Liquid rocket engine thrust chamber collector

Abstract

The invention discloses a liquid rocket engine thrust chamber collector which comprises an arc-shaped wall face and a perforated rib plate. The perforated rib plate is connected with the opening of the arc-shaped wall surface to form a collector cavity A; and a boss communicated with the collector cavity A is arranged on the arc-shaped wall surface. According to the liquid rocket engine thrust chamber collector, the variable cross-section structure with the flow adjusting function is adopted, so that the requirement for uniform flow distribution of a cooling channel of a liquid rocket engine thrust chamber is met, and the inner wall overheating and ablation risks caused by uneven flow distribution of the cooling channel of the thrust chamber are reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid rocket engines, and in particular relates to a thrust chamber collector of a liquid rocket engine. Background Art

[0002] The gas temperature in the thrust chamber of a liquid rocket engine can reach over 3000K, and the combustion chamber has high pressure and fast gas flow rate. High temperature, high pressure and high speed gas will generate huge heat flow on the wall surface, so effective and reliable thermal protection measures must be taken for the thrust chamber. Regenerative cooling is one of the important thermal protection methods for the thrust chamber of a liquid rocket engine. The coolant flows from the collector into the cooling jacket and exchanges heat with the wall surface. The coolant temperature itself rises, and the wall surface temperature is controlled within a reasonable range. The coolant coming out of the cooling jacket will be collected in the collector and then flow out. When designing the regenerative cooling structure of the thrust chamber, it is generally assumed that the coolant flow rate of each cooling channel is the same, and heat transfer calculations are performed on a single cooling channel to determine the appropriate channel structure. In fact, there are hundreds of cooling channels in the thrust chamber. Due to the limitations of the thrust chamber and its collector structure, the coolant flow rate of each channel is different. The uneven distribution of the flow rate leads to different cooling capacities of each channel, which in turn leads to different temperatures in different areas of the inner wall. In severe cases, the inner wall may overheat or even ablate, threatening the reliable operation of the thrust chamber. Studies have shown that the uniformity of pressure distribution in the collector has a certain relationship with the uniformity of flow distribution in the cooling channel. In order to meet the uniformity requirement of coolant flow distribution in the thrust chamber, it is necessary to design a collector structure with flow regulation function. Summary of the invention

[0003] The technology of the present invention solves the problem: Overcoming the shortcomings of the prior art, providing a liquid rocket engine thrust chamber collector, adopting a variable cross-section structure with a flow regulation function to meet the demand for uniform flow distribution in the thrust chamber cooling channel of the liquid rocket engine, and reducing the risk of inner wall overheating and ablation caused by uneven flow distribution in the thrust chamber cooling channel.

[0004] In order to solve the above technical problems, the present invention discloses a liquid rocket engine thrust chamber collector, comprising: an arc-shaped wall surface and a perforated rib plate; wherein the perforated rib plate is connected to the opening of the arc-shaped wall surface to form a collector cavity A; a boss connected to the collector cavity A is arranged on the arc-shaped wall surface.

[0005] In the above-mentioned liquid rocket engine thrust chamber collector, the boss serves as the outlet of the liquid rocket engine thrust chamber collector and is used to eliminate the pressure unevenness caused by the local fluid vortex.

[0006] In the above-mentioned liquid rocket engine thrust chamber collector, the boss is a structure with a variable cross-section.

[0007] In the above-mentioned liquid rocket engine thrust chamber collector, the side of the boss away from the arc-shaped wall is a circular hole, and the junction between the boss and the arc-shaped wall is an elliptical hole; the cross-section of the boss along the direction from the circular hole to the elliptical hole increases uniformly.

[0008] In the above-mentioned liquid rocket engine thrust chamber collector, the collector cavity A is a variable cross-section structure.

[0009] In the above-mentioned liquid rocket engine thrust chamber collector, the flow cross-section area of ​​the collector cavity A at the position of the boss is the largest; the flow cross-section area of ​​the collector cavity A at the position 180° with the boss is the smallest; the flow cross-section area of ​​the collector cavity A along the direction from flow cross-section to flow cross-section decreases uniformly.

[0010] In the above-mentioned liquid rocket engine thrust chamber collector, a plurality of through holes are provided on the perforated rib plate; wherein the through holes are symmetrically arranged on the perforated rib plate with the straight line where the center of the boss is located as the symmetry line.

[0011] In the above-mentioned liquid rocket engine thrust chamber collector, the aperture of the through hole gradually increases in the direction away from the boss.

