A gas generator

Abstract

A gas generator is composed of an injector, an eccentric spoiler ring, a spherical cone combustion chamber and a three-way elbow, wherein the injector is in a round cake shape and is printed by a 3D printer as a whole, the upper half of the eccentric spoiler ring is a cylindrical ring, the top surface of the cylindrical ring is fixedly connected to the bottom edge of the lower boss of the injector by welding, the bottom edge of the side of the cylindrical ring is fixedly connected to the side hole wall of the spherical cone combustion chamber by welding, and the lower half of the eccentric spoiler ring is an open eccentric conical ring; the spherical cone combustion chamber includes a spherical cavity and a conical cavity, wherein the side of the spherical cavity is provided with a side hole, the top of the conical cavity is provided with an outlet, the outlet is fixedly connected to the middle inlet of the three-way elbow by welding, the three-way elbow is in a side T-shape as a whole, the left side of the three-way elbow is a left port, which adopts a flange structure connection form, the right side is a right port, the middle part is a middle inlet, which adopts a boss positioning form. The present invention optimizes the structure of the gas generator, can make the propellant efficiently atomized, mixed and burned, and improves the combustion efficiency.

Description

Technical Field

[0001] The invention relates to a gas generator, which belongs to the technical field of aerospace and liquid rocket engines and is used for a power supply system of a liquid rocket engine. Background Art

[0002] Liquid rockets are generally composed of fairings, instrument cabins, interstages, oxidizer tanks and fuel tanks, pressurization and delivery systems, engines, tail sections, etc. Liquid rocket engines are mainly composed of gas generators, turbo pumps, thrust chambers, and various valves and pipelines. The role of the gas generator in a liquid engine is to atomize, mix, and burn the propellant to produce high-energy, high-temperature, and high-pressure combustion gas, which then expands further to do work and drive the turbine to run at high speed, thereby driving the turbo pump to make the liquid rocket engine work and provide power for the entire rocket. The gas generator is mainly composed of injectors, spoiler rings, and combustion chambers;

[0003] At present, the gas generators used in domestic and foreign gas generators are mostly welded together from scattered sheet metal parts. Not only are they complex in structure, but they are also difficult to manufacture. In particular, a large number of nozzles in the injector part are completed through welding, and the accuracy is difficult to guarantee, resulting in poor propellant atomization effect. In addition, the spoiler ring does not have an eccentric function, and the combustion chamber is mostly a regular cylindrical structure, which makes the propellant mixing effect poor. Therefore, the propellant cannot burn efficiently in the combustion chamber, some of which lead to low combustion efficiency, some lead to high temperatures in some parts of the gas generator, and even burn the gas generator. In addition, the uneven outlet gas temperature causes great damage to the rocket engine power supply system. Summary of the invention

[0004] The technical problem solved by the present invention is: changing the design and manufacturing scheme of the existing gas generator injector, spoiler ring and combustion chamber, changing the method of atomizing and mixing the propellant, overcoming the problem of low combustion efficiency and even high temperature in the gas generator part, which seriously affects the working performance of the gas generator;

[0005] The technical solution of the present invention is: a gas generator, comprising an injector (1), an eccentric spoiler ring (2), a spherical cone combustion chamber (3) and a three-way elbow (4), wherein the injector (1) is in a round cake shape, a lower boss (13) is provided at the bottom thereof, and the whole is printed by a 3D printer; the upper half of the eccentric spoiler ring (2) is a cylindrical ring (21), the top surface of the cylindrical ring (21) is fixedly connected to the bottom edge of the lower boss (13) of the injector (1) by welding, the lower half of the eccentric spoiler ring (2) is an open eccentric conical ring (22), the open cavity (23) formed inside the conical ring (22) faces the spherical surface of the spherical cone combustion chamber (3); the spherical cone combustion chamber (3) is a hollow shell composed of a sphere and a cone, the spherical surface of the spherical cone is tangent to the side surface of the bottom of the cone, and the spherical cone combustion chamber (3) is a hollow shell composed of a sphere and a cone, the spherical surface of the spherical cone is tangent to the bottom side of the cone, and the spherical cone combustion chamber (3) is a hollow shell composed of a sphere and a cone. ) comprises a spherical cavity (32) and a conical cavity (33), wherein a side hole (31) is opened on the side of the spherical cavity (32), and the hole wall of the side hole (31) is fixedly connected to the side bottom edge of the cylindrical ring (21) by welding; an outlet (34) is opened on the top of the conical cavity (33), and the outlet (34) is fixedly connected to the middle inlet (41) of the three-way elbow (4) by welding; the three-way elbow (4) is in a side T-shape as a whole, the left side of the three-way elbow (4) is a left port (43), which adopts a flange structure connection form, and the right side of the three-way elbow (4) is a right port (42), which is used to be fixedly connected to the inlet of the liquid rocket engine power supply system by welding, and the middle part of the three-way elbow (4) is the middle inlet (41), which adopts a boss positioning form and is fixedly connected to the outlet (34) of the spherical cone combustion chamber (3) by welding;

