Cooling nozzle structure and fuel gas generator

Abstract

The invention belongs to the technical field of aerospace equipment, and particularly relates to a cooling nozzle structure and a fuel gas generator. The cooling nozzle structure comprises a cooling spray pipe assembly and a cooling medium connector. A nozzle and a cooling medium cavity are formed in the cooling spray pipe assembly, the nozzle penetrates through the cooling spray pipe assembly in the axial direction of the cooling spray pipe assembly, and the cooling medium cavity surrounds the peripheral side of the nozzle. The cooling medium connector is arranged on the peripheral side of the cooling spray pipe assembly and communicates with the cooling medium cavity. Wherein the cooling medium connector is used for introducing a cooling medium into the cooling medium cavity, and the cooling medium cavity is used for guiding the cooling medium and spraying the cooling medium towards the nozzle so as to control the effective area of the nozzle. According to the cooling nozzle structure provided by the invention, the design of variable nozzle circulation cross section area is adopted, the pressure in the combustion chamber is adjusted, then thrust output is adjusted, and fuel is saved; and the ablation risk can be reduced, the temperature at the nozzle is reduced, and the service life of the structure is prolonged.

Description

Technical Field

[0001] This application belongs to the technical field of aerospace equipment, and particularly relates to a cooling nozzle structure and a gas generator. Background Art

[0002] Gas generators may have different pressure requirements for the system internal under different working conditions (such as changes in atmospheric pressure, temperature, etc. of the external environment, or changes in load conditions, etc.). For example, in a high-altitude environment, the external pressure is relatively low, and the pressure difference in the combustion chamber is more likely to be unbalanced, and a pressure regulation mechanism is required to achieve a stable operating state.

[0003] Existing gas generator technologies mostly adopt a fixed nozzle design, and its pressure control mainly relies on the preset of the throat size and the adjustment of the fuel supply rate. Generally, the mass flow rate of fuel is increased to adjust the pressure in the combustion chamber. This design can maintain a certain stability under short-term operating conditions, but during long-term operation, the heat load of the system gradually increases, the pressure in the combustion chamber fluctuates significantly, and it is easy to cause unstable thrust output or even damage the nozzle structure. Summary of the Invention

[0004] This application provides a cooling nozzle structure and a gas generator to solve the technical problems that the existing fixed nozzle design is difficult to adjust the pressure in the combustion chamber and has a large heat load.

[0005] According to one aspect of this application, a cooling nozzle structure is provided. The cooling nozzle structure includes a cooling nozzle assembly and a cooling medium joint. A nozzle and a cooling medium cavity are formed in the cooling nozzle assembly. The nozzle axially penetrates the cooling nozzle assembly, and the cooling medium cavity surrounds the outer peripheral side of the nozzle. The cooling medium joint is arranged on the peripheral side of the cooling nozzle assembly and communicates with the cooling medium cavity. Among them, the cooling medium joint is used to introduce the cooling medium into the cooling medium cavity, and the cooling medium cavity is used to guide the cooling medium and spray the cooling medium toward the nozzle to control the effective area of the nozzle.

[0006] In an optional solution of this application, the cooling medium cavity includes a cooling medium inlet cavity, a cooling medium diversion cavity, and a plurality of cooling medium spray holes; the cooling medium inlet cavity surrounds the outer peripheral side of the cooling medium diversion cavity and communicates with the cooling medium diversion cavity; the cooling medium diversion cavity surrounds the outer peripheral side of the nozzle and communicates with the nozzle through each cooling medium spray hole.

[0007] In an optional solution of this application, the plurality of cooling medium spray holes are evenly spaced along the circumferential direction of the nozzle.

[0008] In an optional solution of this application, the nozzle includes a reduced diameter section, the reduced diameter section is located on the axial outer side of the cooling nozzle assembly, and the plurality of cooling medium spray holes are all located in the reduced diameter section.

[0009] In an alternative embodiment of the present application, the cooling nozzle assembly includes a nozzle housing, a nozzle guide ring, and a nozzle body; the nozzle body is provided with a first nozzle portion axially penetrating through the cooling nozzle assembly, and a plurality of cooling medium spray holes penetrate through the circumferential wall of the nozzle body and communicate with the first nozzle portion; at least a part of the nozzle body extends axially into the nozzle housing along the axial direction of the cooling nozzle assembly and cooperates with the nozzle housing to form an annular cavity for the circulation of the cooling medium; the nozzle guide ring is provided with a plurality of cooling medium through holes and is clamped between the nozzle housing and the nozzle body to divide the annular cavity into a cooling medium inlet cavity and a cooling medium guiding cavity, and each cooling medium through hole communicates the cooling medium inlet cavity with the cooling medium guiding cavity.

