A thrust chamber impact injector

Abstract

The present invention discloses a thrust chamber impact injector. It comprises an injector body, wherein a first oxidant flow channel, a component flow channel distribution layer and a component cavity distribution layer are sequentially arranged in the axial direction in the injector body; the component flow channel distribution layer is provided with a plurality of fuel flow channels and a plurality of second oxidant flow channels, and the fuel flow channels and the second oxidant flow channels are spaced apart; the component cavity distribution layer is provided with a plurality of oxidant cavities and a plurality of fuel cavities, and the oxidant cavities and the fuel cavities are spaced apart; in order to prevent the oxidant and fuel from entering the cavity, the fuel and oxidant flow channels and the distribution cavity are all designed as partitions; after the oxidant and fuel enter from the oxidant inlet and the fuel inlet respectively, the oxidant flows into the oxidant cavity along the axial flow channel; the fuel flows into the fuel cavity through a plurality of flow channels uniformly distributed in the radial direction, and is finally ejected through the corresponding oxidant outlet and fuel outlet. The injector of the present invention can adopt a split structure, the injector body is made of stainless steel, and the baffle at the outlet is made of copper alloy material, so as to improve the service life of the injector.

Description

Technical Field

[0001] The present invention relates to an injector technology, in particular to a thrust chamber impact injector. Background Art

[0002] As a key component of the thrust chamber, the injector is used to inject, atomize and mix the propellant components, which determines the completeness of the propellant's combustion, combustion stability, working reliability and reusability.

[0003] The thrust chamber working environment of large thrust open cycle liquid oxygen kerosene engine has high temperature (~3600K), high chamber pressure (>8MPa), high heat flux density (~60MW / m 2 ) is a notable feature. High-thrust open-cycle liquid oxygen-kerosene engines often use impingement or centrifugal injectors in their thrust chambers. For example, the RD-107 series engine thrust chambers employ coaxial centrifugal injectors, with hundreds of nozzles brazed to the injectors. The F-1 and H-1 engines use impingement injectors, which have a relatively simple structure and mature processing technology. However, controlling flow field uniformity during new product development can be difficult, resulting in suboptimal combustion efficiency. Summary of the Invention

[0004] In view of the defects or shortcomings of the prior art, the present invention provides a thrust chamber impact injector.

[0005] To this end, the thrust chamber impact injector provided by the present invention includes an injector body, which is a disc-shaped structure. A first oxidant flow channel, a first partition, a component flow channel distribution layer, a second partition, a component cavity distribution layer and a third partition are sequentially arranged in the injector body along the axial direction;

[0006] The outward end of the first oxidant flow channel is an oxidant inlet;

[0007] The component flow channel distribution layer is provided with a plurality of fuel flow channels and a plurality of second oxidant flow channels, wherein the fuel flow channels are arranged along the radial direction of the injector, the outward end of the fuel flow channel is a fuel inlet, and the fuel flow channel is separated from the second oxidant flow channel, and the fuel flow channel and the second oxidant flow channel are distributed at intervals;

[0008] The component cavity distribution layer is distributed with a plurality of oxidant cavities and a plurality of fuel cavities, and the oxidant cavities and the fuel cavities are separated and distributed at intervals;

[0009] The first separator is provided with a plurality of first oxidant flow ports, and the first oxidant flow channel is connected to each second oxidant flow channel through the corresponding first oxidant flow port;

[0010] The second partition plate is provided with a plurality of second oxidant flow ports, and each second oxidant flow channel is connected to one or more oxidant chambers through the corresponding second oxidant flow port;

[0011] The second separator is provided with a plurality of fuel flow ports, and each fuel flow channel is connected to one or more fuel chambers through a corresponding fuel flow port;

[0012] The third partition is provided with a plurality of oxidant outlet holes and a plurality of fuel outlet holes, and the oxidant outlet holes and the fuel outlet holes are distributed at intervals, and at the same time, the oxidants sprayed from adjacent oxidant outlet holes collide, the fuels sprayed from adjacent fuel outlet holes can collide, or the oxidants and fuels sprayed from adjacent oxidant outlet holes and fuel outlet holes collide; the oxidant outlet holes are communicated with the oxidant cavity, and the fuel outlet holes are communicated with the fuel cavity.

[0013] Alternatively, the plurality of fuel flow channels are evenly distributed along the circumference of the injector, and the space between the first and second separators is divided into a plurality of second oxidant flow channels; the plurality of fuel flow channels and the plurality of oxidant flow channels are spaced apart and distributed along the circumference of the injector body. Alternatively, the cross-sections of the oxidant flow port and the second oxidant flow channels are both sector-shaped.

[0014] An optional solution is that the oxidant chamber and the fuel chamber are both annular chamber structures surrounding the axial direction of the injector, and the oxidant chamber and the fuel chamber are distributed at intervals along the radial direction of the injector.

