Thrust chamber oxygen cavity top cover light flow equalizing grating structure

Abstract

The invention discloses a thrust chamber oxygen cavity top cover light flow equalizing fence structure. The thrust chamber oxygen cavity top cover light flow equalizing fence structure comprises a herringbone flow divider, an annular flow equalizing fence and radial flow guide partition plates. The annular flow equalizing fence is of an annular plate-shaped structure provided with a plurality of through holes. The herringbone flow divider is arranged at the oxygen inlet, the lower end of the herringbone flow divider is connected with the annular flow equalizing fence, the upper end of the herringbone flow divider is connected with the dome of the inner cavity of the oxygen cavity top cover, and the herringbone flow divider is used for dividing liquid oxygen entering from the oxygen inlet to the two sides; one end of each radial flow guide partition plate is connected with the inner side edge of the annular flow equalizing fence, and the other end of each radial flow guide partition plate is connected with the oxygen cavity top cover inner cavity dome; the device can be used for uniformly distributing the flow of the head oxygen nozzle of the low-temperature liquid rocket engine, and has wide application prospects.

Description

Technical Field

[0001] This invention relates to a lightweight flow equalization structure for the oxygen chamber top cover of a thrust chamber, belonging to the field of flow equalization technology for oxygen chambers in liquid rocket engines. Background Technology

[0002] Cryogenic liquid rocket engines use liquid fuel and liquid oxygen as propellants and are one of the mainstream propulsion technologies used in launch vehicles worldwide today. When a liquid rocket engine is working, the fuel and oxidizer liquid oxygen are distributed to the nozzle through the fuel head chamber and oxygen head chamber, respectively. After the fuel and oxygen mix in the nozzle exit area, they burn, converting chemical energy into thermal energy and pressure potential energy. The combustion products are then squeezed out through the throat and nozzle to generate thrust.

[0003] In typical liquid rocket engines, liquid oxygen is pressurized by a turbopump and enters the oxygen head chamber through a centralized inlet. Current liquid rocket engines often have hundreds of nozzles in their head section. The uniformity of oxygen nozzle flow distribution directly affects the mixing ratio of the injection unit, the combustion state within the combustion chamber, and the engine's performance stability. Therefore, structures such as flow equalization grids must be designed into the oxygen head chamber to ensure uniform oxygen nozzle flow distribution. However, traditional flow equalization grids covering the entire oxygen head chamber are heavy and have poor uniformity, easily leading to significant deviations in the local mixing ratio from the design value, causing nozzle or thrust chamber ablation. Summary of the Invention

[0004] The purpose of this invention is to overcome the aforementioned shortcomings and provide a lightweight flow equalization grid structure for the oxygen chamber top cover of the thrust chamber. This solves the problems of heavy weight and uneven flow distribution in existing flow equalization grid structures, and avoids the problem of easy ablation of the nozzle and body due to excessively high local mixing ratios. This invention can be used for uniform flow distribution in the oxygen nozzle of the cryogenic liquid rocket engine head, and has broad application prospects.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solution: A lightweight flow equalization grid structure for the oxygen chamber top cover of a thrust chamber is disposed inside the oxygen chamber top cover, including a herringbone-shaped flow divider, an annular flow equalization grid, and a radial flow guide baffle. The annular flow equalization grid is an annular plate-shaped structure with several through holes; The herringbone-shaped diverter is located at the oxygen inlet. The lower end of the herringbone-shaped diverter is connected to the inner edge of the annular flow equalization grid, and the upper end of the herringbone-shaped diverter is connected to the dome of the inner cavity of the oxygen chamber top cover. The herringbone-shaped diverter is used to divert the liquid oxygen entering from the oxygen inlet to both sides. One end of the radial flow guide baffle is connected to the inner edge of the annular flow equalization grid, and the other end is connected to the dome of the oxygen chamber top cover. Several radial flow guide baffles are evenly distributed, with two radial flow guide baffles symmetrically distributed on both sides of the oxygen inlet.

[0006] Furthermore, let the width of the annular flow equalization grid be d, and the radius of the inner cavity of the oxygen chamber top cover be r, satisfying: d=30%r~50%r.