[0010] In an alternative embodiment of the present application, the cooling nozzle assembly further includes a combustion chamber connection ring, and the combustion chamber connection ring is provided with a second nozzle portion axially penetrating through the cooling nozzle assembly; the combustion chamber connection ring is connected to the axially far side of the nozzle body away from the nozzle housing, and the second nozzle portion communicates with the first nozzle portion to form a nozzle.

[0011] In an alternative embodiment of the present application, the nozzle housing, the nozzle guide ring, the nozzle body, and the combustion chamber connection ring are arranged to be detachably connected.

[0012] In an alternative embodiment of the present application, the cooling nozzle assembly further includes a first sealing ring and a second sealing ring; both the first sealing ring and the second sealing ring are clamped between the nozzle housing and the nozzle body and are respectively located at the axial two ends of the annular cavity.

[0013] According to another aspect of the present application, a gas generator is provided, and the gas generator includes a combustion chamber structure, an atomizing nozzle, an igniter, and the above-mentioned cooling nozzle structure; a combustion chamber is formed inside the combustion chamber structure, the atomizing nozzle and the cooling nozzle structure are respectively arranged at the axial two ends of the combustion chamber structure, and the nozzle communicates with the combustion chamber; the igniter is arranged on the circumferential wall of the combustion chamber structure and is arranged close to the atomizing nozzle and is used for igniting the atomized fuel sprayed into the combustion chamber from the atomizing nozzle.

[0014] In an alternative embodiment of the present application, the gas generator further includes a sensor, and the sensor is arranged on the combustion chamber structure to be used for detecting the pressure and temperature inside the combustion chamber.

[0015] In summary, the cooling nozzle structure and the gas generator provided by the present application have at least the following beneficial effects:

[0016] A nozzle and a cooling medium cavity are formed inside the cooling nozzle assembly in the cooling nozzle structure, the cooling medium cavity surrounds the circumference of the nozzle, and the cooling medium is introduced through the cooling medium joint. After passing through the cooling medium cavity, the cooling medium can be sprayed into the nozzle, thereby squeezing the effective area of the nozzle. The effective area of the nozzle refers to the cross-sectional area allowing the cooling medium to flow through.

[0017] This solution adopts the design of a variable nozzle flow cross-sectional area to replace the existing fixed throat design solution. Specifically, the ejected cooling medium can squeeze the effective area of the nozzle to precisely control the pressure in the combustion chamber. At the same time, it can also flexibly adjust the thrust output, significantly improving the adaptability and performance diversity of the thrust system equipped with this gas generator. Moreover, compared with the existing method of adjusting the combustion chamber pressure by increasing the mass flow rate of fuel, it can save fuel.

[0018] In addition, the cooling medium flows in the cooling medium cavity surrounding the outer peripheral side of the nozzle, which can effectively reduce the serious ablation risk brought by the high-temperature gas at the nozzle. Moreover, the mixing of the cooling medium and the high-temperature gas can also reduce the gas temperature at the nozzle, thereby significantly extending the service life of this cooling nozzle structure and reducing the maintenance difficulty and cost. Brief Description of the Drawings

[0019] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings required for the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present application. For those skilled in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0020] Figure 1 Schematic diagram of a gas generator provided according to one embodiment of the present application;

[0021] Figure 2 Cross-sectional view of a cooling nozzle structure provided according to one embodiment of the present application;

[0022] Figure 3 For Figure 2 Partial enlarged view at S in

[0023] Figure 4 For Figure 2 Exploded view of the cooling nozzle structure in

[0024] The reference numerals are as follows:

[0025] 1000, gas generator;

[0026] 100, cooling nozzle structure;

[0027] 10. Cooling nozzle assembly; 11. Nozzle housing; 12. Nozzle guide ring; H2. Cooling medium through-hole; 13. Nozzle body; 131. Nozzle section; 132. Flange; 14. Combustion chamber connection ring; 15. First sealing ring; 16. Second sealing ring; C. Nozzle; C1. First nozzle part; C2. Second nozzle part; D1. Cooling medium chamber; D11. Cooling medium inlet chamber; D12. Cooling medium guide chamber; H1. Cooling medium spray hole;

