CN116906214A - Injector - Google Patents

Abstract

The invention discloses an injector, which relates to the technical field of aerospace engines and is used to reduce the amount of high-temperature gas in contact with the injector and improve the cooling effect on the injector. The injector includes a housing, a separation plate, a first nozzle and a second nozzle, and the housing has a first accommodation chamber and a second accommodation chamber. The first nozzle includes an inner nozzle and an outer nozzle. The third end of the inner nozzle is a closed end. The fourth end is sealed and connected to the panel after passing through the isolation plate. The inner nozzle is connected with the combustion chamber. A first flow channel is provided on the inner nozzle, and the first flow channel is connected with the first accommodation cavity. The outer nozzle is sleeved outside the fourth end, and a second flow channel is provided on the outer nozzle. A third flow channel is formed between the inner wall of the outer nozzle and the outer wall of the inner nozzle. The second flow channel is connected with the second accommodation cavity and the third flow channel. The roads are connected. A fourth flow channel is provided in the second nozzle. The fourth flow channel extends spirally along the axial direction of the second nozzle. The second nozzle is used to inject the second propellant into the combustion chamber and form a liquid cone film.

Description

an injector

Technical field

The invention relates to the technical field of aerospace engines, and in particular to an injector.

Background technique

The liquid rocket engine is the core component of the spacecraft. It is a chemical rocket propulsion system that uses liquid chemicals as energy and working fluid. The thrust chamber of the engine is an important component that converts the chemical energy of the liquid propellant into thrust. The thrust chamber is composed of an injector, a combustion chamber, and a nozzle. The liquid propellant enters the combustion chamber through the injector, generates combustion products through atomization, mixing, and combustion processes, and is ejected from the nozzle at high speed to generate thrust.

As a key component of the thrust chamber, the injector plays a decisive role in the engine's performance. The working environment of the injector has the remarkable characteristics of high temperature, high pressure, and high heat flux density. During the working process, the injector is in direct contact with the high-temperature gas in the combustion chamber, and its reliable cooling must be ensured.

In order to ensure the reliability of injector cooling, in the existing technology, the propellant flow rate is generally increased or the panel on the side of the injector close to the combustion chamber is made of materials with high thermal conductivity. However, in actual use, the above methods The injector panel will be ablated by the high-temperature gas in the combustion chamber and cannot effectively cool the injector.

Contents of the invention

The object of the present invention is to provide an injector for reducing the amount of high-temperature gas in contact with the injector and improving the cooling effect on the injector.

In order to achieve the above object, the present invention provides an injector, which includes a casing, a partition plate, a first nozzle and a second nozzle. The casing has a first end and a second end arranged oppositely. The first end and the second end Covers and panels are provided respectively. The edge of the isolation plate is sealingly connected to the inner wall of the casing. A first accommodation chamber for accommodating the first propellant is formed between the isolation plate, the casing and the cover plate. A first accommodation chamber is formed between the isolation plate, the casing and the panel. A second accommodation chamber for accommodating the second propellant. The first nozzle includes an inner nozzle and an outer nozzle. The inner nozzle has a third end and a fourth end arranged oppositely. The third end is located close to the first end. The third end is a closed end. The fourth end passes through the isolation plate. Connected to the panel, the inner nozzle communicates with the combustion chamber. A first flow channel is provided on the inner nozzle. The first flow channel is connected with the first accommodation chamber and is used for causing the first propellant to flow to the inner nozzle through the first flow channel. The outer nozzle is sleeved outside the fourth end, and a second flow channel is provided on the outer nozzle. A third flow channel is formed between the inner wall of the outer nozzle and the outer wall of the inner nozzle. The second flow channel is connected with the second accommodation cavity and the third flow channel. The third flow channel is connected to the combustion chamber. The second nozzle is provided on the panel, and a fourth flow channel is provided in the second nozzle. The fourth flow channel spirally extends along the axial direction of the second nozzle; both ends of the fourth flow channel are connected to the second accommodation chamber and the combustion chamber respectively. The two nozzles are used to inject the second propellant into the combustion chamber and form a liquid cone film.