[0006] The injector (1) is provided with a conical oxidant nozzle (11) at the top, and the nozzle (11) has a nozzle cavity (111) inside; the injector (1) has an oxidant cavity (112) in the middle, and the nozzle cavity (111) is connected to the oxidant cavity (112); a cylindrical fuel agent nozzle (12) is provided on the side of the injector (1), and the nozzle (12) has a nozzle cavity (121) inside; an annular fuel agent cavity (122) is provided around the circumference of the injector (1), and the nozzle cavity (121) is connected to the annular fuel agent cavity (122); the injector (1) has a A lower boss (13), wherein regularly arranged flow channel holes (14), a three-shot injection hole group (15) and a fuel agent cooling hole (16) are provided in the lower boss (13); the flow channel hole (14) is communicated with the fuel agent cavity (122); the three-shot injection hole group (15) includes two fuel agent holes (151) and one oxidant hole (152), wherein the fuel agent hole (151) is communicated with the flow channel hole (14), and the oxidant hole (152) is communicated with the oxidant cavity (112); and the fuel agent cooling hole (16) is communicated with the fuel agent cavity (122);

[0007] The flow passage holes (14) are uniformly distributed along the annular fuel cavity (122), and the flow passage holes (14) are divided into three groups. The length of the flow passage holes (14) in the first group is 5 mm to 55 mm smaller than the radius of the lower boss (13); the length of the flow passage holes (14) in the second group is 20 mm to 70 mm smaller than the radius of the lower boss (13); and the length of the flow passage holes (14) in the third group is 40 mm to 90 mm smaller than the radius of the lower boss (13); the flow passage holes uniformly distributed in an interval form in the first group of flow passage holes (14) are interconnected in a radial direction;

[0008] The one oxidant hole (152) is located between the two fuel holes (151), the axes of the two fuel holes (151) and the axis of the one oxidant hole (152) are at an angle of 10° to 80°, and the three axes intersect at one point;

[0009] The fuel cooling holes (16) are located in the bottom edge region of the lower boss (13) and are evenly distributed along the circumference;

[0010] The angle between the axis of the cylindrical ring (21) and the axis of the conical ring (22) is 110° to 160°;

[0011] The angle between the axis of the side hole (31) and the axis of the outlet (34) is 100° to 170°;

