocket engine 100 is constituted mainly by a nozzle 108 in which its combustion chamber 116 is located. It further comprises a feed circuit 106, which allows its feeding from two propellant tanks 102 and 104, and other equipment not shown.
    The two reservoirs 102 and 104 are respectively a liquid hydrogen reservoir 102 and a liquid oxygen reservoir 104. The hydrogen is therefore the fuel and the oxygen the oxidant. Naturally, although the following description refers to hydrogen as a fuel and oxygen as an oxidant, the invention can be implemented with any other suitable fuel and oxidant pair; also in the description which follows, the terms 'hydrogen' and 'oxygen' must be understood as being able to be replaced respectively by the terms 'fuel' and 'oxidizing', within the meaning of the invention.
    The nozzle 108 mainly comprises the main combustion chamber 116, located in its upper part, and a divergent 118. The ignition torch 10 is fixed at the top of the nozzle 108, to allow combustion of the propellants to be started in the combustion chamber. combustion 116 and thus start the engine 100. (The positions mentioned: 'up', 'down', refer to the usual position of the engine during storage, as shown in the figures, which does not necessarily correspond to engine orientation in operation).
    The supply circuit 106 serves to supply the main combustion chamber 116 of the engine 100 with fuel and oxidant.
    It comprises for that a hydrogen circuit 112 and an oxygen circuit 114, equipped with 115,118 pumps for respectively pumping hydrogen and oxygen from the corresponding reservoir to the combustion chamber 116, in a manner known per se.
    The ignition torch 10 comprises an internal combustion chamber 21, of small dimensions, which is connected by conduits 22 and 24 respectively to the hydrogen circuit 112 and to the oxygen circuit 114.
    The flow rates of hydrogen and oxygen in the ducts 22 and 24 are regulated respectively by control valves 32 and 34, controlled by a not shown electronic control unit.
    The ignition torch 10 further comprises an oxygen reinjection duct 60, the arrangement of which will be specified below. The flow rate therein is also regulated by the control valve 34.
    The ignition torch 10 operates in the following manner.
    This torch is used to ignite the engine 100, that is to say to initiate the combustion of hydrogen and oxygen injected into the combustion chamber 116.
    This combustion is initiated by the gases discharged by the torch 10 into the chamber 116. The temperature of these gases is very high in order to ensure ignition of the propellants in the chamber 116.
    This temperature is part of the conditions imposed on the gases produced by the torch for their injection into the chamber. These conditions are determined to ensure the most complete combustion possible in the combustion chamber, which usually occurs in a main engine rocket chamber at a temperature of the order of 2400K to 3000K. To achieve this objective, in general the temperature of the injected gas is greater than more than 1000K.
    The gases discharged by the torch 10 are produced by the combustion of hydrogen in the oxygen inside the internal combustion chamber 21: hydrogen and oxygen are simultaneously injected into the chamber 21 (via ducts 22 and 24); these are ignited by sparks produced by a spark plug 37 provided in the chamber 21.
    Their combustion produces water vapor at high temperature. The gases produced are therefore a mixture of water vapor and, depending on the hydrogen / oxygen ratio introduced, hydrogen or residual oxygen.
    In addition, the oxygen reinjection duct allows a complementary supply of oxygen at the outlet (or in the vicinity of the outlet) of the ejection tube 40.
    The overall mixing ratio of the torch 10 is therefore determined not only by the amounts of hydrogen and oxygen introduced into the chamber 21, but also by the amount of oxygen injected through the oxygen reinjection duct 60.
    The mixing ratio of the torch 10 can therefore be modulated or controlled by appropriately controlling the fluid flow rates in the ducts 22, 24 and 60 with the aid of the valves 32 and 34 (the valve 34 enables the control of the flow rates at both in ducts 24 and 60, it would have been possible to provide two separate valves).
    The internal structure of the ignition torch 10 will now be described with reference to FIGS. 2, 3 and 3A.
    The torch 10 comprises a body 20 and an ejection tube 40.
    The body 20 is manufactured in additive manufacturing by sintering metal powders.
    Its central part is occupied by the combustion chamber 21. It has an elongate shuttle or ellipsoid shape, having substantially a shape of revolution along the X axis of the ejection tube 40, which is arranged in the extension from the bedroom 21.
    The body 20 is therefore a thick walled enclosure 25 formed around the combustion chamber 21.