[0028] 20. Cooling medium connector; D2. Cooling medium inlet;

[0029] 200. Combustion chamber structure; R. Combustion chamber;

[0030] 300. Atomizing nozzle; 400. Igniter; 500. Sensor. Detailed implementation manner

[0031] In addition, features limited by "first" and "second" for descriptive purposes only should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Features limited by "first" and "second" may explicitly or implicitly include at least one of the limited features. When the description "a plurality of" appears, the general meaning is at least two, such as two, three, etc., unless otherwise specifically limited.

[0032] In this application, unless otherwise clearly specified and limited, terms such as "installed", "connected", "connected to", "fixed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection, an electrical connection, a direct connection, or an indirect connection through an intermediate medium, and can be the communication inside two components or the interaction relationship between two components. For those skilled in the art, the specific meanings of the above terms in this application can be understood according to specific situations.

[0033] In the description of this specification, terms such as "an embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of this application. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0034] Figure 1Schematic diagram of a gas generator 1000 provided according to one embodiment of the present application. Please refer to Figure 1 , the gas generator 1000 includes a cooling nozzle structure 100, a combustion chamber structure 200, an atomizing nozzle 300, and an igniter 400.

[0035] A combustion chamber R is formed within the combustion chamber structure 200. The atomizing nozzle 300 and the cooling nozzle structure 100 are respectively disposed at two axial ends of the combustion chamber structure 200, and both the atomizing nozzle 300 and the cooling nozzle structure 100 communicate with the combustion chamber R.

[0036] The igniter 400 is disposed on the peripheral wall of the combustion chamber structure 200 and is arranged close to the atomizing nozzle 300, and is used to ignite the atomized fuel sprayed into the combustion chamber R from the atomizing nozzle 300.

[0037] In this embodiment, the gas generator 1000 can be applied to the engine system in the aerospace field. Specifically, the combustion chamber R within the combustion chamber structure 200 provides a closed space for the combustion of the fuel. The atomizing nozzle 300 can introduce the fuel and atomize the fuel and then spray it into the combustion chamber R, and the igniter 400 can ignite the atomized fuel within the combustion chamber R.

[0038] In this way, the ignited atomized fuel can generate high-temperature and high-pressure gas within the combustion chamber R. The high-temperature and high-pressure gas can further expand and eject through the cooling nozzle structure 100, and can provide power for the engine system.

[0039] It should be noted that atomization here refers to dispersing fuel droplets into tiny droplets. It can be understood that since the fuel is atomized after passing through the atomizing nozzle 300, it can greatly increase the contact area between the fuel and the air, ensure better mixing with the air, and improve the combustion rate and efficiency.

[0040] It should be understood that due to the presence of the atomizing nozzle 300, even in the case of a small flow rate of fuel, the small flow rate of fuel can be ensured to burn fully under the condition of fuel atomization. That is, the gas generator 1000 equipped with the atomizing nozzle 300 can adapt to the small flow rate of fuel working condition.

[0041] In an optional embodiment, the atomizing nozzle 300 is formed with self-excited spray holes. Through the design of the self-excited spray hole structure and by utilizing the fluid's own hydrodynamic characteristics, the fluid oscillates at the self-excited spray holes, thereby achieving the atomization effect. Of course, the atomizing nozzle 300 is not limited thereto.

[0042] Understandably, the igniter 400 is a key component for quickly igniting the atomized fuel and air mixture. The igniter 400 can be, for example, a pulse igniter, a piezoelectric ceramic igniter, etc. In a preferred embodiment, the igniter 400 is a hydrogen-oxygen igniter, and specifically, the ignition is completed by a torch formed by a mixture of hydrogen and oxygen. After ignition, hydrogen can continue to be introduced to improve the combustion efficiency. Moreover, the water vapor formed during the ignition process can promote the combustion of the fuel. In this way, the ignition reliability is improved.

[0043] In the illustrated embodiment, the combustion chamber structure 200 has a hollow cylindrical structure, and its axial direction is the extending direction of the axis line. The moving direction of the atomized fuel and the formed combustion gas in the combustion chamber R is the axial direction of the combustion chamber structure 200, that is, moving from the atomizing nozzle 300 towards the cooling nozzle structure 100 and spraying out from the cooling nozzle structure 100.