[0012] The gas generator of the present invention has the following working process: when the fuel enters the annular fuel cavity (122) through the nozzle cavity (121) of the fuel nozzle (12), flows through the flow channel hole (14), and then is sprayed into the inner cavity of the cylindrical ring (21) of the eccentric spoiler ring (2) through the fuel hole (151) of the three-strike injection hole group (15); the oxidant enters the oxidant cavity (112) through the oxidant nozzle (111), and then is sprayed into the inner cavity of the cylindrical ring (21) of the eccentric spoiler ring (2) through the oxidant hole (152) of the three-strike injection hole group (15); the two fuel holes (151) of the three-strike injection hole group (15) spray two streams of fuel and one oxidant. A stream of oxidant injected through the hole (152) impacts the inner cavity of the cylindrical ring (21) to be atomized, mixed and burned, and combustion produces combustion gas; at the same time, the fuel agent is directly injected into the inner cavity of the cylindrical ring (21) of the eccentric spoiler ring (2) through the fuel agent cooling hole (16) in the bottom edge area of ​​the lower boss (13). Since the injected fuel agent has a much lower temperature than the combustion environment, it evaporates in the high temperature environment of the inner cavity of the cylindrical ring (21) to form an edge cooling layer, which not only reduces the wall temperature, but also enhances the mixing effect, thereby avoiding high temperature in the local area of ​​the gas generator; the unevaporated fuel agent impacts the inner wall surface of the conical ring (22) of the eccentric spoiler ring (2) to form a cooling liquid film, thereby avoiding the eccentric spoiler ring (2) from being burned. The eccentric spoiler ring (2) guides the combustion gas in the inner cavity of the cylindrical ring (21) to the spherical surface of the spherical cavity (32). Since the open cavity (23) formed inside the conical ring (22) of the eccentric spoiler ring (2) has a cavity that gradually transitions from the bottom to the top of the conical ring (22), the cavity gradually shrinks, and the combustion gas is compressed in the open cavity (23) to form a first recirculation vortex, which is beneficial to further mixing and combustion of unburned fuel and oxidant, thereby improving the combustion efficiency. The recirculation vortex stabilizes the combustion flame. When the combustion gas passes through the conical ring (22) of the eccentric spoiler ring (2) and enters the spherical cavity (32) of the spherical cone combustion chamber (3), the cavity suddenly increases, so that the combustion gas is compressed in the open cavity (23). It expands rapidly, forming a second recirculation vortex along the wall of the spherical cavity (32); when the gas enters the spherical cavity (32), it will reach the back of the conical ring (22) of the eccentric spoiler ring (2) due to diffusion, forming a third recirculation vortex; when the gas passes through the conical cavity (33) of the spherical cone combustion chamber (3), the gas is compressed again because its volume gradually changes from the bottom to the top of the conical cavity (33), and the volume gradually shrinks; when the gas enters the inner cavity of the middle inlet (41) of the three-way elbow (4), the inner cavity of the middle inlet (41) is connected with the inner cavity of the right port (42) and the inner cavity of the left port (43) at the same time, and the volume increases again, and the gas will expand again, further enhancing the gas mixing effect. After multiple recirculation vortices and multiple compressions and expansions, the gas mixing is enhanced, the combustion efficiency is further improved, and the uniformity of the outlet gas temperature is ensured;

[0013] The advantages of the present invention compared with the prior art are: the present invention applies a gas generator with a three-shot injection hole, an eccentric spoiler ring and a spherical-conical combustion chamber to the field of liquid rocket engines, and changes a roughly positioned welded nozzle into a 3D-printed injection hole form. The process is simple and the manufacturing is precise, and the fuel and oxidant can be efficiently atomized, mixed and burned, thereby improving the combustion efficiency; at the same time, the fuel sprayed into the fuel cooling hole evaporates at high temperature to form a side cooling layer, which not only reduces the wall temperature, but also enhances the mixing effect, thereby avoiding local high temperature in the gas generator; the spoiler ring with an eccentric structure greatly enhances the disturbance effect of the fuel gas, and guides the fuel gas into the special-shaped spherical-conical combustion chamber, and after multiple recirculation vortices and multiple compressions and expansions, the fuel gas mixing is enhanced, the combustion efficiency is further improved, and the uniformity of the outlet gas temperature is ensured. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a front cross-sectional view of the gas generator structure of the present invention;

[0015] Figure 2 A three-dimensional cross-sectional view of an injector of the gas generator of the present invention;

[0016] Figure 3 A bottom-view cross-sectional view of an injector flow channel hole of the gas generator of the present invention;

[0017] Figure 4 A bottom view of a three-strike injection hole group of an injector of the gas generator of the present invention;

[0018] Figure 5 A bottom view of a partial view of a three-strike injection hole group of an injector of the gas generator of the present invention;

[0019] Figure 6 It is a partial cross-sectional view of a three-strike injection hole group of an injector of the gas generator of the present invention;

[0020] Figure 7 A bottom view of the fuel cooling hole of the injector of the gas generator of the present invention;

[0021] Figure 8 A bottom view of the injector of the gas generator of the present invention;

[0022] Fig. 9 It is a front cross-sectional view of an eccentric spoiler ring of the gas generator of the present invention;