[0007] Furthermore, the annular flow equalization grid includes a region without through holes and a region with through holes; The area without through holes is located at the oxygen inlet and is an approximately triangular area with a circular arc base. The inner edge of the annular flow equalization grid connected to the large end of the herringbone splitter is the base of the approximately triangular area. Areas other than those without through holes are areas with through holes.

[0008] Furthermore, the inner edge of the annular flow equalization grid is provided with a bending structure towards the injector, and the height of the bending structure is 1.5 to 2.5 times the thickness of the annular flow equalization grid.

[0009] Furthermore, there are 5 radial flow guide baffles.

[0010] Furthermore, let A and B be the connection points between the two radial flow guide baffles located on both sides of the oxygen inlet and the inner edge of the annular flow equalization grid, respectively, and let C and D be the connection points between the large end of the herringbone splitter and the inner edge of the annular flow equalization grid, respectively. Then the angle corresponding to the arc CD is 40% to 60% of the angle corresponding to the arc AB.

[0011] Furthermore, the radial flow guide baffle includes a baffle and a reinforcing fixing structure; The partition is an approximately triangular flat plate structure. The upper part of the partition is connected to the dome of the oxygen chamber top cover, and the other two sides are connected to the inner edge of the annular flow equalization grid through a reinforced fixing structure.

[0012] Furthermore, the diaphragm reinforcement structure includes columns and spoke-shaped suspension cables; The bottom of the column and the outer side of the spoke-shaped suspension cable are connected to the inner edge of the annular flow equalization grid. The top of the column is connected to the dome of the oxygen chamber top cover. The inner side of the spoke-shaped suspension cable is connected to the edge of the inwardly protruding platform of the oxygen chamber top cover.

[0013] Furthermore, the thickness of the partition is 0.5~2mm.

[0014] Compared with the prior art, the present invention has at least one of the following advantages: (1) In view of the need for uniform flow distribution of oxygen nozzles in the head of cryogenic liquid rocket engines, the present invention adopts a lightweight flow equalization structure, which helps to improve the thrust-to-mass ratio of the engine. (2) The present invention is equipped with a herringbone-shaped diverter, which can evenly divert liquid oxygen from the centralized inlet to both sides, preventing the problem of excessive flow rate of the nozzle directly opposite the inlet caused by direct scouring of the inlet flow. (3) By designing an annular flow equalization grid structure that does not cover the entire oxygen chamber, the present invention can prevent the oxygen flow rate of the nozzle below from being too large, and achieve weight reduction of the flow equalization grid structure while ensuring the flow equalization effect. (4) By setting a radial flow guide baffle, the present invention can prevent the generation of swirling flow in the inner open area, thereby preventing the difference in flow rate between the inner and outer ring nozzles due to the pressure difference of the swirling flow. Attached Figure Description

[0015] Figure 1 A diagram of the thrust chamber head equipped with a lightweight flow equalization structure top cover; Figure 2 The top cover is provided with a lightweight flow equalization structure for the oxygen chamber top cover of the thrust chamber. (a) is a front view, (b) is a top view, (c) is a partial view showing the connection relationship between the partition and the column, and (d) is a partial view showing the cross-sectional shape of the spoke-shaped suspension cable. Wherein: 1-Liquid oxygen top cover; 2-Injector; 3-Fuel collector; 4-Hinge-shaped flow guide; 5-Annular flow equalization grid; 6-Radial flow guide baffle; 7-Baffle; 8-Column; 9-Spoke-shaped suspension cable. Detailed Implementation

[0016] The features and advantages of the present invention will become clearer and more explicit from the following detailed description.

[0017] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments. Although various aspects of embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated otherwise.

[0018] A lightweight flow equalization structure for the oxygen chamber top cover of a thrust chamber comprises a herringbone-shaped flow divider, an annular flow equalization grid, and a radial flow guide baffle in the central area, which are fixedly installed inside the oxygen chamber top cover at the engine head as flow equalization structures.

[0019] The herringbone-shaped distributor faces the oxygen inlet and serves to evenly distribute liquid oxygen from the central inlet to both sides. Its bottom is connected to the annular flow equalization grid, and its top is connected to the dome of the inner cavity of the top cover.