When the above technical solution is adopted, the injector provided by the present invention includes a housing, a separation plate and a first nozzle. The separation plate, the housing and the cover plate are surrounded by a first accommodation chamber for containing the first propellant. The first nozzle includes an inner nozzle and an outer nozzle. The inner nozzle is provided with a first flow channel. The first flow channel is connected with the first accommodation chamber and is used to make the first propellant flow to the inner nozzle through the first flow channel, and then from the inner nozzle. The fourth end is injected into the combustion chamber. The outer nozzle is sleeved outside the fourth end, and a second flow channel is provided on the outer nozzle. A third flow channel is formed between the inner wall of the outer nozzle and the outer wall of the inner nozzle. The second flow channel is connected with the second accommodation cavity and the third flow channel. The third flow channel is also connected to the combustion chamber. It is set up in such a way that the second propellant is injected into the combustion chamber after passing through the second flow channel and the third flow channel. The first propellant and the second propellant are burning. It is atomized, mixed and burned indoors to produce high-temperature gas. In addition, the injector provided by the present invention further includes a second nozzle. The second nozzle is provided on the panel. A fourth flow channel is provided in the second nozzle. The fourth flow channel extends spirally along the axial direction of the second nozzle. The fourth flow channel Both ends of the passage are connected to the second accommodation chamber and the combustion chamber respectively, so that the second propellant in the second accommodation chamber enters the combustion chamber through the fourth flow passage, thereby causing the second nozzle to inject the second propellant into the combustion chamber. , and forms a liquid cone film. The liquid cone film separates the panel of the injector from the high-temperature gas and prevents the high-temperature gas from directly contacting the panel and ablating the panel. Furthermore, it can improve the cooling effect of the injector and extend the use of the injector. life.

Description of the drawings

The drawings described here are used to provide a further understanding of the present invention and constitute a part of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the attached picture:

Figure 1 is a bottom view of an injector provided by an embodiment of the present invention;

Figure 2 is a partial schematic diagram of A-A in Figure 1;

Figure 3 is an enlarged schematic diagram of point B in Figure 2.

Reference signs:

1—casing, 11—panel, 2—isolation plate, 3—first accommodation chamber, 4—second accommodation chamber,

5—the first nozzle, 51—the inner nozzle, 511—the first flow channel, 512—the step, 52—the outer nozzle,

521—second flow channel, 522—third flow channel, 53—mixing chamber, 6—second nozzle, 61—casing, 62—nozzle body, 63—fourth flow channel.

Detailed ways

In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer, the present invention will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention and are not intended to limit the present invention.

It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

In addition, the terms “first” and “second” are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of indicated technical features. Therefore, features defined as "first" and "second" may explicitly or implicitly include one or more of these features. In the description of the present invention, "plurality" means two or more than two, unless otherwise explicitly and specifically limited. "Several" means one or more than one, unless otherwise expressly and specifically limited.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "back", "left", "right", etc. are based on those shown in the accompanying drawings. The orientation or positional relationship is only for the convenience of describing the present invention and simplifying the description. It does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention.

In the description of the present invention, it should be noted that, unless otherwise clearly stated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection or a detachable connection. Connection, or integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be an internal connection between two elements or an interaction between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

For the liquid oxygen kerosene engine thrust chamber, its working environment has the remarkable characteristics of high temperature (about 3600K), high pressure (about 20MPa), and high heat flow density (about 60MW/m ² ). As a key component of the thrust chamber, the injector It is used to spray, atomize and mix propellant components to ensure stable and efficient operation of the engine, which plays a decisive role in the engine's performance. During the working process, the injector is in direct contact with the high-temperature gas in the combustion chamber, and its reliable cooling must be ensured. Reliable cooling of the injector surface has become one of the keys to the open cycle liquid oxygen kerosene engine. In the existing technology, methods are generally used to increase the propellant flow rate or use materials with high thermal conductivity for the panel on the side of the injector close to the combustion chamber. However, during actual use of the above methods, the injector panel will be affected by the high temperature in the combustion chamber. The ablation of gas cannot effectively cool the injector.

In addition, at present, the injector panels of the thrust chambers of engines such as liquid oxygen, liquid hydrogen, and liquid oxygen methane generally use sweating panels, which form a low-temperature environment on the injector surface through the penetration of liquid hydrogen or methane. However, the sweat cooling structure is complex, and kerosene is easy to coke and deposit carbon, which can easily block the tiny sweat cooling holes. When using kerosene as fuel, the injector cannot use the sweat cooling method because kerosene is easy to coke. The afterburning cycle engine uses copper alloy materials with high chamber pressure and high thermal conductivity and copper-steel brazing connections. It has a complex structure, many processing steps, a long cycle, and a very high cost.