[0023] Fig.10 It is a front cross-sectional view of a spherical-conical combustion chamber of the gas generator of the present invention;

[0024] Fig.11 It is a front cross-sectional view of a three-way elbow of the gas generator of the present invention;

[0025] Fig.12 It is a left side view of the three-way elbow of the gas generator described in the present invention. DETAILED DESCRIPTION

[0026] The specific implementation of the present invention is described below in conjunction with the accompanying drawings;

[0027] The gas generator described in the present invention is applied to the power supply system of a liquid rocket engine. In actual use, the fuel agent nozzle (12) of the gas generator injector (1) is connected to the fuel agent storage tank through a pipeline, and the oxidant nozzle (11) is connected to the oxidant storage tank through a pipeline, so as to provide the gas generator with fuel and oxidant; the right port (42) of the three-way elbow (4) of the gas generator is fixedly connected to the inlet of the liquid rocket engine power supply system by welding, and the left port (43) is connected to other devices by bolts and is usually used in a closed state. The fuel agent and the oxidant are sprayed into the inner cavity of the cylindrical ring (21) of the eccentric spoiler ring (2) through the injector (1) to collide, atomize and burn, and after combustion, combustion gas is generated. The combustion gas is introduced into the spherical cone combustion chamber (3) for further mixing and combustion, and then passes through the middle inlet (41) and the inner cavity of the right port (42) of the three-way elbow (4), and finally discharged into the power supply system of the liquid rocket engine to provide power for the entire rocket;

[0028] like Figure 1As shown, the gas generator of the present invention comprises an injector (1), an eccentric spoiler ring (2), a spherical cone combustion chamber (3) and a three-way elbow (4), wherein the injector (1) is in the shape of a round pancake, a lower boss (13) is provided at the bottom thereof, and the whole is printed by a 3D printer; the upper half of the eccentric spoiler ring (2) is a cylindrical ring (21), the top surface of the cylindrical ring (21) is fixedly connected to the bottom edge of the lower boss (13) of the injector (1) by welding, and the lower half of the eccentric spoiler ring (2) is an open eccentric conical ring (22), and the open conical ring (22) is formed inside the conical ring (22). The oral cavity (23) faces the spherical surface of the spheroconical combustion chamber (3); the spheroconical combustion chamber (3) is a hollow shell composed of a sphere and a cone, wherein the spherical surface is tangent to the side surface of the bottom of the cone; the spheroconical combustion chamber (3) comprises a spherical cavity (32) and a conical cavity (33), wherein a side hole (31) is formed on the side of the spherical cavity (32), and the hole wall of the side hole (31) is fixedly connected to the side bottom edge of the cylindrical ring (21) by welding; an outlet (34) is formed on the top of the conical cavity (33), and the outlet (34) is fixedly connected to the middle inlet (41) of the three-way elbow (4) by welding. The three-way elbow (4) is in a side T-shape as a whole. The left side of the three-way elbow (4) is a left port (43) which adopts a flange structure connection form. The right side of the three-way elbow (4) is a right port (42) which is used to be fixedly connected to the inlet of the liquid rocket engine power supply system by welding. The middle part of the three-way elbow (4) is a middle inlet (41) which adopts a boss positioning form and is fixedly connected to the outlet (34) of the spherical cone combustion chamber (3) by welding.

[0029] like Figure 2 The figure shows a front cross-sectional view of an injector (1). The injector (1) is entirely printed using a 3D printer. A conical oxidant nozzle (11) is provided at the top of the injector (1), and a nozzle cavity (111) is provided inside the nozzle (11); an oxidant cavity (112) is provided in the middle of the injector (1), and the nozzle cavity (111) is communicated with the oxidant cavity (112); a cylindrical fuel nozzle (12) is provided on the side of the injector (1), and a nozzle cavity (121) is provided inside the nozzle (12); an annular fuel cavity (122) is provided around the circumference of the injector (1), and the nozzle cavity (121) is connected to the annular fuel cavity (122). 122); a lower boss (13) is provided at the bottom of the injector (1), and a regularly arranged flow channel hole (14), a three-shot injection hole group (15) and a fuel agent cooling hole (16) are provided in the lower boss (13); the flow channel hole (14) is in communication with the fuel agent cavity (122); the three-shot injection hole group (15) includes two fuel agent holes (151) and one oxidant hole (152), wherein the fuel agent hole (151) is in communication with the flow channel hole (14), and the oxidant hole (152) is in communication with the oxidant cavity (112); the fuel agent cooling hole (16) is in communication with the fuel agent cavity (122);

