End face combustion solid-liquid fuel gas generator

Abstract

The invention discloses an end face combustion solid-liquid fuel gas generator which comprises a combustion chamber and a solid grain arranged in the combustion chamber, an exhaust port communicated with a combustion cavity is formed in one end of the combustion chamber, and the end, facing the exhaust port, of the solid grain is a combustion end. A space formed by the end face of the combustion end and the cavity wall of the end, provided with the exhaust port, of the combustion cavity is a combustion space, the spring is arranged in the combustion cavity, and the cavity wall, located between the end of the non-combustion end of the solid grain and the cavity wall of the combustion cavity, of the combustion cavity is provided with an annular groove capable of abutting against the combustion end. The movement of the solid grain towards the exhaust port is limited; the annular groove enables the two ends of the spring to abut against the solid grain and the combustion cavity respectively and to be in a compressed state, so that elastic force for moving towards the exhaust port is continuously applied to the solid grain, and the combustion space is kept unchanged in the combustion process of the solid grain.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field, and particularly relates to a solid-liquid fuel gas generator with end-face combustion. BACKGROUND

[0002] The fuel gas generator is one of important components in the field of combined ramjet, which is used to generate high-temperature and high-pressure rich fuel gas to produce thrust by secondary combustion with the incoming flow.

[0003] The solid-liquid fuel gas generator with end-face combustion has the advantages of constant combustion surface and relatively stable combustion condition. However, the solid-liquid fuel gas generator with end-face combustion has a key restriction, that is, the solid propellant combustion surface will retreat, the combustion space will expand, the relative position between the oxidizer injection hole and the combustion surface will change, the high-speed oxidizer jet at the outlet of the injection hole needs to pass through a longer fuel gas layer to reach the new combustion surface, which leads to the decrease of the mixing efficiency of the oxidizer and the fuel, and the combustion condition will be deviated. Moreover, when the mixing efficiency decreases to a certain degree, the fuel gas generator is prone to flameout.

[0004] In summary, in the combustion process of the existing solid-liquid fuel gas generator with end-face combustion, the solid propellant combustion surface retreats, which leads to the expansion of the combustion space. SUMMARY

[0005] The present application relates to the technical field, and particularly relates to a solid-liquid fuel gas generator with end-face combustion.

[0006] To solve the above technical problems, the present application specifically provides the following technical scheme:

[0007] The end-face combustion solid-liquid-gas generator comprises a combustion chamber with a combustion cavity inside, an exhaust port being opened at one end of the combustion chamber and being communicated with the combustion cavity; a solid propellant column being arranged inside the combustion cavity and being movable along its axis inside the combustion cavity, the side wall of the solid propellant column being attached to the cavity wall of the combustion cavity, and the end of the solid propellant column towards the exhaust port being a combustion end, wherein the end face of the combustion end and the space formed by the cavity wall of the combustion cavity at one end of the exhaust port are a combustion space; a spring being arranged inside the combustion cavity and being located between the end of the non-combustion end of the solid propellant column and the cavity wall of the combustion cavity, the cavity wall of the combustion cavity being provided with an annular groove capable of abutting against the combustion end to limit the movement of the solid propellant column towards the exhaust port; and the position of the annular groove is arranged so that the two ends of the spring abut against the solid propellant column and the combustion cavity respectively and are in a compressed state to continuously apply an elastic force to the solid propellant column to move towards the exhaust port, so that the combustion space remains unchanged during the combustion of the solid propellant column; an oxidant channel being opened on the side wall of the combustion chamber and being communicated with the combustion space; and a multifunctional channel being opened on the side wall of the combustion chamber and being communicated with the combustion space.

[0008] Further, the combustion chamber comprises a cylindrical barrel and a sealing flange and a nozzle arranged at two ends of the cylindrical barrel respectively, wherein the nozzle is a conical pipe, the large end of the nozzle is connected to the end of the cylindrical barrel, and the small end of the nozzle is the exhaust port; the oxidant channel and the multifunctional channel are opened on the barrel wall of the cylindrical barrel.

[0009] Further, an installation flange wrapping the nozzle is arranged outside the nozzle, the installation flange is connected to the end of the cylindrical barrel to make the end of the nozzle abut against and seal with the end of the cylindrical barrel, and a heat insulation layer is arranged between the installation flange and the nozzle.