[0044] Figure 2 It is a cross-sectional view of the cooling nozzle structure 100 provided according to one embodiment of the present application. Figure 3 For Figure 2 the exploded view of the cooling nozzle structure 100 in. Please refer to Figure 2 and Figure 3 , in some alternative embodiments, the cooling nozzle structure 100 includes a cooling nozzle assembly 10 and a cooling medium joint 20.

[0045] A nozzle C and a cooling medium cavity D1 are formed in the cooling nozzle assembly 10. The nozzle C penetrates the cooling nozzle assembly 10 along the axial direction of the cooling nozzle assembly 10, and the cooling medium cavity D1 surrounds the outer peripheral side of the nozzle C. The cooling medium joint 20 is disposed on the peripheral side of the cooling nozzle assembly 10 and communicates with the cooling medium cavity D1.

[0046] Among them, the cooling medium joint 20 is used to introduce the cooling medium into the cooling medium cavity D1, and the cooling medium cavity D1 is used to guide the cooling medium and spray the cooling medium towards the nozzle C to control the effective area of the nozzle C.

[0047] In this embodiment, the cooling nozzle structure 100 at least includes a cooling nozzle assembly 10 and a cooling medium joint 20. Among them, a nozzle C is formed in the cooling nozzle assembly 10, and the nozzle C communicates with the combustion chamber R. The high-temperature and high-pressure combustion gas in the combustion chamber R can be sprayed out from the nozzle C.

[0048] Moreover, a cooling medium cavity D1 surrounding the outer peripheral side of the nozzle C is also formed in the cooling nozzle assembly 10. The cooling medium cavity D1 communicates with the cooling medium joint 20, and the cooling medium joint 20 can be connected to a cooling medium supply pipeline to supply the cooling medium to the cooling medium cavity D1.

[0049] Under the guidance of the cooling medium in the cooling medium cavity D1, it can be ejected into the nozzle C, thereby changing the area of the nozzle C. The area here refers to the area that allows the high-temperature and high-pressure gas to flow through the nozzle C, that is, the cross-sectional area perpendicular to the axial direction of the nozzle C. It can be understood that the size of the narrowest part of the nozzle C is one of the important factors affecting the pressure, thrust, gas flow velocity, etc. in the combustion chamber R. The effective area of the nozzle C refers to the cross-sectional area of its narrowest part, that is, the minimum flow cross-sectional area of the nozzle C.

[0050] It should be understood that the injection depth of the cooling medium into the nozzle C can squeeze the effective area of the nozzle C, thereby achieving the purpose of controlling the effective area of the nozzle C. In specific applications, parameters such as the pressure and flow rate of the provided cooling medium can be controlled to control the injection depth of the cooling medium in the nozzle C, thereby regulating the effective area of the nozzle C.

[0051] It can be seen that this solution adopts the design of a variable nozzle flow cross-sectional area to replace the existing fixed throat design solution. Specifically, the ejected cooling medium can squeeze the effective area of the nozzle to precisely control the pressure in the combustion chamber R, and at the same time, it can also flexibly adjust the thrust output, significantly improving the adaptability and performance diversity of the thrust system equipped with the gas generator 1000. And, compared with the existing method of increasing the mass flow rate of fuel to adjust the combustion chamber pressure, it can save fuel.

[0052] In addition, the cooling medium flows in the cooling medium cavity D1 surrounding the outer peripheral side of the nozzle C, which can effectively reduce the serious ablation risk caused by high-temperature gas at the nozzle. And, the mixing of the cooling medium and the high-temperature gas can also reduce the gas temperature at the nozzle, thereby significantly extending the service life of the cooling nozzle structure 100 and reducing the maintenance difficulty and cost.

[0053] In an optional embodiment, the cooling medium is water, but of course it is not limited to this. For example, it can also be a liquid mixture containing water. In an optional embodiment, a cooling medium inlet D2 is formed in the cooling medium joint 20. The cooling medium inlet D2 communicates with the cooling medium cavity D1 and enables the cooling medium to flow to introduce the cooling medium into the cooling medium cavity D1.