[0030] like Figure 3As shown, it is a cross-sectional view of the flow channel holes (14) of the injector (1) from above, wherein the flow channel holes (14) are uniformly distributed along the annular fuel agent cavity (122), and the flow channel holes (14) are divided into three groups, wherein the length of the flow channel holes (14) of the first group is 5 mm to 55 mm smaller than the radius of the lower boss (13); the length of the flow channel holes (14) of the second group is 20 mm to 70 mm smaller than the radius of the lower boss (13); the length of the flow channel holes (14) of the third group is 40 mm to 90 mm smaller than the radius of the lower boss (13); the flow channel holes uniformly distributed in an interval form in the first group of flow channel holes (14) are interconnected in the radial direction;

[0031] In this embodiment, the flow channel holes (14) are arranged in three groups, totaling 32 in number. The flow channel holes (14) between groups are staggered and evenly distributed along the circumference. The radius of the lower boss (13) of the injector (1) is 120 mm. The first group of flow channel holes (14) is evenly distributed with 8 holes along the circumference. The length of each flow channel hole (14) is 5 mm to 55 mm smaller than the radius of the lower boss (13), and is designed to be 90 mm. The aperture of each flow channel hole (14) is 9 mm. The first group of 8 flow channel holes (14) are designed along 0°, 45°, 90°, 135°, 180°, 225°, 270°, and 315°, respectively. The four flow channel holes (14) along 45°, 135°, 225°, and 315° are connected to each other, and the diameter of the connected holes is 5 mm. The second group of flow channel holes (14) has eight evenly distributed along the circumference, the length of each flow channel hole (14) is 20 mm to 70 mm smaller than the radius of the lower boss (13), and is designed to be 70 mm, and the aperture of each flow channel hole (14) is 9 mm; the second group of eight flow channel holes (14) are designed at angles of 22.5°, 67.5°, 112.5°, 157.5°, 202.5°, 247.5°, 292.5°, and 337.5°, respectively. The third group of flow channel holes (14) is evenly distributed along the circumference of 16 holes, the length of each flow channel hole (14) is 40 mm to 90 mm smaller than the radius of the lower boss (13), and is designed to be 40 mm, and the aperture of each flow channel hole (14) is 8 mm; the third group of 16 flow channel holes (14) are respectively designed along 11.25°, 33.75°, 56.25°, 78.75°, 101.25°, 123.75°, 146.25°, 168.75°, 191.25°, 213.75°, 236.25°, 258.75°, 281.25°, 303.75°, 326.25°, and 348.75°;

[0032] like Figure 4As shown, it is a bottom view of the three-strike injection hole group (15) of the injector (1), wherein the bottom of the injector (1) is provided with 6 circles of three-strike injection hole groups (15) evenly distributed along the circumference, and the number of three-strike injection hole groups (15) included in each circle is 4, 8, 16, 16, 32, and 32 from the inside to the outside respectively; in order to ensure that the three-strike injection hole groups (15) are distributed relatively evenly on the bottom surface of the injector (1), the adjacent hole groups on the third circle and the fifth circle are arranged in an "eight" shape;

[0033] like Figure 5 , which is a partial bottom view of a three-shot injection hole group (15) of an injector (1). As can be seen from the figure, the three-shot injection hole group (15) includes two fuel holes (151) and one oxidant hole (152), wherein one oxidant hole (152) is located between the two fuel holes (151);

[0034] like Figure 6 The figure is a partial cross-sectional view of the three-shot injection hole group (15) of the injector (1). It can be seen from the figure that the one oxidant hole (152) is located in the middle of the two fuel holes (151), and the axes of the two fuel holes (151) and the axis of the one oxidant hole (152) are at an angle of 10° to 80°, and the three axes intersect at one point. In this embodiment, the axes of the two fuel holes (151) and the axis of the one oxidant hole (152) are at an angle of 15°; the oxidant hole (152) is connected to the oxidant cavity (112), and the fuel hole (151) is connected to the flow channel hole (14);