[0015] An optional solution is that the third partition plate is provided with multiple circles of oxidant outlets and multiple circles of fuel outlets distributed axially around the injector, each circle of oxidant outlets is provided with several oxidant outlets, and each circle of fuel outlets is provided with several fuel outlets; along the radial direction of the injector, a single circle of oxidant outlets is distributed alternately with a single circle of fuel outlets, or more than two circles of oxidant outlets are distributed alternately with more than two circles of fuel outlets.

[0016] An optional solution is that the third partition is an independent component.

[0017] An optional solution is that the third partition is assembled from multiple injector rings with ring structures, and each injector ring corresponds one-to-one to each oxidant cavity and fuel cavity of the component cavity distribution layer; each injector ring is provided with multiple component outlets.

[0018] An optional solution is that each injector ring is provided with at least one circle of component outlets.

[0019] An optional solution is that the material of the third partition is copper alloy; the material of the injector body is stainless steel.

[0020] An optional solution is that the component outlets located on the same circle are distributed in pairs, with each pair having two component outlets, and the two component outlets in the same pair are opened axially intersecting so that the components ejected from the two component outlets can collide.

[0021] An optional solution is that the aperture sizes of the outlets of the components in the same circle are the same; and the aperture sizes of the outlets of the components in adjacent circles are different.

[0022] Alternatively, the distance between the impact site and the injector surface is 6 to 30 mm.

[0023] Alternatively, the distance between the impact site of the fuel component and the injector surface is different from the distance between the impact site of the oxidizer component and the injector surface.

[0024] The injector of the present invention has a uniform flow field distribution and controllable combustion efficiency. Furthermore, the injector body can be made of low-cost stainless steel, while the injector ring is made of copper alloy. By rationally designing the injector disc and injector ring structure, the problem of reliable connection between dissimilar materials is solved.

[0025] In a preferred embodiment, the present invention employs large-size injector rings, oxidizer rings, and fuel rings arranged in alternating patterns, with the impactor pairs arranged on each ring having different apertures. The alternating arrangement of the large and small-aperture injector rings ensures that the combustion locations of the liquid oxygen and kerosene propellants in different areas of the injector face are not aligned, achieving stable combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a structural diagram of an injector according to an embodiment of the present invention;

[0027] Figure 2 for Figure 1 CC cross-sectional view;

[0028] Figure 3 1. It is a diagram showing the structure of the injector ring in an embodiment of the present invention;

[0029] Figure 4 Schematic diagram of the self-strike collision principle in an embodiment of the present invention. DETAILED DESCRIPTION

[0030] Unless otherwise specified, the scientific and technical terms used herein are understood according to the knowledge of ordinary technicians in the relevant fields.

[0031] The axial, radial, circumferential and other directional or orientation terms described herein are consistent with the corresponding directions or orientations in the drawings of the specification. It should be noted that the specific directions or orientations in the drawings are intended to explain the present invention, and equivalent rotations or substitutions made by those skilled in the art based on the disclosure herein are within the scope of protection of the present invention.

[0032] See also Figure 1 and 2 As shown, the injector of the present invention includes an injector body 1, which is a disc-shaped structure. A first oxidant flow channel 7, a first separator 11, a component flow channel distribution layer, a second separator, a component cavity distribution layer and a third separator 2 are provided in the injector body along the axial direction of the injector.

[0033] The external end of the first oxidant flow channel is the oxidant inlet;

[0034] The component flow channel distribution layer is provided with a plurality of second oxidant flow channels and a plurality of fuel flow channels, each fuel flow channel is arranged along the radial direction of the injector, the outward end of the fuel flow channel is a fuel inlet, and the fuel flow channel is separated from the second oxidant flow channel, and the fuel flow channel and the second oxidant flow channel are spaced and distributed between the first separator and the second separator;

[0035] The component distribution chamber is provided with a plurality of oxidant chambers 6 and a plurality of fuel chambers 5, and the oxidant chambers and the fuel chambers are separated and distributed at intervals;

[0036] The first separator is provided with a plurality of first oxidant flow openings communicating with the first oxidant flow channel and each of the second oxidant flow channels, wherein the distribution of the plurality of first oxidant flow openings on the first separator depends on the distribution positions of the plurality of second oxidant flow channels, such that the first oxidant flow channel communicates with each of the second oxidant flow channels through the corresponding first oxidant flow openings;

[0037] The second partition plate has a plurality of second oxidant flow openings connected to the second oxidant flow channels and the oxidant chambers. The distribution of the plurality of second oxidant flow openings on the second partition plate depends on the distribution positions of the plurality of second oxidant flow channels and the distribution positions of the plurality of oxidant chambers, such that each second oxidant flow channel communicates with one or more oxidant chambers through the corresponding second oxidant flow openings.