[0054] Figure 3 For Figure 2 the partial enlarged view at S in Figure 3 Please refer to In a further optional embodiment, the cooling medium cavity D1 includes a cooling medium inlet cavity D11, a cooling medium diversion cavity D12, and a plurality of cooling medium spray holes H1. The cooling medium inlet cavity D11 surrounds the outer peripheral side of the cooling medium diversion cavity D12 and communicates with the cooling medium diversion cavity D12. The cooling medium diversion cavity D12 surrounds the outer peripheral side of the nozzle C and communicates with the nozzle C via each cooling medium spray hole H1.

[0055] In this embodiment, the cooling medium cavity D1 adopts a double-layer annular cavity layout design. Judging based on the axis line of the nozzle C, the cooling medium inlet cavity D11 is relatively outer, and the cooling medium guiding cavity D12 is relatively inner. Both of them are annular cavities surrounding the nozzle C and are connected.

[0056] Moreover, a plurality of cooling medium spray holes H1 are provided on the inner peripheral wall of the nozzle C. The cooling medium spray holes H1 are connected to the cooling medium guiding cavity D12, and then the cooling medium is led out from the cooling medium guiding cavity D12 into the nozzle C. In addition, the cooling medium inlet cavity D11 is connected to the cooling medium inlet D2 to introduce the cooling medium into the cavity.

[0057] In this solution, the double-layer annular cavity design is adopted to realize the flow of the cooling medium, ensure the uniform flow of the cooling medium on the outer peripheral side of the nozzle C, reduce the risk of overheating caused by uneven cooling or local retention, and improve the thermal stability and reliability of the cooling nozzle structure 100 by optimizing the cooling water flow path.

[0058] In a further optional embodiment, a plurality of cooling medium spray holes H1 are arranged at equal intervals along the circumferential direction of the nozzle C. In this embodiment, the included angles formed by the connecting lines from the centers of any two adjacent cooling medium spray holes H1 to the axis line of the nozzle C are equal, that is, they are evenly arranged in the circumferential direction.

[0059] In this way, a uniformly distributed cooling medium spray column can be formed on the circumferential side of the nozzle C, that is, a cooling medium ring is formed to uniformly squeeze the effective area of the nozzle C. This layout of the cooling medium spray holes H1 is more conducive to ensuring the accuracy of controlling the effective area of the nozzle C.

[0060] In a further optional embodiment, the nozzle C includes a reduced diameter section, and the reduced diameter section is located axially outside the cooling nozzle assembly 10, and a plurality of cooling medium spray holes H1 are all located in the reduced diameter section.

[0061] It can be understood that the area of the nozzle C mentioned above refers to the area at the reduced diameter section of the nozzle C. The reduced diameter section is the section with the smallest area in the nozzle C, and the opening size of the reduced diameter section is one of the important factors affecting the pressure in the combustion chamber R, the output thrust, and the gas flow velocity and flow rate of the ejected gas.

[0062] Here, the flow cross-sectional area of the reduced diameter section is adjusted by these cooling medium spray holes H1. Specifically, the effective area of the nozzle C refers to the flow cross-sectional area of its reduced diameter section.

[0063] Figure 4 For Figure 2 the explosion view of the cooling nozzle structure 100 in. Please refer to Figure 4, in some alternative embodiments, the cooling nozzle assembly 10 includes a nozzle housing 11, a nozzle guide ring 12, and a nozzle body 13.

[0064] The nozzle body 13 is provided with a first nozzle portion C1 axially penetrating through the cooling nozzle assembly 10, and a plurality of cooling medium spray holes H1 penetrate through the circumferential wall of the nozzle body 13 and communicate with the first nozzle portion C1.

[0065] At least a part of the nozzle body 13 extends axially into the nozzle housing 11 along the cooling nozzle assembly 10 and cooperates with the nozzle housing 11 to form an annular cavity for the circulation of the cooling medium.

[0066] The nozzle guide ring 12 is provided with a plurality of cooling medium through holes H2 and is clamped between the nozzle housing 11 and the nozzle body 13 to divide the annular cavity into a cooling medium inlet cavity D11 and a cooling medium guiding cavity D12, and each cooling medium through hole H2 communicates the cooling medium inlet cavity D11 and the cooling medium guiding cavity D12.