In order to solve the above technical problems existing in the prior art, as shown in Figures 1 and 2, an embodiment of the present invention provides an injector, including a housing 1, a separation plate 2, a first nozzle 5 and a second nozzle 6 , the housing 1 has a first end and a second end arranged oppositely, and the first end and the second end are respectively provided with a cover plate and a panel 11. The edge of the isolation plate 2 is sealingly connected to the inner wall of the casing 1. A first accommodation chamber 3 for accommodating the first propellant is formed between the isolation plate 2, the casing 1 and the cover plate. The isolation plate 2, the casing 1 A second accommodation chamber 4 for accommodating the second propellant is formed between the insulator and the panel 11 . The first nozzle 5 includes an inner nozzle 51 and an outer nozzle 52. The inner nozzle 51 has a third end and a fourth end arranged oppositely. The third end is located close to the first end, the third end is a closed end, and the fourth end passes through After passing through the isolation plate 2, it is connected to the panel 11, and the inner nozzle 51 is connected with the combustion chamber. The inner nozzle 51 is provided with a first flow channel 511 . The first flow channel 511 is connected with the first accommodation chamber 3 and is used to allow the first propellant to flow to the inner nozzle 51 through the first flow channel 511 . The outer nozzle 52 is sleeved outside the fourth end. The outer nozzle 52 is provided with a second flow channel 521. A third flow channel 522 is formed between the inner wall of the outer nozzle 52 and the outer wall of the inner nozzle 51. The second flow channel 521 is connected to the outer wall of the inner nozzle 51. The second accommodation cavity 4 is connected to the third flow channel 522, and the third flow channel 522 is also connected to the combustion chamber. The second nozzle 6 is provided on the panel 11. A fourth flow channel 63 is provided in the second nozzle 6. The fourth flow channel 63 extends spirally along the axial direction of the second nozzle 6. Both ends of the fourth flow channel 63 are connected to the second flow channel 63 respectively. Accommodating the chamber 4 and the combustion chamber, the second nozzle 6 is used to inject the second propellant into the combustion chamber and form a liquid cone film.

When the above technical solution is adopted, the injector provided by the embodiment of the present invention includes a housing 1, a separation plate 2 and a first nozzle 5. The separation plate 2, the housing 1 and the cover plate are surrounded by a formation for accommodating the first propeller. The first containing chamber 3 of the agent, the first nozzle 5 includes an inner nozzle 51 and an outer nozzle 52, the inner nozzle 51 is provided with a first flow channel 511, the first flow channel 511 is connected with the first containing cavity 3, and is used to make the first propulsion The agent flows to the inner nozzle 51 through the first flow channel 511, and is then injected into the combustion chamber from the fourth end of the inner nozzle 51. The outer nozzle 52 is sleeved outside the fourth end. The outer nozzle 52 is provided with a second flow channel 521. A third flow channel 522 is formed between the inner wall of the outer nozzle 52 and the outer wall of the inner nozzle 51. The second flow channel 521 is connected to the outer wall of the inner nozzle 51. The second accommodation chamber 4 is connected to the third flow channel 522, and the third flow channel 522 is also connected to the combustion chamber. This arrangement allows the second propellant to be injected into the combustion chamber after passing through the second flow channel 521 and the third flow channel 522. , the first propellant and the second propellant are atomized, mixed and burned in the combustion chamber to produce high-temperature gas. In addition, the injector provided by the present invention also includes a second nozzle 6. The second nozzle 6 is provided on the panel 11. A fourth flow channel 63 is provided in the second nozzle 6. The fourth flow channel 63 is along the axis of the second nozzle 6. The direction spirally extends, and both ends of the fourth flow channel 63 are connected to the second accommodation chamber 4 and the combustion chamber respectively, so that the second propellant in the second accommodation chamber 4 enters the combustion chamber through the fourth flow channel 63, thereby making the second propellant enter the combustion chamber through the fourth flow channel 63. The nozzle 6 injects the second propellant into the combustion chamber and forms a liquid cone film. The liquid cone film separates the panel 11 of the injector from the high-temperature gas and prevents the high-temperature gas from directly contacting the panel 11 and ablating the panel 11. Further, It can improve the cooling effect of the injector, extend the service life of the injector, and reduce the cost of using the injector.