    It has three projecting projections 23, 31 and 33 in which are fixed external connections 28, 30 and 35 to pass respectively fuel supply lines (hydrogen) and oxidant (oxygen) 22 and 24, and the conduit oxygen reinjection 60.
    Also, each of the ducts 22, 24 and 60 is formed in several parts: a pipe portion 22e, 24e, 60e, which connects, as the case may be, one or the other of the supply ducts 112, 114 to the body 20 via a control valve 32 or 34; a portion of the external connection 28, 30 or 35 respectively; and an inner pipe portion 22i, 24i, 60i arranged in the thickness of the wall of the body 20 and / or of the tube 40.
    The supply ducts 22i and 24i internal to the body 20 thus serve to conduct hydrogen and oxygen from the external connections 28,30 to the combustion chamber 21.
    The oxygen reinjection duct 60 is connected upstream to the oxygen supply circuit 114. Upstream of the valve 34, it comprises a common pipe portion with the conduit 24 (denoted 24, 60). Downstream of this valve, it comprises a portion of pipe connected to the connection 35. It then comprises an internal portion 60i (also called internal conduit 60i) from the connection 35 to the outlet of the tube 40 at which it therefore allows to inject oxygen to cause the second combustion.
    The combustion chamber 21 allows the combustion of hydrogen in oxygen; this combustion is initiated by a spark plug or any other initiation or energy input system 37 disposed in the combustion chamber.
    This combustion produces combustion gases, which are discharged from the combustion chamber 21 via the ejection tube 40. This being the combustion of hydrogen in oxygen occurs not only in the combustion chamber, but also in the ejection tube 40 and outside thereof in the combustion chamber 116.
    The tube 40 has two ends: a first end through which it is connected to the body 20, and a second end or outlet 44, which is placed in the main combustion chamber 116 of the rocket engine. (More generally, the output of an ignition torch according to the invention could be placed in the main combustion chamber or in a gas generator or 'prechamber' of a rocket engine).
    The tube 40 has an internal duct 46 which starts from the combustion chamber 21 and opens into the main combustion chamber 116.
    In order to reduce the mechanical stresses in the body which may be caused by the very high temperature differences between the propellants (hydrogen, oxygen) which are or may be extremely cold, and the combustion gases which on the contrary are hot, the following provisions are adopted.
    First, the wall of the body is particularly thick; the internal conduits 22i, 24i supplying hydrogen and oxygen do not inject hydrogen or oxygen directly into the combustion chamber 21 but instead have baffles in the thickness of the wall 25 so that the fluid they transport is partially heated before being injected into the chamber 21. This therefore reduces the temperature of the wall 25.
    Internal conduit 22i for supplying hydrogen
    To promote the heat exchange between the hydrogen and the torch body (FIGS. 3 and 3A), the hydrogen supply internal conduit 22i has a cylindrical intermediate chamber 26 which surrounds the combustion chamber 21 (at least in a view along the axis of the tube 40).
    This cylindrical chamber forms a portion of thermal damping. In this chamber, the hydrogen flows in a direction D which, in the plane of section, is parallel to the axis X of the ejection tube: this direction D forms an angle β with respect to the radial direction (screw with respect to the center C of the combustion chamber); the angle β is 90 ° and is therefore significantly greater than 45 °.
    In the intermediate chamber 26, the hydrogen thus circulates inside the wall 25 without approaching the combustion chamber 21; this allows large heat exchanges to take place between the hydrogen and the body 20 and thus the temperature of the body 20 does not rise unacceptably.
    Upstream, the intermediate chamber 26 is connected to the connection 28 by a connecting section 29. Downstream, the intermediate chamber 26 is connected to the combustion chamber 21 through injection holes 27.
    As can be seen in FIG. 3A (detail extracted from the axial section of FIG. 3), the hydrogen supply duct 22 has, in the plane of section (which passes through the center C of the combustion chamber 21 ), at least one elbow angle greater than 120 °.
    Thus, in this embodiment, the hydrogen supply duct 22 comprises a baffle; the fuel (hydrogen) is therefore forced to circulate in the wall 25 of the body 20 over a certain distance, which favors the heat exchange between the hydrogen and the body 20 and thus makes it possible to maintain the latter at a temperature sufficiently low.
    Internal conduit 24i oxygen supply
    The internal conduit 24i connects the connector 30 to oxygen injection holes 39 formed in the wall of the combustion chamber 21. Oxvaene reincorporation conduit 60
    The internal duct 60i is arranged in the thickness first of the body 20, then further downstream in the thickness of the ejection tube 40.