[0035] like Figure 7 , which is a bottom view of the fuel agent cooling holes (16) of the injector (1). It can be seen from the figure that there are 64 fuel agent cooling holes (16) in total, which are evenly distributed along the circumference at the bottom edge area of ​​the lower boss (13) of the injector (1);

[0036] like Figure 8 As shown, Figure 3 , Figure 4 and Figure 7 The combined structure is a bottom view of the injector (1);

[0037] like Fig. 9 As shown, it is a three-dimensional cross-sectional view of an eccentric spoiler ring (2), wherein the upper half of the eccentric spoiler ring (2) is a cylindrical ring (21), and the lower half is an open eccentric conical ring (22), and the angle between the axis of the cylindrical ring (21) and the axis of the conical ring (22) is θ3, ranging from 110° to 160°. In the present embodiment, the angle is designed to be 130°;

[0038] like Fig.10As shown, it is a three-dimensional cross-sectional view of a spherical cone combustion chamber (3), wherein the spherical cone combustion chamber (3) is a hollow shell composed of a sphere and a cone, and a circular hole (31) is opened on the side of the conical combustion chamber (3), and the angle between the axis of the side hole (31) and the axis of the outlet (34) is θ1, ranging from 100° to 170°. In this embodiment, the angle is designed to be 120°;

[0039] like Fig.11 and Fig.12 As shown, it is a front view, a cross-sectional view and a left view of a three-way elbow (4), wherein the three-way elbow (4) is in a side T-shape as a whole, the middle part is a middle inlet (41), which is a boss positioning welding form; the right side is a right port (42), which is also a boss positioning welding form; the left side is a left port (43), which is a flange structure connection form;

[0040] When the fuel is injected into the inner cavity of the cylindrical ring (21) of the eccentric spoiler ring (2) through the fuel holes (152) of the three-strike injection hole group (15), the oxidant is injected into the inner cavity of the cylindrical ring (21) of the eccentric spoiler ring (2) through the oxidant holes (151) of the three-strike injection hole group (15); the two fuels injected into the two fuel holes (151) of the three-strike injection hole group (15) and the one oxidant injected into the one oxidant hole (152) collide with each other in the inner cavity of the cylindrical ring (21), are atomized, mixed and burned, and combustion is performed, and combustion generates combustion gas; at the same time, the fuel is injected into the inner cavity of the cylindrical ring (21) through the oxidant holes (151) of the three-strike injection hole group (15). The fuel cooling hole (16) is directly sprayed into the inner cavity of the cylindrical ring (21) of the eccentric spoiler ring (2). Since the injected fuel has a much lower temperature than the combustion environment, it evaporates in the high temperature environment of the inner cavity of the cylindrical ring (21) to form a peripheral cooling layer, which not only reduces the wall temperature but also enhances the mixing effect, thereby avoiding the occurrence of high temperature in the local area of ​​the gas generator; the fuel gas is introduced into the spherical cone combustion chamber (3) for further mixing and combustion, and then passes through the inner cavity of the middle inlet (41) and the right port (42) of the three-way elbow (4), and finally discharged into the liquid rocket engine power supply system;

[0041] Practice has proved that the combustion efficiency of the gas generator used in the present invention is improved by more than 30% compared with the combustion efficiency of the original gas generator; the uniformity of the outlet gas temperature is within the range of ±25°C, which meets the allowable range of the operating temperature difference mutation of the specific materials of the power components used in the power supply system of the liquid rocket engine, prolongs the service life, and ensures the working stability of the liquid rocket engine;

[0042] The above description is only a specific implementation mode of the present invention, but the protection of the present invention is not limited thereto. Any improvement without substantial change made by those skilled in the art without changing the principle and its application in the technical field of liquid rocket engine propellant gas generator should also be regarded as the protection scope of the present invention.

[0043] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in this field.