[0038] At the same time, a plurality of second oxidant flow ports are distributed on the second separator, connecting the fuel flow channels and the fuel cavities. The distribution of the plurality of fuel flow ports on the second separator depends on the distribution positions of the plurality of fuel flow channels and the distribution positions of the plurality of fuel cavities, so that each fuel flow channel communicates with one or more fuel cavities through the corresponding fuel flow ports.

[0039] There are multiple oxidizer outlet holes and multiple fuel outlet holes distributed on the third partition plate. The distribution of the multiple oxidizer outlet holes and the multiple fuel outlet holes on the third partition plate needs to take into account the distribution of the multiple oxidizer cavities and the multiple fuel cavities, and the oxidizer outlet holes and the fuel outlet holes are distributed at regular intervals, so that each oxidizer outlet hole is connected to the corresponding oxidizer cavity, and each fuel outlet hole is connected to the corresponding fuel cavity; at the same time, the oxidizers sprayed from adjacent oxidizer outlet holes collide (self-strike), the fuels sprayed from adjacent fuel outlet holes can collide (self-strike), or the oxidizers and fuels sprayed from adjacent oxidizer outlet holes and fuel outlet holes collide (mutually strike). Specifically, the component collision of the nozzle can be achieved by designing the axial inclination angle of each adjacent outlet hole.

[0040] In order to prevent the oxidizer and fuel from entering the cavity, the fuel and oxidizer flow channels and distribution cavity are designed with compartments; after the oxidizer and fuel enter from the oxidizer inlet and fuel inlet respectively, the oxidizer flows into the oxidizer cavity 6 along the axial flow channel; the fuel flows into the fuel cavity 5 through several flow channels evenly distributed along the radial direction. The fuel and oxidizer flow through their respective flow channels and finally enter the thrust chamber through the component impact pair on the third partition.

[0041] In a specific solution, the structural distribution mode of the component flow channel distribution layer, the component cavity distribution layer and the interior or on the third partition can be designed based on the principle of easy processing and uniform distribution of components. Figure 1 and 2 As shown, multiple fuel flow channels 4 within the component flow channel distribution layer are evenly distributed along the circumference of the injector, dividing the space between the first and second separators into multiple second oxidant flow channels 3. The multiple fuel flow channels and multiple oxidant flow channels are spaced apart and distributed along the circumference of the injector body. Furthermore, preferably, the cross-sections of the oxidant flow port and the second oxidant flow channels are both fan-shaped.

[0042] The oxidant cavity and the fuel cavity of the component cavity distribution layer are both annular cavity structures surrounding the axial direction of the injector, and the oxidant cavity and the fuel cavity are distributed at intervals along the radial direction of the injector.

[0043] There are multiple circles of oxidant outlets and multiple circles of fuel outlets distributed axially around the injector on the third partition, each circle of oxidant outlets is distributed with several oxidant outlets, and each circle of fuel outlets is distributed with several fuel outlets; along the radial direction of the injector, a single circle of oxidant outlets is distributed alternately with a single circle of fuel outlets, or more than two circles of oxidant outlets are distributed alternately with more than two circles of fuel outlets.

[0044] In some embodiments, the injector of the present invention adopts a split structure, with the third baffle 2 being a separate component from the injector body 1. This allows the third baffle to be made of high-temperature resistant materials, while the injector body can be made of low-cost materials. Specifically, the third baffle is made of a copper alloy, while the injector body is made of stainless steel. Copper alloy has a thermal conductivity over 10 times that of stainless steel, ensuring reliable thermal protection of the injector surface. In this embodiment, the two materials can be joined using electron beam welding or brazing.

[0045] In a further preferred embodiment, Figure 3 As shown, the third partition is assembled from a plurality of injector rings, each of which is provided with a component outlet (i.e., an oxidant outlet and a fuel outlet); specifically, it is assembled from a plurality of oxidizer rings 21 and a plurality of fuel rings 22, and the oxidizer rings 21 and the fuel rings 22 are distributed and assembled into the third partition in a one-to-one correspondence with the oxidizer cavity and the fuel cavity. According to the diameter of the injector, a multi-ring combination is adopted. In the specific scheme, the width L of each ring varies from 10 to 50 mm, and an equal width and evenly divided design structure can also be adopted. In the preferred scheme, each injector ring is provided with one or more circles of component outlets, Figure 3 Two circles are shown.