    Like conduit 22i, conduit 60i has a thermal damping portion constituted by an intermediate chamber 61. This chamber has a shape of revolution about the X axis and is arranged around the end of the chamber 21 located on the side ejection tube 40. The conduit 60i connects the chamber 61 to the connector 35 via a conduit portion not shown.
    Downstream of the chamber 61, the conduit 60i is arranged inside the wall of the tube 40. In this part, the conduit 60i forms a helix 63 with several turns around the tube 40, which makes it possible to maximize heat exchange between the tube 40 and the oxygen. At the end of the tube 40, the conduit 601 opens into the combustion chamber 116 of the engine 100. It therefore releases the oxygen substantially at the point of exit of the gases discharged by the ejection tube 40.
    Fixation
    The ignition torch 10 further has a fastening flange 70 arranged around the tube 40 and which serves to fix it on. the nozzle 108.
    For this purpose, between the body 20 and the flange 70, the wall of the tube 40 is very thick; it thus has sufficient mechanical strength to transmit the weight of the body 20 to the flange 70.
    This thickness is used to thermally insulate the tube 40 of the flange, and thus prevent a rise in temperature thereof.
    Indeed, the tube 40 has a heat insulating passage 48. This passage is arranged radially between the inner conduit 46 of the tube 40 and the flange 70.
    It extends more axially (on the X axis) upstream and downstream relative to the plane of attachment of the flange 70 on the tube 40.
    The passage 48 is isolated from the fluids (respectively combustion gas and oxygen) circulating in the conduits 46 and 60; it is in communication only with the atmosphere surrounding the torch 10.
    In the embodiment shown, the passageway 48 communicates with the atmosphere located on the side opposite the body 20, with respect to the flange 70. In another embodiment, the chamber 48 could communicate with the atmosphere on the same side that the body 20 with respect to the flange 70.
    Second embodiment
    A second embodiment of the ignition torch 10 will now be presented in relation with FIG. 4. This second embodiment is identical to the first embodiment, with the exception of certain characteristics that will be specified below. .
    The difference between the first and second embodiments is the oxygen and hydrogen regulation mode.
    In the first embodiment, the valves 32 and 34 make it possible to regulate each of the flow rates of hydrogen and oxygen in the conduits 22, 24 and 60.
    In contrast, in the second embodiment these three flow rates are not regulated by control valves but are simply controlled by the use of calibrated passage section plates.
    In the embodiment shown, to simplify manufacture, the body 20 does not have projecting projection 33, and therefore no external connection 35.
    In this embodiment, since the connection 30, the same pipe 24e, 60e constitutes the outer portion of the conduit 24 and the conduit 60. This pipe connects the connector 30 directly to the circuit 114; there is no control valve 34.
    Similarly another pipe forms the conduit 22e and directly connects the connector 28 to the circuit 112; there is also no control valve 32.
    The inner pipe 24i and the inner pipe 60i are both connected upstream to a calibrated plate 52, disposed against the connector 30 and connected to the conduit 24e, 60e via the latter.
    The calibrated platen 52 is a disk-shaped plate having two calibrated orifices 54 and 55. The calibrated orifices 54 form restrictions which control the flow of fluid respectively in the ducts 24i and 60i.
    Advantageously, the plate 52 is removable: After unscrewing the connector 30, it is easy to disassemble the plate to replace it with another.
    For example, it is possible to replace a plate 52 with another plate 52 'whose calibrated orifices 54' and 55 'have passage sections different from those of the passages 54 and 55: this change then makes it possible in a simple way to modify the mixing ratio of the torch 10 as well as the cooling mode of the tube 40.
    Although the present invention has been described with reference to specific exemplary embodiments, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In addition, individual features of the various embodiments mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    An ignition torch (10) for a rocket motor, comprising: a body (20) in which a combustion chamber (21) is provided; an ejection tube (40) for exhausting combustion gases exiting the combustion chamber; the body (20) being configured to allow the supply of fuel and oxidant to the combustion chamber via respectively a fuel supply pipe (22) and an oxidant supply pipe (24); the ignition torch (10) being characterized in that it further comprises an oxidant reinjection duct (60) configured to allow an oxidant injection substantially at the outlet of the ejection tube (40).