[0067] In this embodiment, the nozzle housing 11, the nozzle guide ring 12, and the nozzle body 13 are sequentially spliced axially, the nozzle guide ring 12 is clamped between the nozzle housing 11 and the nozzle body 13, and the nozzle housing 11 cooperates with the nozzle body 13 to form an annular cavity therebetween.

[0068] The annular cavity is divided by the nozzle guide ring 12 to form a double-layer annular cavity layout and corresponds to the cooling medium inlet cavity D11 and the cooling medium guiding cavity D12 respectively. Moreover, a plurality of cooling medium through holes H2 are provided on the circumferential wall of the nozzle guide ring 12 to communicate the cooling medium inlet cavity D11 and the cooling medium guiding cavity D12, so that the cooling medium enters the nozzle C after passing through the cooling medium inlet D2, the cooling medium inlet cavity D11, the cooling medium through hole H2, the cooling medium guiding cavity D12, and the cooling medium spray hole H1.

[0069] In this way, after the cooling medium circulates circuitously through the double-layer annular cavity, the risk of local retention causing local overheating can be effectively reduced, and the cooling medium can also absorb heat sufficiently to ensure the cooling effect.

[0070] Specifically, the nozzle housing 11 is provided with an installation through hole axially penetrating, the nozzle body 13 is provided with a first nozzle portion C1 axially penetrating and a part of it extends into the installation through hole of the nozzle housing 11 to cooperate to form an annular cavity. The nozzle guide ring 12 is designed according to the shape of the annular cavity to divide the annular cavity.

[0071] In one embodiment, at least a part of the first nozzle portion C1 has a variable diameter design. Specifically, the first nozzle portion C1 is tapered along the direction of the gas ejection. In the illustrated embodiment, the first nozzle portion C1 is shaped like a flared opening, with the narrow end located on the outer side in the axial direction. In one embodiment, the constricted section of the nozzle C refers to the outer axial section of the first nozzle portion C1, where the opening size of this section is the smallest. Correspondingly, the cooling medium injection hole H1 is located at the constricted section of the first nozzle portion C1 to communicate with the first nozzle portion C1.

[0072] In one embodiment, a plurality of cooling medium through-holes H2 are evenly spaced on the circumferential wall of the nozzle guide ring 12. This facilitates the formation of a swirling flow of the cooling medium into the cooling medium guide cavity D12 to ensure the cooling effect.

[0073] In a further optional embodiment, the cooling nozzle assembly 10 further includes a combustion chamber connection ring 14, and the combustion chamber connection ring 14 is provided with a second nozzle portion C2 that axially penetrates through the cooling nozzle assembly 10.

[0074] The combustion chamber connection ring 14 is connected to the axial side of the nozzle body 13 away from the nozzle housing 11, and the second nozzle portion C2 communicates with the first nozzle portion C1 to form the nozzle C.

[0075] In this embodiment, the combustion chamber connection ring 14 is used for auxiliary assembly to achieve cooperation with the combustion chamber structure 200 to fix the entire cooling nozzle structure 100. The combustion chamber connection ring 14 is formed with a second nozzle portion C2, and the second nozzle portion C2 communicates with the first nozzle portion C1, thereby forming the nozzle C.

[0076] In a further optional embodiment, the nozzle housing 11, the nozzle guide ring 12, the nozzle body 13, and the combustion chamber connection ring 14 are provided as detachably connected.

[0077] In this embodiment, the nozzle housing 11, the nozzle guide ring 12, the nozzle body 13, and the combustion chamber connection ring 14 are axially spliced in sequence. In the illustrated embodiment, bolts are used to achieve the detachable connection, and it is also detachably assembled with the combustion chamber structure 200.

[0078] In this way, the cooling nozzle structure in this solution adopts a replaceable design, allowing the cooling nozzle structure 100 with different angles and sizes to be adjusted according to the task requirements. The replacement process is simplified through modular design. In addition, the convenient replaceability not only improves the adaptability of the gas generator 1000 but also enhances the flexibility of pressure regulation. In particular, during long-term operation, the pressure change caused by the ablation problem of the nozzle can be effectively corrected through replacement, avoiding the high cost and complex maintenance problems in the traditional design.

[0079] In an alternative embodiment, the nozzle housing 11 and the cooling medium connector 20 are integrally formed, thus ensuring better sealing performance. In another alternative embodiment, the nozzle housing 11 and the cooling medium connector 20 are detachably connected, such as by a threaded connection, which facilitates maintenance.