Claims

1. A gas generator, characterized in that: The invention comprises an injector (1), an eccentric spoiler ring (2), a spherical cone combustion chamber (3) and a three-way elbow (4), wherein the injector (1) is in a round cake shape, a lower boss (13) is provided at the bottom thereof, and the whole is printed by a 3D printer; the upper half of the eccentric spoiler ring (2) is a cylindrical ring (21), the top surface of the cylindrical ring (21) is fixedly connected to the bottom edge of the lower boss (13) of the injector (1) by welding, the lower half of the eccentric spoiler ring (2) is an open eccentric conical ring (22), and the open cavity (23) formed inside the conical ring (22) faces the spherical surface of the spherical cone combustion chamber (3); the spherical cone combustion chamber (3) is a hollow shell composed of a sphere and a cone, the spherical surface of the spherical cone is tangent to the side surface of the bottom of the cone, and the spherical cone combustion chamber (3) comprises a spherical cavity (32 ) and a conical cavity (33), wherein a side hole (31) is opened on the side of the spherical cavity (32), and the hole wall of the side hole (31) is fixedly connected to the side bottom edge of the cylindrical ring (21) by welding; an outlet (34) is opened on the top of the conical cavity (33), and the outlet (34) is fixedly connected to the middle inlet (41) of the three-way elbow (4) by welding; the three-way elbow (4) is in a side T-shape as a whole, the left side of the three-way elbow (4) is a left port (43), which adopts a flange structure connection form, and the right side of the three-way elbow (4) is a right port (42), which is used to be fixedly connected to the inlet of the liquid rocket engine power supply system by welding, and the middle part of the three-way elbow (4) is the middle inlet (41), which adopts a boss positioning form and is fixedly connected to the outlet (34) of the spherical cone combustion chamber (3) by welding.

2. The gas generator according to claim 1, characterized in that: The top of the injector (1) is provided with a conical oxidant nozzle (11), the interior of the oxidant nozzle (11) is a first nozzle cavity (111); the middle of the injector (1) is an oxidant cavity (112), the first nozzle cavity (111) is connected to the oxidant cavity (112); the side of the injector (1) is provided with a cylindrical fuel nozzle (12), the interior of the fuel nozzle (12) is a second nozzle cavity (121); the circumference of the injector (1) is provided with an annular fuel cavity (122), the second nozzle cavity (121) is connected to the annular fuel cavity (122); the injector A lower boss (13) is provided at the bottom of (1), and a regularly arranged flow channel hole (14), a three-shot injection hole group (15) and a fuel agent cooling hole (16) are provided in the lower boss (13); the flow channel hole (14) is communicated with the fuel agent cavity (122); the three-shot injection hole group (15) includes two fuel agent holes (151) and one oxidant hole (152), wherein the fuel agent hole (151) is communicated with the flow channel hole (14), and the oxidant hole (152) is communicated with the oxidant cavity (112); and the fuel agent cooling hole (16) is communicated with the fuel agent cavity (122).

3. The gas generator according to claim 2, characterized in that: The flow passage holes (14) are uniformly distributed along the annular fuel cavity (122). The flow passage holes (14) are divided into three groups. The length of the flow passage holes (14) in the first group is 5 mm to 55 mm smaller than the radius of the lower boss (13); the length of the flow passage holes (14) in the second group is 20 mm to 70 mm smaller than the radius of the lower boss (13); the length of the flow passage holes (14) in the third group is 40 mm to 90 mm smaller than the radius of the lower boss (13); the flow passage holes uniformly distributed in an interval form in the first group of flow passage holes (14) are interconnected in the radial direction.

4. The gas generator according to claim 2, characterized in that: The one oxidant hole (152) is located in the middle of the two fuel holes (151), the axes of the two fuel holes (151) are at an angle of 10° to 80° with the axis of the one oxidant hole (152), and the three axes intersect at one point.

5. The gas generator according to claim 2, characterized in that: The fuel cooling holes (16) are located in the bottom edge area of ​​the lower boss (13) and are evenly distributed along the circumference.

6. The gas generator according to claim 1, characterized in that: The angle between the axis of the cylindrical ring (21) and the axis of the conical ring (22) is 110° to 160°.

7. The gas generator according to claim 1, characterized in that: The angle between the axis of the side hole (31) and the axis of the outlet (34) is 100° to 170°.

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