[0010] Further, the combustion end of the solid propellant column is a conical surface structure to increase the combustion surface area.

[0011] Further, a heat insulation layer is arranged on the inner cavity wall of the combustion cavity and attached to the solid propellant column.

[0012] Further, a support plate is arranged at the end of the spring abutting against the solid propellant column, and the support plate abuts against the solid propellant column.

[0013] Further, a plurality of oxidant channels are arranged and are distributed in a circumferential spiral manner to guide the generation of rotational flow in the combustion space.

[0014] Further, the multifunctional channels are provided with a plurality of channels, which can be used for ignition, monitoring pressure of the combustion chamber and monitoring temperature of the gas respectively.

[0015] Compared with the prior art, the present application has the following advantages:

[0016] The end-face combustion solid-liquid gas generator provided by the present application can steadily feed the solid propellant column to the direction of the annular groove by the cooperation of the annular groove and the spring, so that the burning end of the solid propellant column is always located at the annular groove, the burning surface does not move, the whole combustion space remains unchanged, and the stability of combustion is ensured. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the following embodiment or prior art description will be briefly introduced. Obviously, the drawings in the following description are only exemplary, and other drawings can be obtained by the provided drawings without creative labor for those skilled in the art.

[0018] Figure 1 Fig. 1 is an external schematic view of the end-face combustion solid-liquid gas generator;

[0019] Figure 2 Fig. 2 is a schematic view of the internal structure of the end-face combustion solid-liquid gas generator;

[0020] Figure 3 Fig. 3 is a schematic view of the distribution of the oxidant channel and the multifunctional channel;

[0021] Figure 4 Fig. 4 is a curve diagram of the internal pressure of the combustion chamber when the solid propellant column is burning.

[0022] The reference numerals in the drawings represent the following respectively:

[0023] 1-combustion chamber, 11-combustion chamber, 12-combustion space, 13-exhaust port;

[0024] 101-cylindrical body, 102-sealing flange, 103-nozzle, 104-mounting flange, 105-thermal insulation layer;

[0025] 2-solid propellant column, 21-burning end, 22-thermal insulation layer;

[0026] 3-spring, 31-supporting plate;

[0027] 4-oxidant channel;

[0028] 5-multifunctional channel. DETAILED DESCRIPTION

[0029] With reference to the drawings of the embodiments of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all the other embodiments obtained by those of ordinary skill in the art without creative work fall within the scope of the present application.

[0030] As shown in the drawings, Figure 1 The present application provides a face-burning solid-liquid fuel gas generator. The solid fuel column 2 is steadily fed towards the annular groove by the spring 3 during the whole combustion process, and the burning end 21 of the solid fuel column 2 is always located at the annular groove, so that the burning surface will not move.

[0031] The combustion chamber 1 is made of high-temperature-resistant alloy material and has a combustion chamber 11 inside. An exhaust port 13 is formed at one end of the combustion chamber 1 and is connected to the combustion chamber 11.

[0032] To facilitate the movement of the solid fuel column 2 in the combustion chamber 11, the combustion chamber 11 is in a cylindrical structure, preferably a circular cylindrical structure. The cavity wall is precisely ground to ensure close fitting with the solid fuel column 2 and to ensure sealing.

[0033] The exhaust port 13 is in a conical structure, which can effectively accelerate the exhaust speed of the combustion products and improve the exhaust efficiency.

[0034] The solid fuel column 2 is in a cylindrical structure with a cross section matching the combustion chamber 11. It is arranged inside the combustion chamber 11 along the axis of the combustion chamber 11 and can move inside the combustion chamber 11 along its own axis. The end of the solid fuel column 2 towards the exhaust port 13 is the burning end 21. The space formed by the end face of the burning end 21 and the cavity wall of the combustion chamber 11 with the exhaust port 13 at one end is the combustion space 12.

[0035] Specifically, the solid fuel column 2 is pressed from high-energy composite propellant, preferably HTPB fuel or paraffin fuel. Further, the solid fuel column 2 fuel composition also includes aluminum powder and magnesium powder to increase the combustion heat value.

[0036] A spring 3 is arranged between the end of the solid fuel column 2 and the cavity wall of the combustion chamber 11. The cavity wall of the combustion chamber 11 has an annular groove that can abut against the burning end 21 to limit the movement of the solid fuel column 2 towards the exhaust port 13.