In specific implementation, the first propellant may be liquid oxygen, the second propellant may be fuel, and the fuel may be kerosene. Of course, this is only an example and is not a specific limitation. It should be noted that with the development of low-cost liquid oxygen and kerosene engines, the salient features of liquid oxygen and kerosene engines are medium chamber pressure, low cost and rapid development and production. High-performance, open-cycle liquid oxygen and kerosene engines based on additive manufacturing Become one of the main directions of development. The open cycle liquid oxygen kerosene engine thrust adopts the form of a coaxial centrifugal injector, that is, in the injector provided by the embodiment of the present invention, the inner nozzle 51 and the outer nozzle 52 are coaxially arranged. In actual situations, mounting holes for installing the first nozzle 5 and the second nozzle 6 are opened on the panel 11, and the outlet ends of the first nozzle 5 and the second nozzle 6 are both connected to the combustion chamber. The panel 11 can be made of stainless steel. Compared with the copper alloy material of the panel 11 in the prior art, the cost of the panel 11 is lower. In this way, the cost of the injector can be reduced. It should be noted that after the second propellant injected from the second nozzle 6 forms a liquid cone film, it participates in combustion in the combustion chamber to avoid waste of the second propellant.

In one example, as shown in FIG. 3 , the second nozzle 6 includes a shell 61 and a nozzle body 62 . The shell 61 is fixedly provided on the panel 11 . The nozzle body 62 is sleeved in the shell 61 . The outer wall of the nozzle body 62 is provided with a A fourth flow channel 63 is formed between the swirl groove and the inner wall of the housing 61 . The swirl groove extends from one end of the second nozzle 6 away from the combustion chamber to an end close to the combustion chamber. Further, the two ends of the fourth flow channel 63 are respectively connected with the second accommodation chamber and the combustion chamber. The swirl groove can be understood as Similar to the external threads provided on the outer wall of the nozzle body 62, the second propellant flows along the extending direction of the swirl groove, thus facilitating the formation of the liquid cone film.

In another example, the second nozzle 6 has a cylindrical structure, and a spiral arrangement is opened in the second nozzle 6 in the direction from an end of the second nozzle 6 away from the combustion chamber to an end of the second nozzle 6 close to the combustion chamber. The tangential hole is the fourth flow channel 63. In this case, the tangential hole extends spirally with the axis of the second nozzle 6 as the axis.

In a possible implementation, in the direction from the end of the second nozzle 6 away from the combustion chamber to the end of the second nozzle 6 close to the combustion chamber, the inner wall of the shell 61 has a first cylindrical section, a constriction section, and a mutually connected first cylindrical section. The second cylindrical section, the nozzle body 62 matches the first cylindrical section. The structure of the contraction section can be a frustum-like structure, and the diameter of the second cylindrical section is smaller than the diameter of the first cylindrical section. This facilitates the formation of the liquid cone membrane, and makes the diameter of the formed liquid cone membrane larger, making the liquid cone membrane The area of the covered panel 11 is increased, minimizing the area of high-temperature gas in direct contact with the panel 11 and enhancing the protective effect on the panel 11 .

In some embodiments, as shown in FIG. 1 , the number of first nozzles 5 is multiple, and the multiple first nozzles 5 form multiple first nozzle groups, and each first nozzle group includes multiple first nozzles. 5 are arranged along the circumferential direction of the housing 1, and a plurality of first nozzle groups are arranged sequentially along the radial direction of the housing 1. At this time, the uniformity of distribution of the first propellant and the second propellant in the combustion chamber can be improved, the mixing effect of the first propellant and the second propellant can be enhanced, and the combustion efficiency and effect of the combustion chamber can be improved.

In a possible implementation, as shown in FIGS. 1 and 2 , the number of second nozzles 6 is multiple, and at least one second nozzle 6 is provided between any adjacent first nozzles 5 . During specific implementation, the second nozzles 6 should be installed at other exposed positions on the panel 11 except the first nozzle 5 as much as possible. In this way, the area of the panel 11 covered by the liquid cone film can be increased and the protection of the panel 11 can be enhanced. effect. The diameter of the second nozzle 6 can be 4mm-5mm, of course, it depends on the actual situation.

It should be noted that while ensuring reliable cooling of the panel 11, the combustion efficiency of the combustion chamber also needs to be considered. The flow rate of the second propellant injected from the second nozzle 6 cannot be too large, otherwise it will affect the first propellant on the injector. Mixing ratio distribution of nozzle 5. In specific implementation, the ratio of the second propellant flow rate used for cooling to the total flow rate of the second propellant sprayed from the injector is about 3% to 10%. The second nozzle 6 can be a small flow nozzle. It can work stably at a flow rate of ≯10g/s, and at the same time, it can form a liquid film cone with a large angle at the outlet of the second nozzle 6. These liquid film cones can cover the panel 11 as much as possible except for the first nozzle 5 and the second nozzle. The exposed position outside the second nozzle 6 effectively prevents high-temperature gas from flowing back and protects the injector panel 11 .