[0012] In the above-mentioned liquid rocket engine thrust chamber collector, the liquid rocket engine thrust chamber collector is a symmetrical structure with the straight line where the center of the boss is located as the symmetry line.

[0013] In the above-mentioned liquid rocket engine thrust chamber collector, the liquid rocket engine thrust chamber collector is installed on the combustion chamber; a collector cavity B is formed between the perforated rib plate and the combustion chamber, and the collector cavity B and the collector cavity A together form a double cavity structure.

[0014] The present invention has the following advantages:

[0015] (1) The present invention discloses a liquid rocket engine thrust chamber collector having a gradually changing flow area, which can greatly reduce the uneven pressure distribution in the collector and thus improve the uneven flow in the channel.

[0016] (2) The present invention discloses a thrust chamber collector of a liquid rocket engine. The perforated rib plate naturally divides the collector into two chambers, further improving uniformity. At the same time, the perforated rib plate and the arc-shaped wall are integrally formed to improve the strength of the collector, while reducing welds and improving reliability.

[0017] (3) The present invention discloses a thrust chamber collector of a liquid rocket engine, wherein the flow cross section at the outlet is a gradual structure, and the boss and the arc-shaped wall surface achieve a smooth transition, thereby reducing local vortices and improving local flow distribution. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1is a three-dimensional view of a thrust chamber collector of a liquid rocket engine in an embodiment of the present invention;

[0019] Figure 2 is a cross-sectional view of a thrust chamber collector of a liquid rocket engine in an embodiment of the present invention;

[0020] Figure 3 is a front view of a thrust chamber collector of a liquid rocket engine in an embodiment of the present invention;

[0021] Figure 4 is a rear view of a thrust chamber collector of a liquid rocket engine in an embodiment of the present invention;

[0022] Figure 5 is a top view of a thrust chamber collector of a liquid rocket engine in an embodiment of the present invention;

[0023] Figure 6 It is a schematic diagram of the installation of a thrust chamber collector and a combustion chamber of a liquid rocket engine in an embodiment of the present invention. DETAILED DESCRIPTION

[0024] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0025] One of the core ideas of the present invention is to design a variable cross-section collector with flow regulation function, the pressure distribution in the cavity is more uniform, which is conducive to the uniform distribution of the flow in the cooling channel. The structure can be formed in an integrated manner, thereby improving the structural strength and reliability.

[0026] Reference Figures 1 to 5 In this embodiment, the thrust chamber collector of the liquid rocket engine includes: an arc-shaped wall surface 1 and a perforated rib plate 2. The perforated rib plate 2 is connected to the opening of the arc-shaped wall surface 1 to form a collector cavity A10; a boss 3 connected to the collector cavity A10 is provided on the arc-shaped wall surface 1. The perforated rib plate 2 is connected to the opening of the arc-shaped wall surface 1 to improve the strength.

[0027] In this embodiment, the boss 3 is used as the outlet of the thrust chamber collector of the liquid rocket engine, and is mainly used to eliminate the uneven pressure caused by the local fluid vortex. The boss 3 is a variable cross-section structure: the side of the boss 3 away from the arc-shaped wall surface 1 is a circular hole 7, and the part where the boss 3 and the arc-shaped wall surface 1 meet is an elliptical hole 8; the cross-section of the boss 3 along the direction from the circular hole 7 to the elliptical hole 8 increases uniformly.

[0028] In this embodiment, the collector cavity A10 is a variable cross-section structure: the area of ​​the flow cross section 5 of the collector cavity A10 at the position of the boss 3 is the largest; the area of ​​the flow cross section 4 of the collector cavity A10 at a position 180° from the boss 3 is the smallest; the area of ​​the flow cross section of the collector cavity A10 along the direction from the flow cross section 5 to the flow cross section 4 is uniformly reduced. This collector with a variable flow cross section has the function of regulating the pressure inside the collector, which is conducive to the uniform distribution of the flow.

[0029] In this embodiment, a plurality of through holes 6 are provided on the perforated rib plate 2. The through holes 6 are symmetrically arranged on the perforated rib plate 2 with the straight line where the center of the boss 3 is located as the symmetry line; and the aperture of the through holes 6 gradually increases in the direction away from the boss 3.

[0030] In this embodiment, the thrust chamber collector of the liquid rocket engine is a symmetrical structure with the straight line where the center of the boss 3 is located as the symmetry line.