[0037] Specifically, the position of the annular groove is set as follows: when the burning end 21 of the solid propellant 2 abuts against the inner groove, the two ends of the spring 3 abut against the solid propellant 2 and the combustion chamber 11 respectively and are in a compressed state; at this time, the spring 3 can continuously exert a spring force on the solid propellant 2 to move towards the exhaust port 13. During the combustion of the solid propellant 2, as the solid propellant is continuously consumed, the spring 3 is gradually elongated to push the solid propellant 2 to move towards the exhaust port 13, so that the volume of the combustion space 12 is always kept unchanged, thereby ensuring the stability of the combustion process.

[0038] A plurality of oxidant channels 4 and multifunctional channels 5 are formed in the side wall of the combustion chamber 1 and are in communication with the combustion space 12.

[0039] Specifically, the oxidant channel 4 is made of stainless steel and is polished inside to reduce the resistance of the oxidant flow; a precise flow control valve is arranged at the inlet of the oxidant channel 4, which can adjust the supply amount of the oxidant in real time according to the pressure and temperature changes in the combustion space 12, so as to ensure the full combustion reaction.

[0040] The multifunctional channel 5 is used to realize multiple functions, and a standard quick connector is arranged at the end of the multifunctional channel 5 for convenient connection with various detection and control devices.

[0041] The present embodiment provides the following examples for the combustion chamber 1.

[0042] As shown in the figure, the combustion chamber 1 includes a cylindrical body 101 and a sealing flange 102 and a nozzle 103 arranged at the two ends of the cylindrical body 101 respectively, wherein the nozzle 103 is a tapered pipe, one end of the nozzle 103 with a large opening is connected with the end of the cylindrical body 101, and the other end of the nozzle 103 with a small opening is the exhaust port 13; the oxidant channel 4 and the multifunctional channel 5 are formed in the wall of the cylindrical body 101.

[0043] Further, an installation flange 104 is arranged outside the nozzle 103 to wrap the nozzle 103, and the installation flange 104 is connected with the end of the cylindrical body 101 to make the end of the nozzle 103 abut against and seal with the end of the cylindrical body 101, wherein an insulating layer 105 is arranged between the installation flange 104 and the nozzle 103.

[0044] An annular sealing groove is formed in the connecting end face of the cylindrical body 101, and a nickel-based alloy wound gasket is embedded in the groove, so that when the installation flange 104 is fastened by bolts, the end face of the nozzle 103 and the end face of the cylindrical body 101 are sealed by the gasket.

[0045] The insulating layer 105 is made of polyimide, phenolic resin or high-silicon fiber material.

[0046] The embodiment provides the following examples for the solid propellant 2.

[0047] The burning end 21 of the solid propellant 2 is in a conical surface structure, so as to increase the burning surface area, thereby reducing the diameter of the propellant and improving the volume utilization.

[0048] The inner cavity wall of the combustion cavity 11 is provided with a heat insulation layer 22 which is attached to the solid propellant 2.

[0049] Specifically, the heat insulation layer 22 is made of polyimide, phenolic resin or high-silicon fiber material.

[0050] The end of the spring 3 abutting against the solid propellant 2 is provided with a support plate 31, the support plate 31 abuts against the solid propellant 2, and the edge of the support plate 31 is attached to the heat insulation layer 22.

[0051] Specifically, the spring 3 is a sealing spring, and is made of high-temperature alloy material so as to maintain the rigidity under high temperature.

[0052] The support plate 31 is made of polyimide, phenolic resin or high-silicon fiber material.

[0053] The oxidant channel 4 is provided with multiple, preferably four, circumferential spiral distribution, so as to guide the rotational flow generated in the combustion space 12, thereby improving the burning surface recession rate of the solid propellant 2.

[0054] The multifunctional channel 5 is provided with multiple, at least one for ignition, one for monitoring the pressure of the combustion cavity 11, and two for monitoring the gas temperature.

[0055] Specifically, the multifunctional channel 5 is provided with four, one of which is used for ignition, one is used for pressure measurement, and the other two are used for temperature measurement.

[0056] The embodiment is based on the laboratory scale solid-liquid gas generator ground test bench, and verification experiments are carried out.