[0080] In an alternative embodiment, the nozzle body 13 includes a nozzle section 131 and a flange 132 located axially on one side of the nozzle section 131. A reduced-diameter section is formed inside the nozzle section 131, and a plurality of cooling medium spray holes H1 are evenly spaced on the circumferential wall of the nozzle section 131.

[0081] The nozzle section 131 extends into the nozzle housing 11 to cooperate with the nozzle housing 11 to form an annular cavity, and the flange 132 is located outside the nozzle housing 11 to assist in connecting the nozzle housing 11 and the combustion chamber connection ring 14.

[0082] In a specific application, under the extrusion of the connecting bolts, the nozzle guide ring 12 is clamped between the nozzle housing 11 and the nozzle body 13 to partition the annular cavity. The nozzle section 131 is provided with a boss for positioning to ensure the assembly accuracy of the nozzle section 131.

[0083] In a further alternative embodiment, the cooling nozzle assembly 10 further includes a first sealing ring 15 and a second sealing ring 16. Both the first sealing ring 15 and the second sealing ring 16 are clamped between the nozzle housing 11 and the nozzle body 13 and are respectively located at the axial two ends of the annular cavity.

[0084] In the present application, the annular cavity, as the main part of the cooling medium cavity D1, is axially formed by splicing the nozzle housing 11 and the nozzle body 13. Therefore, the first sealing ring 15 and the second sealing ring 16 are arranged at the axial two ends of the annular cavity to ensure the sealing performance of the annular cavity, that is, the sealing performance of the cooling medium cavity D1, and to prevent the leakage of the cooling medium.

[0085] In some alternative embodiments, the gas generator 1000 further includes a sensor 500, which is disposed on the combustion chamber structure 200 to detect the pressure and temperature in the combustion chamber R.

[0086] In the present embodiment, sensor mounting holes are provided on the circumferential wall of the combustion chamber structure 200 for mounting the sensor 500 to facilitate the acquisition of the pressure and temperature in the combustion chamber.

[0087] In one embodiment, the number of sensors 500 is 2, one of which is a temperature sensor and the other is a pressure sensor. In another embodiment, a single sensor 500 integrates temperature detection function and pressure detection function.

[0088] In summary, in the solution provided by this application, the cooling medium has a dual impact function. It can not only cool the nozzle but also extrude the locking section of nozzle C, flexibly adjusting the combustion chamber pressure. This solution only needs to adjust the flow rate and pressure of the cooling medium to control the pressure. Combined with the atomizing nozzle, it is especially suitable for small gas generators.

[0089] In addition, for a small engine system, it can dynamically adjust the thrust output by controlling the effective area of the nozzle to meet the pressure requirements under different conditions. Moreover, the mixing of the cooling medium and the high-temperature gas can effectively reduce the temperature at the ejection point, reduce the risk of component ablation, and extend the service life of the system.

[0090] Furthermore, by adopting a nozzle guide ring to form a double-layer annular cavity structure, the phenomenon of cooling dead zones in traditional designs is avoided. The optimization of the cooling medium flow path not only improves the cooling efficiency but also avoids overheating and thermal stress problems caused by excessive local temperature. The optimized cooling medium flow path ensures the uniformity and stability of the cooling medium flow, further enhancing the thermal stability and the adaptability to high-temperature and high-pressure environments during the pressure regulation process.

[0091] Furthermore, the adoptable replaceable nozzle design can adapt nozzles of different specifications according to different mission requirements, optimizing the pressure regulation effect. The modular design of the nozzle enables the nozzle to be quickly replaced when ablation or damage occurs, without the need to replace the entire cooling nozzle assembly. This design not only reduces the maintenance cost but also increases the flexibility and adaptability of the system, being especially suitable for gas generators operating under multiple conditions for a long time.

[0092] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present application. Those skilled in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present application.

Claims

1. A cooling nozzle structure, characterized in that: include: A cooling nozzle assembly (10) having a nozzle (C) and a cooling medium cavity (D1) formed therein, wherein the nozzle (C) penetrates the cooling nozzle assembly (10) along the axial direction of the cooling nozzle assembly (10), and the cooling medium cavity (D1) surrounds the outer peripheral side of the nozzle (C); and A cooling medium joint (20) is arranged on the peripheral side of the cooling nozzle assembly (10) and is connected to the cooling medium cavity (D1); The cooling medium joint (20) is used to introduce cooling medium into the cooling medium cavity (D1), and the cooling medium cavity (D1) is used to guide the cooling medium and spray the cooling medium toward the nozzle (C) to control the effective area of ​​the nozzle (C).

