Integrated injector system for liquid rocket engines

Abstract

The application provides a liquid rocket engine integrated injector system, which comprises an oxidant injection section and a fuel injection section connected through a rib plate; the oxidant injection section is provided with an oxidant inlet, an oxidant inlet liquid collecting cavity, a pre-injection flow regulating device and a support column; the fuel injection section is provided with a fuel inlet, a fuel inlet liquid collecting cavity, a fuel flow dividing hole and a fuel pre-injection liquid collecting cavity; a nozzle unit is connected with the pre-injection flow regulating device and the nozzle support column in sequence; liquid oxidant enters the nozzle unit through the oxidant inlet, the oxidant inlet liquid collecting cavity and the pre-injection flow regulating hole in sequence; liquid fuel enters the nozzle unit through the fuel inlet, the fuel inlet liquid collecting cavity and the fuel flow dividing hole in sequence, and the oxidant and the fuel are atomized and mixed in the nozzle unit and sprayed out from an outlet. The application realizes the structural integration of the injector, solves the problem of forming difficulty of the complex flow channel structure of the injector, has the advantages of high structural strength and uniform flow distribution, and is suitable for the additive manufacturing production technology.

Description

Technical Field

[0001] This invention relates to the field of rocket engines, and more specifically, to an integrated injector system for a liquid rocket engine. Background Technology

[0002] The liquid rocket engine injector is a core component of the engine and has a direct impact on its combustion performance. For injectors using a coaxial injection method, the production of injectors is generally carried out by machining and brazing. This involves multiple processes such as parts machining, press fitting, edge rolling, and welding. The process is complex, has a long production cycle, and is costly. At the same time, it also suffers from problems such as low brazing qualification rate.

[0003] The injection nozzle is manufactured using additive manufacturing technology, resulting in a one-piece molding process with low processing costs, short production cycles, and high structural strength, making it a promising technology with broad application prospects.

[0004] Meanwhile, the production of injectors using additive manufacturing technology faces challenges due to the complex flow channel structure and difficult molding process, making the adaptability of the structure a pressing problem that needs to be solved. Summary of the Invention

[0005] In view of the deficiencies in the prior art, the purpose of this invention is to provide an integrated injector system for liquid rocket engines.

[0006] According to the present invention, an integrated injector system for a liquid rocket engine includes an integrally formed oxidizer injection section 1, a fuel injection section 2, and a nozzle unit 15, wherein the oxidizer injection section 1 and the fuel injection section 2 are connected by a rib plate 3.

[0007] The oxidant injection section 1 includes an oxidant inlet 11, an oxidant inlet collection chamber 12, and a pre-spray rectifier 13; wherein the oxidant inlet 11 is connected to the oxidant inlet collection chamber 12, and the pre-spray rectifier 13 is installed in the oxidant inlet collection chamber 12.

[0008] The fuel injection section 2 includes a fuel inlet 21, a fuel inlet collecting chamber 22, a fuel diversion orifice 23, and a fuel pre-injection collecting chamber 24; wherein the fuel inlet 21 is connected to the fuel inlet collecting chamber 22, and the fuel inlet collecting chamber 22 is connected to the fuel pre-injection collecting chamber 24 through the fuel diversion orifice 23.

[0009] The liquid oxidant enters the nozzle unit 15 sequentially through the oxidant inlet 11, the oxidant inlet collection chamber 12, and the pre-spray rectifier 13;

[0010] Liquid fuel enters the nozzle unit 15 sequentially through fuel inlet 21, fuel inlet collection chamber 22, fuel diversion hole 23, and fuel pre-injection collection chamber 24;

[0011] The liquid oxidant and liquid fuel are atomized and mixed within the nozzle unit 15 and then ejected from the outlet.

[0012] Preferably, the oxidant inlet collection chamber 12 further includes a support column 14, which includes a nozzle support column 141 and an inter-nozzle support column 142. The nozzle support column 141 supports the nozzle unit 15, and the inter-nozzle support column 142 supports the rib plate 3.

[0013] Preferably, the nozzle unit 15, the pre-spray rectifier 13, and the nozzle support column 141 are connected in sequence.

[0014] Preferably, the pre-spray rectifier 13 is disposed on the upper side of the nozzle unit 15, and the pre-spray rectifier 13 and the nozzle unit 15 are internally connected.

[0015] Preferably, the pre-spray rectifier 13 is provided with a connecting hole in the circumference, and the connecting hole connects the inner cavity of the pre-spray rectifier 13 and the oxidant inlet collection cavity 12.