    [2" id="c-fr-0002]
    The ignition torch (10) of claim 1, further comprising a fuel supply control valve (32) and / or an oxidant supply control valve (34) in the combustion chamber and / or an oxidant reinjection control valve (32) adapted to regulate a fuel supply flow respectively in the combustion chamber, an oxidant feed rate in the combustion chamber, and / or an oxidant injection rate in the oxidant reinjection conduit (60).
    [3" id="c-fr-0003]
    An ignition torch according to claim 1 or 2, further comprising a fuel supply plate (52) of calibrated passage section disposed on the fuel supply conduit, and / or a fuel supply stage. oxidizer with a calibrated passage section disposed on the oxidant feed duct, and / or an oxidizing reinjection platen with a calibrated passage section disposed on the oxidant reinjection duct.
    [4" id="c-fr-0004]
    4. ignition torch (10) according to claim 3, wherein said plate (52) or at least one of said plates is removable.
    [5" id="c-fr-0005]
    5. Ignition torch (10) according to any one of claims 1 to 4, wherein the oxidizer feed platen and the oxidant reinjection platen form a single platen (52).
    [6" id="c-fr-0006]
    The ignition torch (10) according to any one of claims 1 to 5, wherein the oxidant reinjection duct (60) is arranged at least partly in a thickness of a wall of the ejection tube ( 40).
    [7" id="c-fr-0007]
    The ignition torch (10) according to any one of claims 1 to 6, wherein the fuel supply conduit (22) and / or the oxidant feed conduit (24) has a baffle formed in the body (20) of the ignition torch (10).
    [8" id="c-fr-0008]
    The ignition torch (10) according to any one of claims 1 to 7, wherein the fuel supply duct (22) and / or the oxidant supply duct (24) and / or the duct (60) includes a thermal damping portion (26) that extends into the wall (25) of the torch body (20) in a direction at an angle greater than 45 ° to a radial direction vis-à-vis a center (C) of the combustion chamber (21).
    [9" id="c-fr-0009]
    9. An ignition torch (10) according to any one of claims 1 to 8, having a fastening flange arranged around the ejection tube, and a passage (48) of thermal insulation, arranged radially between an inner duct. (46) of the ejection tube and the flange (70), and fluidly isolated from the oxidant reinjection duct.
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    同族专利:
    公开号 | 公开日
    JP2017075604A|2017-04-20|
    JP6246881B2|2017-12-13|
    EP3156635A1|2017-04-19|
    RU2016140562A|2018-04-16|
    US20170107946A1|2017-04-20|
    FR3042543B1|2019-08-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20040231318A1|2003-05-19|2004-11-25|Fisher Steven C.|Bi-propellant injector with flame-holding zone igniter|
    US20080264372A1|2007-03-19|2008-10-30|Sisk David B|Two-stage ignition system|
    JPH0814561A|1994-06-29|1996-01-19|Ishikawajima Harima Heavy Ind Co Ltd|Pilot torch|
    CN103644044B|2013-11-26|2015-10-28|北京航空航天大学|Be applied to polychormism simulated engine and the ignition schemes thereof of the research of Vacuum Plume effect experiment|CN109578167B|2018-11-21|2019-12-13|中国人民解放军国防科技大学|Engine injector and engine with same|
    DE102019100090A1|2019-01-04|2020-07-09|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Ignition device and method for operating the ignition device|
    JP6993752B1|2020-08-04|2022-01-14|紀和化学工業株式会社|Graphic sheet, graphic sheet with protective film, its manufacturing method and its usage|
    法律状态:
    2016-10-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-21| PLSC| Publication of the preliminary search report|Effective date: 20170421 |
    2017-10-23| PLFP| Fee payment|Year of fee payment: 3 |
    2018-10-23| PLFP| Fee payment|Year of fee payment: 4 |
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    2021-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559765|2015-10-14|
    FR1559765A|FR3042543B1|2015-10-14|2015-10-14|IGNITION TORCH FOR FUSE MOTOR|FR1559765A| FR3042543B1|2015-10-14|2015-10-14|IGNITION TORCH FOR FUSE MOTOR|
    JP2016201501A| JP6246881B2|2015-10-14|2016-10-13|Rocket engine with versatile ignition torch|
    EP16193763.6A| EP3156635A1|2015-10-14|2016-10-13|Rocket engine with versatile lighter|
    US15/292,227| US20170107946A1|2015-10-14|2016-10-13|Rocket engine with a versatile ignition torch|
    RU2016140562A| RU2016140562A|2015-10-14|2016-10-14|UNIVERSAL IGNITION ROCKET ENGINE|
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