2. The cooling nozzle structure according to claim 1, characterized in that: The cooling medium cavity (D1) comprises a cooling medium inlet cavity (D11), a cooling medium guide cavity (D12) and a plurality of cooling medium spray holes (H1); The cooling medium inlet chamber (D11) surrounds the outer peripheral side of the cooling medium flow guide chamber (D12) and is connected to the cooling medium flow guide chamber (D12); The cooling medium guide cavity (D12) surrounds the outer peripheral side of the nozzle (C) and is connected to the nozzle (C) via each of the cooling medium spray holes (H1).

3. The cooling nozzle structure according to claim 2, characterized in that: The plurality of cooling medium spray holes (H1) are evenly spaced apart along the circumference of the spray port (C).

4. The cooling nozzle structure according to claim 2, characterized in that: The nozzle (C) comprises a constricted section, the constricted section is located axially outside the cooling nozzle assembly (10), and the plurality of cooling medium spray holes (H1) are all located in the constricted section.

5. The cooling nozzle structure according to claim 2, characterized in that: The cooling nozzle assembly (10) comprises a nozzle housing (11), a nozzle guide ring (12) and a nozzle body (13); The nozzle body (13) is provided with a first nozzle portion (C1) penetrating along the axial direction of the cooling nozzle assembly (10), and a plurality of cooling medium spray holes (H1) penetrate the peripheral wall of the nozzle body (13) and are connected to the first nozzle portion (C1); At least a portion of the nozzle body (13) extends into the nozzle housing (11) along the axial direction of the cooling nozzle assembly (10), and cooperates with the nozzle housing (11) to form an annular cavity for the circulation of cooling medium; The nozzle guide ring (12) is provided with a plurality of cooling medium through holes (H2) and is clamped between the nozzle shell (11) and the nozzle body (13) to separate the ring cavity into the cooling medium inlet cavity (D11) and the cooling medium guide cavity (D12), and each of the cooling medium through holes (H2) connects the cooling medium inlet cavity (D11) and the cooling medium guide cavity (D12).

6. The cooling nozzle structure according to claim 5, characterized in that: The cooling nozzle assembly (10) further comprises a combustion chamber connecting ring (14), wherein the combustion chamber connecting ring (14) is provided with a second nozzle portion (C2) penetrating along the axial direction of the cooling nozzle assembly (10); The combustion chamber connecting ring (14) is connected to the axial side of the nozzle body (13) away from the nozzle housing (11), and the second nozzle portion (C2) is connected to the first nozzle portion (C1) to form the nozzle (C).

7. The cooling nozzle structure according to claim 6, characterized in that: The nozzle housing (11), the nozzle guide ring (12), the nozzle body (13) and the combustion chamber connecting ring (14) are arranged to be detachably connected.

8. The cooling nozzle structure according to claim 5, characterized in that: The cooling nozzle assembly (10) further comprises a first sealing ring (15) and a second sealing ring (16); The first sealing ring (15) and the second sealing ring (16) are both sandwiched between the nozzle housing (11) and the nozzle body (13), and are respectively located at two axial ends of the annular cavity.

9. A gas generator, characterized in that: It comprises a combustion chamber structure (200), an atomizing nozzle (300), an igniter (400), and a cooling nozzle structure (100) according to any one of claims 1 to 8; A combustion chamber (R) is formed in the combustion chamber structure (200); the atomizing nozzle (300) and the cooling nozzle structure (100) are respectively arranged at two axial ends of the combustion chamber structure (200); and the nozzle (C) is connected to the combustion chamber (R); The igniter (400) is disposed on the peripheral wall of the combustion chamber structure (200) and is arranged close to the atomizing nozzle (300), and is used to ignite the atomized fuel sprayed from the atomizing nozzle (300) into the combustion chamber (R).

10. The gas generator according to claim 9, characterized in that: It also includes a sensor (500), wherein the sensor (500) is arranged on the combustion chamber structure (200) to detect the pressure and temperature in the combustion chamber (R).

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