As an optional way, the fourth end of the inner nozzle 51 is accommodated in the outer nozzle 52 , so that a mixing chamber 53 is formed between the inner nozzle 51 and the outer nozzle 52 , so that the first propulsion injected from the first nozzle 5 The first propellant and the second propellant can be atomized and mixed in the mixing chamber 53, which can improve the mixing effect of the first propellant and the second propellant.

As a possible implementation method, the outer shell 61 and the nozzle body 62 have an interference fit, which makes the installation of the second nozzle 6 convenient and quick. Of course, the outer shell 61 can also be connected to the nozzle body 62 through welding. This is just an example. description, not as a specific limitation.

In an optional manner, the inner nozzle 51 has a step 512 at the connection position with the isolation plate 2. The step 512 is resisted and limited on the side of the isolation plate 2 close to the second accommodation cavity. In this way, the installation of the first nozzle 5 in the shell can be enhanced. The stability within the body 1 improves the structural stability of the injector.

In the above description of the embodiments, specific features, structures, materials or characteristics may be combined in any suitable manner in any one or more embodiments or examples.

The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the present invention, and all of them should be covered. within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims (10)

1. An injector, characterized in that it includes: A shell, the shell has a first end and a second end arranged oppositely, and the first end and the second end are respectively provided with a cover plate and a panel; An isolation plate, the edge of which is sealingly connected to the inner wall of the housing, and a first accommodation chamber for accommodating the first propellant is formed between the isolation plate, the housing and the cover plate. ; A second accommodation chamber for accommodating the second propellant is formed between the isolation plate, the housing and the panel; A first nozzle, including an inner nozzle and an outer nozzle; the inner nozzle has a third end and a fourth end arranged oppositely, the third end is located close to the first end, and the third end is a closed end , the fourth end passes through the isolation plate and is connected to the panel, the inner nozzle is connected to the combustion chamber; a first flow channel is provided on the inner nozzle, and the first flow channel is connected to the first accommodation The cavities are connected to allow the first propellant to flow to the inner nozzle through the first flow channel; the outer nozzle is sleeved outside the fourth end, and a second flow channel is provided on the outer nozzle. , a third flow channel is formed between the inner wall of the outer nozzle and the outer wall of the inner nozzle, the second flow channel is connected to the second accommodation cavity and the third flow channel, and the third flow channel Also communicated with the combustion chamber; A second nozzle is provided on the panel. A fourth flow channel is provided in the second nozzle. The fourth flow channel extends spirally along the axial direction of the second nozzle; both ends of the fourth flow channel The second accommodation chamber and the combustion chamber are respectively connected, and the second nozzle is used to inject the second propellant into the combustion chamber and form a liquid cone film. 2. The injector according to claim 1, wherein the second nozzle includes: A shell, provided on the panel; The nozzle body is sleeved in the housing; a swirl groove is provided on the outer wall of the nozzle body, and the fourth flow channel is formed between the swirl groove and the inner wall of the housing. 3. The injector according to claim 1, wherein the second nozzle is a cylindrical structure, extending in a direction from an end of the second nozzle away from the combustion chamber to an end close to the combustion chamber. , a spirally arranged tangential hole is opened in the second nozzle, and the tangential hole is the fourth flow channel. 4. The injector according to claim 2, wherein from an end of the second nozzle away from the combustion chamber to an end close to the combustion chamber, the inner wall of the housing has interconnected A first cylindrical section, a constriction section and a second cylindrical section; the nozzle body cooperates with the first cylindrical section. 5. The injector according to claim 1, wherein the number of the first nozzles is multiple, and the plurality of first nozzles form a plurality of first nozzle groups, and each of the first nozzles The plurality of first nozzles included in the group are arranged along the circumferential direction of the housing; the plurality of first nozzle groups are arranged sequentially along the radial direction of the housing. 6. The injector according to claim 5, wherein the number of the second nozzles is multiple, and at least one second nozzle is provided between any adjacent first nozzles. 7. The injector according to claim 1, wherein the panel is made of stainless steel. 8. The injector according to claim 1, wherein the fourth end of the inner nozzle is accommodated in the outer nozzle, so that a mixing chamber is formed between the inner nozzle and the outer nozzle. . 9. The injector according to claim 2, wherein the housing is an interference fit with the nozzle body. 10. The injector according to claim 1, wherein the inner nozzle has a step at a connection position with the isolation plate, and the step resists and is limited to the isolation plate close to the second accommodation cavity. side.