[0020] The annular flow equalization grid does not cover the entire flow area of ​​the oxygen cavity; its width occupies only about 40% of the inner cavity radius, and the remaining part inside is in an open flow state.

[0021] No through holes are provided in the approximately triangular area with the large end of the herringbone splitter as the base, directly opposite the liquid oxygen inlet and facing the annular flow equalization grid.

[0022] The inner edge of the annular flow equalization grid is designed with a downward bending structure, and the total bending height is about twice the thickness of the flow equalization grid substrate.

[0023] The inner area not occupied by the annular flow equalization grid is provided with 5 (or more) radial flow guide baffles.

[0024] Five (or several) radial flow guide baffles are evenly distributed around the circumference, with two symmetrically distributed on both sides of the oxygen inlet. There is a distance between the radial flow guide baffles on both sides of the inlet and the large end of the herringbone splitter. The arc angle of the herringbone separator accounts for about 50% of the angle between the two.

[0025] The radial flow guide baffle consists of a thinner inner baffle and a reinforcing frame formed by columns and bottom spoke-shaped suspension cables. To reduce weight, the thickness of the baffle is 0.5~2mm, sufficient to separate the fluid zones. The columns and bottom spoke-shaped suspension cables together form a reinforced and fixed structure for the baffle and the annular flow equalization grid.

[0026] The bottom of the column and the outer side of the spoke-shaped suspension cable are connected to the edge of the annular flow equalization grid. The top of the column is connected to the dome inside the top cover. The inner side of the spoke-shaped suspension cable is connected to the edge of the first platform protruding inward from the top cover. All connections are provided with rounded corner transitions.

[0027] This invention discloses a lightweight flow equalization structure for the oxygen chamber top cover of a thrust chamber. Addressing the need for uniform flow distribution of oxygen nozzles in the head of cryogenic liquid rocket engines, the lightweight flow equalization structure helps improve the thrust-to-mass ratio of the engine.

[0028] The herringbone-shaped diverter of this invention faces the oxygen inlet and serves to evenly distribute liquid oxygen from the centralized inlet to both sides. Its bottom is connected to the annular flow equalization grid and its top is connected to the dome of the inner cavity of the top cover. On the one hand, it can realize the structural fixation of the diverter itself, and on the other hand, it also provides a suspension cable-like fixation function for the inner edge of the annular flow equalization grid.

[0029] The annular flow equalization grid does not cover the entire flow area of ​​the oxygen cavity; its width occupies only about 40% of the inner cavity radius, and the remaining part inside is in an open flow state. This allows for weight reduction of the flow equalization grid structure while ensuring the flow equalization effect.

[0030] The annular flow equalization grid, facing the liquid oxygen inlet, has no through holes in the approximately triangular area with the large end of the herringbone-shaped distributor as the base. This helps to prevent excessive oxygen flow to the nozzles below it.

[0031] The inner edge of the annular flow equalization grid is designed with a downward bending structure. The total bending height is about twice the thickness of the flow equalization grid substrate, which can strengthen the flow equalization grid structure.

[0032] The inner area not occupied by the annular flow equalization grid is equipped with 5 radial flow guide baffles to prevent swirling flow in the open inner area, thereby preventing the difference in flow rate between the inner and outer ring nozzles due to the pressure difference of the swirling flow.

[0033] Five (or more) radial flow guide baffles are evenly distributed around the circumference, with two symmetrically distributed on both sides of the oxygen inlet. There is a distance between the radial flow guide baffles on both sides of the inlet and the large end of the herringbone splitter. The arc angle of the herringbone separator accounts for about 50% of the angle between the two, which can prevent the flow rate in the area directly opposite the inlet from being too large.

[0034] The radial flow guide baffle consists of a thinner inner baffle and a reinforcing frame formed by columns and bottom spoke-shaped suspension cables. To reduce weight, the thickness of the baffle is 0.5~2mm, sufficient to separate the fluid zones. The columns and bottom spoke-shaped suspension cables together form a reinforced and fixed structure for the baffle and the annular flow equalization grid.

[0035] The bottom of the column and the outer side of the spoke-shaped suspension cable are connected to the edge of the annular flow equalization grid. The top of the column is connected to the dome inside the top cover. The inner side of the spoke-shaped suspension cable is connected to the edge of the first platform protruding inward from the top cover. All connections are provided with rounded corners to avoid stress concentration.