[0016] Preferably, the fuel diversion holes 23 are evenly distributed around the periphery of the fuel injection pre-collection chamber 24.

[0017] Preferably, the fuel diversion hole 23 is a teardrop-shaped structure hole.

[0018] Preferably, the pre-spray rectifier 13 is a trapezoidal rectifier structure with multiple holes in the circumference. The bottom of the pre-spray rectifier 13 is connected to the top of the nozzle unit 15, and the top of the pre-spray rectifier 13 is supported by the nozzle support column 141.

[0019] Preferably, the nozzle unit 15 is provided with a fuel pipe for supplying liquid fuel at the top, and the fuel pipe extends to the bottom of the nozzle unit 15.

[0020] Preferably, an intermediate cavity is provided between the fuel pipe and the outer wall of the nozzle unit 15, and a connecting hole is provided on the periphery of the nozzle unit 15, the connecting hole connecting the fuel pre-injection liquid collection chamber 24 and the intermediate cavity.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. The injector structure designed in this invention is an integrated structure with advantages such as high structural strength, and is suitable for production using additive manufacturing technology.

[0023] 2. The present invention makes the flow more uniform by setting up a pre-spray rectification device structure.

[0024] 3. This invention solves the problem of difficult molding of complex injector structures by adopting a support column and a teardrop-shaped flow channel hole structure. Attached Figure Description

[0025] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0026] Figure 1 This is a cross-sectional structural schematic diagram of an integrated liquid rocket engine injector according to the present invention;

[0027] Figure 2 This is a schematic cross-sectional view of the pre-spray rectifier device of the present invention;

[0028] Figure 3 This is the nozzle inter-support column structure of the present invention;

[0029] Figure 4 This is the nozzle unit structure of the present invention;

[0030] Figure 5 This is a schematic diagram of the teardrop-shaped structure hole of the present invention. Detailed Implementation

[0031] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0032] like Figures 1 to 5 As shown, an integrated liquid rocket engine injector system according to the present invention includes an oxidizer injection section 1 and a fuel injection section 2, wherein the oxidizer injection section 1 and the fuel injection section 2 are connected by a rib plate 3; the oxidizer injection section 1 is provided with an oxidizer inlet 11, an oxidizer inlet collecting chamber 12, a pre-injection rectifier 13 and a support column 14, the support column 14 being composed of a nozzle support column 141 and an inter-nozzle support column 142; the oxidizer inlet 11 is sequentially connected to the oxidizer inlet collecting chamber 12, the pre-injection rectifier 13 and the nozzle unit 15. The fuel injection section 2 is equipped with a fuel inlet 21, a fuel inlet collection chamber 22, a fuel diversion hole 23, and a fuel pre-injection collection chamber 24. The nozzle unit 15 is connected in sequence to the pre-injection rectifier 13 and the nozzle support column 141 to achieve effective support for the nozzle unit. The fuel inlet 21 is connected in sequence to the fuel inlet collection chamber 22, the fuel diversion hole 23, the fuel pre-injection collection chamber 24, and the nozzle unit 15. The liquid oxidant enters the nozzle unit 15 in sequence through the oxidant inlet 11, the oxidant inlet collection chamber 12, and the pre-injection rectifier 13. The liquid fuel enters the nozzle unit 15 in sequence through the fuel inlet 21, the fuel inlet collection chamber 22, and the fuel diversion hole 23. The oxidant and fuel are atomized and mixed in the nozzle unit 15 and sprayed out from the outlet.

[0033] like Figure 2 As shown, the pre-spray rectifier 13 is a trapezoidal rectifier structure with multiple circumferential holes, distributed at the upper end of each nozzle unit 15, to rectify the oxidant before it enters the nozzle. Furthermore, the side of the pre-spray rectifier 13 has multiple connecting holes evenly spaced along the circumferential direction. These connecting holes connect the oxidant inlet collection chamber 12 and the internal cavity of the pre-spray rectifier 13, and the internal cavity of the pre-spray rectifier 13 is connected to the upper end of the nozzle unit 15.

[0034] The nozzle unit 15 includes two inlets. The first inlet is a fuel pipe located at the center of the top of the nozzle unit 15, extending to the bottom of the nozzle unit 15, with a slight gap between the fuel pipe and the bottom of the nozzle unit 15. An intermediate cavity is provided between the outer wall of the fuel pipe and the inner wall of the nozzle unit 15. A connecting hole is provided on the periphery of the outer wall of the nozzle unit 15, connecting the fuel pre-injection liquid collection chamber 24 and the intermediate cavity. Liquid fuel enters the fuel pipe from the center of the top of the nozzle unit 15 and then flows into the bottom of the nozzle unit 15, while liquid oxidant enters the intermediate cavity from the connecting hole on the periphery of the outer wall of the nozzle unit 15 and then flows into the bottom of the nozzle unit 15, where the two converge.