[0046] To achieve high combustion efficiency and good combustion stability in high-thrust engines (injector diameter ≥ 400 mm), the preferred embodiment of the present invention utilizes self-impacting to achieve fine atomization particle size. In this preferred embodiment, component outlets (oxidizer or fuel outlets) located on the same circle are arranged in pairs, with each pair having two component outlets. The two component outlets within a pair are axially intersecting, allowing components ejected from the two outlets to collide. Figure 3 The oxidizer ring 21 and the fuel ring 22 are each provided with two rows of impactors, distributed on concentric circles of different diameters. In a more preferred embodiment, the apertures of the component outlets within a circle are the same; the apertures of the component outlets of adjacent circles are different.

[0047] In some other solutions, combined Figure 4 As shown, combustion efficiency can be improved by designing the aperture ΦA of the component outlet and the impact height H between components (i.e., the distance between the impact site and the injector surface). Specifically, the aperture of each ring or ring of impact pairs varies, and the impact height is selected based on a balance of thermal protection and combustion efficiency, typically ranging from 6 to 30 mm. Furthermore, different impact heights can be selected for different components (oxidizer or fuel). For example, for liquid oxygen-kerosene engine injectors, the kerosene impact height is lower than the liquid oxygen impact height to better protect the injector surface.

[0048] Based on the disclosure of this article, those skilled in the art can make equivalent substitutions or combinations of the above features to obtain other specific examples of the present invention, all of which fall within the protection scope of the present invention.

Claims

1. A thrust chamber impact injector, characterized in that: The invention comprises an injector body (1), which is a disc-shaped structure and has a diameter greater than or equal to φ400 mm; A first oxidant flow channel (7), a first partition, a component flow channel distribution layer, a second partition, a component cavity distribution layer and a third partition (2) are sequentially arranged in the injector body along the axial direction; The outward end of the first oxidant flow channel is an oxidant inlet; The component flow channel distribution layer is provided with a plurality of fuel flow channels (4) and a plurality of second oxidant flow channels (3), wherein the fuel flow channels are arranged along the radial direction of the injector, the outward end of the fuel flow channel is a fuel inlet, and the fuel flow channel is separated from the second oxidant flow channel, and the fuel flow channel and the second oxidant flow channel are distributed at intervals; The component cavity distribution layer is distributed with a plurality of oxidant cavities (6) and a plurality of fuel cavities (5), and the oxidant cavities and the fuel cavities are separated and distributed at intervals; The first partition plate (11) is provided with a plurality of first oxidant flow ports (8), and the first oxidant flow channel is connected to each second oxidant flow channel through the corresponding first oxidant flow port; The second partition plate is provided with a plurality of second oxidant flow ports (9), and each second oxidant flow channel is communicated with one or more oxidant chambers through the corresponding second oxidant flow port; The second partition plate is provided with a plurality of fuel flow ports, and each fuel flow channel is communicated with one or more fuel chambers through a corresponding fuel flow port (10); The third partition is provided with a plurality of oxidant outlet holes and a plurality of fuel outlet holes, and the oxidant outlet holes and the fuel outlet holes are spaced apart, and at the same time, the oxidants sprayed from adjacent oxidant outlet holes collide, the fuels sprayed from adjacent fuel outlet holes can collide, or the oxidants and fuels sprayed from adjacent oxidant outlet holes and fuel outlet holes collide; the oxidant outlet holes are communicated with the oxidant cavity, and the fuel outlet holes are communicated with the fuel cavity; the plurality of fuel flow channels (4) are evenly distributed along the circumference of the injector, and the space between the first partition and the second partition is divided into a plurality of second oxidant flow channels (3); the plurality of fuel flow channels and the plurality of oxidant flow channels are spaced apart along the circumference of the injector body (1); the cross sections of the oxidant flow port and the second oxidant flow channel are both fan-shaped; the oxidant cavity and the fuel cavity are both around the injector axis The third baffle is an independent component; the third baffle is assembled from multiple injector rings with an annular structure, and each injector ring corresponds to each oxidant cavity and fuel cavity of the component cavity distribution layer one by one; each injector ring is provided with multiple component outlets; each injector ring is provided with at least one circle of component outlets; the material of the third baffle is copper alloy; the material of the injector body is stainless steel.

2. The thrust chamber impact injector according to claim 1, characterized in that: The component outlets located on the same circle are distributed in pairs, each pair has two component outlets, and the openings of the two component outlets in the same pair intersect axially, so that the components ejected from the two component outlets can collide.

3. The thrust chamber impact injector according to claim 1, characterized in that: The aperture sizes of the component outlets in the same circle are the same; the aperture sizes of the component outlets in adjacent circles are different.

4. The thrust chamber impact injector according to claim 1, characterized in that: The distance between the impact site and the injector surface is 6 to 30 mm.

5. The thrust chamber impact injector according to claim 1, characterized in that: The distance between the impact site of the fuel component and the injector surface is different from the distance between the impact site of the oxidizer component and the injector surface.

6. The thrust chamber impact injector according to claim 1, characterized in that: The width of the injector ring is 10 to 50 mm.

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