[0036] Example: The purpose of this invention is to provide a lightweight flow equalization structure for the oxygen chamber top cover of a thrust chamber, such as... Figure 1 As shown, the head of a liquid rocket engine consists of an oxygen chamber cap 1, an injector 2, and a fuel collector 3. Figure 2 As shown, a lightweight flow equalization structure for the oxygen chamber top cover of a thrust chamber is provided, wherein a herringbone-shaped flow divider 4, an annular flow equalization grid 5, and a central radial flow guide baffle 6 are fixedly installed inside the oxygen chamber top cover 1 at the engine head as flow equalization structures.

[0037] The herringbone-shaped diverter 4 of this invention faces the oxygen inlet and serves to evenly divert liquid oxygen from the centralized inlet to both sides. Its bottom is connected to the annular flow equalization grid 5 and its top is connected to the dome of the inner cavity of the top cover. On the one hand, it can fix the result of the diverter itself, and on the other hand, it also provides a suspension cable-like fixing function for the inner edge of the annular flow equalization grid.

[0038] The annular flow equalization grid 5 does not cover the entire flow area of ​​the oxygen cavity. Its width only occupies about 40% of the inner cavity radius, and the remaining part inside is in an open flow state. This can reduce the weight of the flow equalization grid structure while ensuring the flow equalization effect.

[0039] The annular flow equalization grid 5, facing the liquid oxygen inlet, has no through holes in the approximately triangular area with the large end of the herringbone-shaped distributor as the base. This can prevent excessive oxygen flow from the nozzle below it.

[0040] The inner edge of the annular flow equalization grid 5 is designed with a downward bending structure. The total bending height is about twice the thickness of the flow equalization grid substrate, which can strengthen the flow equalization grid structure.

[0041] The inner area of ​​the unoccupied annular flow equalization grid 5 is provided with 5 (several) radial flow guide baffles, which can prevent swirling flow in the open inner area, thereby preventing the difference in flow rate between the inner and outer ring nozzles due to the pressure difference of the swirling flow.

[0042] Five (or several) radial flow guide baffles 6 are evenly distributed around the circumference, with two symmetrically distributed on both sides of the oxygen inlet. There is a gap between the radial flow guide baffles 6 on both sides of the inlet and the large end of the herringbone separator 5. The arc angle of the herringbone separator accounts for about 50% of the angle between the two, which can prevent the flow rate in the area directly opposite the inlet from being too large.

[0043] The radial flow guide baffle 6 consists of a thinner inner baffle 7 and a reinforced frame formed by a column 8 and a bottom spoke-shaped suspension cable 9. To reduce weight, the thickness of the baffle 7 is 1~2mm, which is sufficient to separate the fluid areas. The column 8 and the bottom spoke-shaped suspension cable 9 together form a reinforced fixing structure for the baffle 7 and the annular flow equalization grid 5.

[0044] The bottom of the column 8 and the outer side of the spoke-shaped suspension cable 9 are connected to the edge of the annular flow equalization grid 5. The top of the column 8 is connected to the dome of the inner cavity of the top cover. The inner side of the spoke-shaped suspension cable 9 is connected to the edge of the first platform protruding inward from the top cover. All connections are provided with rounded corners to avoid stress concentration.

[0045] Liquid oxygen flows from the oxygen inlet through the annular flow equalization grid 5 to both sides. The liquid oxygen on both sides flows circumferentially along the annular flow equalization grid to the opposite side of the oxygen inlet. During the circumferential flow, the liquid oxygen flows downward from the flow equalization grid holes and is distributed to the nozzles below the annular flow equalization grid. At the same time, when passing through a partition to form a zone, a portion of the liquid oxygen flows to the central open area and flows downward to the nozzles in the central area.

[0046] This invention discloses a lightweight flow equalization structure for the oxygen chamber top cover of a thrust chamber. Addressing the need for uniform flow distribution of oxygen nozzles in the head of cryogenic liquid rocket engines, the lightweight flow equalization structure helps improve the thrust-to-mass ratio of the engine.