[0035] like Figure 3 As shown, the fuel diversion orifice 23 has a teardrop-shaped structure and is evenly distributed downstream of the fuel inlet collection chamber 22 to achieve rectification and distribution of fuel before it enters the nozzle.

[0036] The nozzle support column 141 and the nozzle inter-support column 142 effectively support the nozzle unit 15 and the rib plate 3, preventing molding problems such as collapse during the manufacturing process.

[0037] This invention discloses an integrated injector system for a liquid rocket engine, suitable for production using additive manufacturing technology, and possesses advantages such as integrated production and high structural strength. This invention achieves integrated injector structure, solving the problem of difficult molding of complex flow channel structures in injectors, and has the advantages of high structural strength and uniform flow distribution, making it suitable for additive manufacturing production technology.

[0038] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0039] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. An integrated injector system for a liquid rocket engine, characterized in that, It includes an integrally formed oxidizer injection section (1), fuel injection section (2), and nozzle unit (15), wherein: the oxidizer injection section (1) and the fuel injection section (2) are connected by a rib plate (3); The oxidant injection section (1) includes an oxidant inlet (11), an oxidant inlet collection chamber (12), and a pre-spray rectifier (13); wherein the oxidant inlet (11) is connected to the oxidant inlet collection chamber (12), and the pre-spray rectifier (13) is installed inside the oxidant inlet collection chamber (12); The fuel injection section (2) includes a fuel inlet (21), a fuel inlet collection chamber (22), a fuel diversion hole (23), and a fuel injection pre-collection chamber (24); wherein the fuel inlet (21) is connected to the fuel inlet collection chamber (22), and the fuel inlet collection chamber (22) is connected to the fuel injection pre-collection chamber (24) through the fuel diversion hole (23); The liquid oxidant enters the nozzle unit (15) sequentially through the oxidant inlet (11), the oxidant inlet collection chamber (12), and the pre-spray rectifier (13); Liquid fuel enters the nozzle unit (15) sequentially through the fuel inlet (21), the fuel inlet collection chamber (22), the fuel diversion hole (23), and the fuel pre-injection collection chamber (24); The liquid oxidant and liquid fuel are atomized and mixed in the nozzle unit (15) and sprayed out from the outlet; The oxidant inlet collection chamber (12) also includes a support column (14), which includes a nozzle support column (141) and an inter-nozzle support column (142). The nozzle support column (141) supports the nozzle unit (15), and the inter-nozzle support column (142) is used to support the rib plate (3). The fuel diversion hole (23) is a teardrop-shaped structure hole.

2. The integrated liquid rocket engine injector system according to claim 1, characterized in that, The nozzle unit (15), the pre-spray rectifier (13), and the nozzle support column (141) are connected in sequence.

3. The integrated liquid rocket engine injector system according to claim 1, characterized in that, The pre-spray rectifier (13) is located on the upper side of the nozzle unit (15), and the pre-spray rectifier (13) and the nozzle unit (15) are internally connected.

4. The integrated liquid rocket engine injector system according to claim 3, characterized in that, The pre-spray rectifier (13) is provided with a connecting hole in the circumference, which connects the inner cavity of the pre-spray rectifier (13) and the oxidant inlet collection cavity (12).

5. The integrated liquid rocket engine injector system according to claim 1, characterized in that, The fuel diversion holes (23) are evenly distributed around the fuel injection pre-collection chamber (24).

6. The integrated liquid rocket engine injector system according to claim 1, characterized in that, The pre-spray rectifier (13) is a trapezoidal rectifier structure with multiple holes in the circumference. The bottom of the pre-spray rectifier (13) is connected to the top of the nozzle unit (15), and the top of the pre-spray rectifier (13) is supported by the nozzle support column (141).

7. The integrated liquid rocket engine injector system according to claim 1, characterized in that, The nozzle unit (15) is provided with a fuel pipe at the top for liquid fuel to enter, and the fuel pipe extends to the bottom of the nozzle unit (15).

8. The integrated liquid rocket engine injector system according to claim 7, characterized in that, An intermediate cavity is provided between the fuel pipeline and the outer wall of the nozzle unit (15). A connecting hole is provided on the periphery of the nozzle unit (15), and the connecting hole connects the fuel injection pre-collection chamber (24) and the intermediate cavity.

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