[0031] In this embodiment, the liquid rocket engine thrust chamber collector is installed on the combustion chamber 9, such as Figure 6 As shown, a collector cavity B11 is formed between the perforated rib plate 2 and the combustion chamber 9. The collector cavity B11 and the collector cavity A10 together form a double-cavity structure. When the fluid flows through the double-cavity structure, it can play a role of secondary flow balancing, further improving the flow uniformity.

[0032] In summary, the present invention discloses a liquid rocket engine thrust chamber collector, which is an annular structure. The cross-sectional area of ​​the fluid flow in the collector is variable, the flow area near the collector outlet is relatively large, and then gradually decreases along the annular direction, and the flow cross-sectional areas on both sides of the outlet are symmetrically distributed. This structure with a gradual flow area change can greatly reduce the uneven pressure distribution in the collector, thereby improving the uneven channel flow. Furthermore, the liquid rocket engine thrust chamber collector is designed with a full-circle perforated rib plate, and based on the additive manufacturing process, the perforated rib plate and the arc-shaped wall can be integrally formed. The aperture of the rib plate with holes is smaller near the boss, and larger near the position 180° from the outlet; there is a collector cavity between the rib plate with holes and the arc-shaped wall. When the collector is installed in the combustion chamber, the rib plate with holes and the combustion chamber structure can form a second collector cavity, realizing the layout of the double collector cavity, and the pressure distribution in the collector can be further adjusted to achieve the purpose of improving the flow distribution in the cooling channel. At the same time, the rib plate with holes can improve the structural strength of the annular collector. Furthermore, the boss and the arc-shaped wall are designed to be a uniformly gradient structure, from an elliptical cross section to a circular cross section, and the elliptical cross section and the arc-shaped wall ring have a smooth transition. After the circular outlet, a flange and other structures connected to the pipeline can be set according to needs.

[0033] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0034] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A liquid rocket engine thrust chamber collector, characterized in that: include: A circular arc wall surface (1) and a perforated rib plate (2); wherein the perforated rib plate (2) is connected to the opening of the circular arc wall surface (1) to form a collector cavity A (10); and a boss (3) connected to the collector cavity A (10) is provided on the circular arc wall surface (1).

2. The liquid rocket engine thrust chamber collector according to claim 1, characterized in that: The boss (3) serves as an outlet of a thrust chamber collector of a liquid rocket engine and is used to eliminate uneven pressure caused by a local fluid vortex.

3. The liquid rocket engine thrust chamber collector according to claim 1, characterized in that: The boss (3) is a structure with a variable cross-section.

4. The liquid rocket engine thrust chamber collector according to claim 3, characterized in that: The side of the boss (3) away from the arc-shaped wall surface (1) is a circular hole (7), and the junction between the boss (3) and the arc-shaped wall surface (1) is an elliptical hole (8); the cross section of the boss (3) along the direction from the circular hole (7) to the elliptical hole (8) increases uniformly.

5. The liquid rocket engine thrust chamber collector according to claim 1, characterized in that: The collector cavity A (10) is a structure with a variable cross-section.

6. The liquid rocket engine thrust chamber collector according to claim 5, characterized in that: The flow cross section (5) of the collector cavity A (10) at the position where the boss (3) is located has the largest area; the flow cross section (4) of the collector cavity A (10) at a position 180 degrees from the boss (3) has the smallest area; and the flow cross section area of ​​the collector cavity A (10) along the direction from the flow cross section (5) to the flow cross section (4) decreases uniformly.

7. The liquid rocket engine thrust chamber collector according to claim 1, characterized in that: A plurality of through holes (6) are provided on the perforated rib plate (2); wherein the through holes (6) are symmetrically arranged on the perforated rib plate (2) with the straight line where the center of the boss (3) is located as the symmetry line.

8. The liquid rocket engine thrust chamber collector according to claim 7, characterized in that: The diameter of the through hole (6) gradually increases in a direction away from the boss (3).

9. The liquid rocket engine thrust chamber collector according to claim 1, characterized in that: The thrust chamber collector of a liquid rocket engine is a symmetrical structure with the straight line where the center of the boss (3) is located as the symmetry line.

10. The liquid rocket engine thrust chamber collector according to claim 1, characterized in that: A thrust chamber collector of a liquid rocket engine is installed on a combustion chamber (9); a collector cavity B (11) is formed between a perforated rib plate (2) and the combustion chamber (9); the collector cavity B (11) and the collector cavity A (10) together form a double cavity structure.

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