[0057] The experimental results are shown in Figure 4 The combustion process of the end-face combustion solid-liquid gas generator after ignition is very stable, the present application stabilizes the feeding of the solid propellant, so that the whole combustion space remains unchanged during the combustion process of the solid propellant, and the long-time combustion capacity and combustion stability of the end-face combustion solid-liquid gas generator are ensured.

[0058] The above examples are only exemplary embodiments of the present application, and are not used to limit the present application, the protection scope of the present application is defined by the claims. Those skilled in the art can make various modifications or equivalent replacements to the present application within the spirit and protection scope of the present application, and such modifications or equivalent replacements are also regarded as falling within the protection scope of the present application.

Claims

1. A liquid-gas solid fuel end-fired combustion generator, characterized by, The combustion chamber (1) comprises a combustion chamber (11) inside, an exhaust port (13) is opened at one end of the combustion chamber (1) and communicated with the combustion chamber (11); A solid propellant column (2) is arranged inside the combustion chamber (11) and can move along its axis inside the combustion chamber (11), the side wall of the solid propellant column (2) is attached to the cavity wall of the combustion chamber (11), the end of the solid propellant column (2) towards the exhaust port (13) is a combustion end (21), wherein the space formed by the end face of the combustion end (21) and the cavity wall of the combustion chamber (11) with the exhaust port (13) at one end is a combustion space (12); A spring (3) is arranged inside the combustion chamber (11) and between the end of the non-combustion end (21) of the solid propellant column (2) and the cavity wall of the combustion chamber (11), the cavity wall of the combustion chamber (11) is provided with an annular groove capable of abutting against the combustion end (21) to limit the movement of the solid propellant column (2) towards the exhaust port (13); The position of the annular groove is arranged so that the two ends of the spring (3) are respectively abutted against the solid propellant column (2) and the combustion chamber (11) and are in a compressed state to continuously apply a spring force to the solid propellant column (2) to move towards the exhaust port (13), so that the combustion space (12) remains unchanged during the combustion of the solid propellant column (2); An oxidant channel (4) is opened on the side wall of the combustion chamber (1) and communicated with the combustion space (12); A multifunctional channel (5) is opened on the side wall of the combustion chamber (1) and communicated with the combustion space (12). The combustion chamber (1) comprises a cylindrical barrel (101) and a sealing flange (102) and a nozzle (103) arranged at both ends of the cylindrical barrel (101), wherein the nozzle (103) is a conical pipe, the large end of the nozzle (103) is connected with the end of the cylindrical barrel (101), and the small end of the nozzle (103) is the exhaust port (13); 2. The end-fired, solid-liquid fuel, gas generator of claim 1, wherein, The oxidant channel (4) and the multifunctional channel (5) are opened on the barrel wall of the cylindrical barrel (101). An installation flange (104) is arranged outside the nozzle (103) to wrap itself, the installation flange (104) is connected with the end of the cylindrical barrel (101) to make the end of the nozzle (103) abut against and seal with the end of the cylindrical barrel (101), wherein an insulating layer (105) is arranged between the installation flange (104) and the nozzle (103).

3. The end-fired solid-gas liquid fuel generator of claim 2, wherein The combustion end (21) of the solid propellant column (2) is a conical surface structure to increase the burning surface area.

4. The end-fired solid-gas liquid fuelled combustor as claimed in claim 1 or 3 wherein, An insulating layer (22) is arranged on the inner cavity wall of the combustion chamber (11) and attached to the solid propellant column (2).

5. The end-fired solid-liquid fuel gas generator of claim 4, wherein ​ 6. The end-fired, solid-liquid fuel, gas generator of claim 5, wherein, A support plate (31) is arranged at the end of the spring (3) abutting against the solid propellant (2), the support plate (31) abuts against the solid propellant (2), and the edge of the support plate (31) is attached to the heat insulation layer (22).

7. The end-fired, solid-liquid-gas combustor of claim 1, wherein The oxidant channels (4) are arranged in multiple numbers and are distributed in a circular spiral manner to guide the generation of a rotating flow in the combustion space (12).

8. The end-fired, solid-liquid fuel, gas generator of claim 7, wherein, The multifunctional channels (5) are arranged in multiple numbers and can be used for ignition, monitoring the pressure of the combustion chamber (11) and monitoring the gas temperature respectively.

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