[0047] The present invention has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and embodiments of the present invention without departing from the spirit and scope of the invention, and all such modifications and improvements fall within the scope of the present invention. The scope of protection of the present invention is defined by the appended claims.

[0048] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A lightweight flow equalization grid structure for the top cover of the oxygen chamber of a thrust chamber, characterized in that, Located inside the oxygen chamber top cover (1), it includes a herringbone-shaped flow divider (4), an annular flow equalization grid (5), and a radial flow guide baffle (6). The annular flow equalization grid (5) is an annular plate structure with several through holes; The herringbone-shaped diverter (4) is located at the oxygen inlet. The lower end of the herringbone-shaped diverter (4) is connected to the inner edge of the annular flow equalization grid (5), and the upper end of the herringbone-shaped diverter (4) is connected to the dome of the inner cavity of the oxygen chamber top cover (1). The herringbone-shaped diverter (4) is used to divert the liquid oxygen entering from the oxygen inlet to both sides. One end of the radial flow guide baffle (6) is connected to the inner edge of the annular flow equalization grid (5), and the other end is connected to the dome of the oxygen chamber top cover (1). Several radial flow guide baffles (6) are evenly distributed, and two radial flow guide baffles (6) are symmetrically distributed on both sides of the oxygen inlet.

2. The lightweight flow equalization grid structure for the oxygen chamber top cover of the thrust chamber according to claim 1, characterized in that, Let the width of the annular flow equalization grid (5) be d, and the inner radius of the oxygen chamber top cover (1) be r, satisfying: d=30%r~50%r。 3. The lightweight flow equalization grid structure for the thrust chamber oxygen cavity top cover according to claim 1, characterized in that, The annular flow equalization grid (5) includes a region without through holes and a region with through holes; The area without through holes is located at the oxygen inlet and is an approximately triangular area with a circular arc base. The inner edge of the annular flow equalization grid (5) connected to the large end of the herringbone splitter (4) is the base of the approximately triangular area. Areas other than those without through holes are areas with through holes.

4. The lightweight flow equalization grid structure for the oxygen chamber top cover of the thrust chamber according to claim 1, characterized in that, The inner edge of the annular flow equalization grid (5) is provided with a bending structure in the direction of the injector (2), and the height of the bending structure is 1.5 to 2.5 times the thickness of the annular flow equalization grid (5).

5. The lightweight flow equalization grid structure for the oxygen chamber top cover of the thrust chamber according to claim 1, characterized in that, There are 5 radial flow guide baffles (6).

6. A lightweight flow equalization grid structure for the oxygen chamber top cover of a thrust chamber according to claim 1, characterized in that, it is provided with The connection points between the two radial flow guide baffles (6) located on both sides of the oxygen inlet and the inner edge of the annular flow equalization grid (5) are A and B, respectively. The connection points between the large end of the herringbone splitter (4) and the inner edge of the annular flow equalization grid (5) are C and D, respectively. Then the angle corresponding to the arc CD is 40%~60% of the angle corresponding to the arc AB.

7. The lightweight flow equalization grid structure for the oxygen chamber top cover of the thrust chamber according to claim 1, characterized in that, The radial flow guide baffle (6) includes a baffle (7) and a reinforcing fixing structure; The partition (7) is a triangular flat plate structure. The upper side of the partition (7) is connected to the dome of the inner cavity of the oxygen chamber top cover (1), and the other two sides are connected to the inner edge of the annular flow equalization grid (5) through a reinforced fixing structure.

8. The lightweight flow equalization grid structure for the oxygen chamber top cover of the thrust chamber according to claim 7, characterized in that, The diaphragm reinforcement structure includes columns (8) and spoke-shaped suspension cables (9); The bottom of the column (8) and the outer side of the spoke-shaped suspension cable (9) are connected to the inner edge of the annular flow equalization grid (5). The top of the column (8) is connected to the dome of the inner cavity of the oxygen chamber top cover (1). The inner side of the spoke-shaped suspension cable (9) is connected to the inner edge of the platform protruding inward from the oxygen chamber top cover (1).

9. A lightweight flow equalization grid structure for the oxygen chamber top cover of a thrust chamber according to claim 8, characterized in that, The thickness of the partition (7) is 0.5~2mm.

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