Large-flow rectifying device of rocket engine and large-flow rectifying grid of thrust chamber
By designing a large flow rectifier gate of the thrust chamber with an inner concave section and an outer edge turning section in the rocket engine, the problem of uneven flow velocity and total pressure distribution in the gas bend flow field is solved, the uniformity of the total pressure distribution of the gas and the uniform distribution of the propellant mass is achieved, and the performance of the thrust chamber is improved.
Patent Information
- Application Number
- CN202510431859.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-08
- Publication Date
- 2025-06-17
AI Technical Summary
In the liquid oxygen kerosene re-combustion cycle engine, the gas flow velocity and total pressure in the flow field of the gas bent pipe are unevenly distributed, resulting in uneven distribution of propellant mass and mixing ratios, which in turn reduces the performance of the thrust chamber and may stimulate unstable combustion.
A large flow rectifier gate for thrust chamber of rocket engines is designed, including an inner concave section and an outer edge turning section. A number of through holes with equal apertures are arranged on the inner concave section. The through holes are symmetrically distributed, with neat structures, and the number of holes increases in sequence from the inside to the outside. The penetration rate of the rectifier gate is between 30% and 40%, and an oxidation-resistant high-temperature alloy material is used.
Through the design of the rectifier gate, the uniformity of the total pressure distribution of the gas is significantly improved, the uniform distribution of propellant mass and mixing ratio is achieved, the performance of the thrust chamber is improved, and the problem of low gas flow rate in the gas bend area is avoided.
Smart Images
Figure CN120159654A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of rocket engines, relates to a staged combustion cycle engine with liquid oxygen and kerosene, and particularly relates to a large-flow rectifying device for a rocket engine and a large-flow rectifying grid for a thrust chamber. Background Art
[0002] The staged combustion cycle engine with liquid oxygen and kerosene uses a gas generator to generate gas, which drives a turbine and then enters an injector through a gas elbow to participate in combustion. There are pressure gradients, "secondary flows" and vortices in the flow field of the gas in the gas elbow. The gas flow velocity and total pressure distribution are uneven in the central area and the edge area of the flow cross-section, resulting in uneven distribution of the mass and mixing ratio of the propellants entering the injector, thereby reducing the performance of the thrust chamber and possibly triggering unstable combustion. Therefore, setting a rectifying device at the elbow outlet can greatly improve the total pressure uniformity of the gas.
[0003] The oxygen-rich gas flow of the new generation of large-thrust liquid oxygen and kerosene engines has increased significantly, and the flow field in the gas elbow is more complex, with extremely uneven flow velocity and total pressure distribution. Therefore, a rectifying grid is needed to balance the total pressure distribution of the gas while avoiding excessive total pressure loss. Summary of the Invention
[0004] Aiming at the deficiencies of the existing technology, the purpose of the present invention is to provide a large-flow rectifying device for a rocket engine and a large-flow rectifying grid for a thrust chamber to solve the technical problem of uneven gas flow velocity and total pressure distribution in the flow field of the gas elbow in the existing technology.
[0005] To solve the above technical problems, the present invention is implemented by adopting the following technical solutions:
[0006] A large-flow rectifying grid for a rocket engine thrust chamber, the rectifying grid includes a concave section, and an outer edge turning section is coaxially arranged on the outer edge of the concave section.
[0007] A plurality of through holes with equal apertures are opened on the concave section. The through holes include a central through hole opened with the center point of the concave section as the center and a plurality of outer through holes symmetrically distributed with the central through hole as the center. The plurality of outer through holes are evenly distributed outward in a concentric circle manner with the central through hole as the center, and the central axes of all the through holes intersect at the center point of the concave section.
[0008] The present invention also has the following technical features:
[0009] The number of layers of the through holes of the through holes increases sequentially from the center point of the concave section outward. The central through hole is the first layer, and the number of through holes on the through hole layer of the outer through holes increases by 6(n - 1), where n is the number of layers of the through holes of the through holes, and n > 1.
[0010] The penetration rate of the rectifying grid is between 30% and 40%.
[0011] The turning angle of the outer edge turning section is between 20° and 40°.
[0012] The present invention also protects a large-flow rectifying device for a rocket engine, which includes a gas bend pipe. The gas bend is connected to an injector, and a rectifying grid is arranged at the connection position between the gas bend pipe and the injector. The rectifying grid adopts the large-flow rectifying grid for the thrust chamber of the rocket engine described in any one of the above.
[0013] The outer edge turning section is fixedly connected to the inner wall joints of the gas bend pipe and the injector, and the area enclosed by the outer edge turning section and the inner wall surface of the gas bend pipe forms a recirculation zone.
[0014] The outer edge turning section is integrally arranged with a hollow frustum base. The hollow frustum base is located below the concave section, and the concave section exactly corresponds to the hollow part of the hollow frustum base.
[0015] Both the rectifying grid and the gas bend pipe are made of oxidation-resistant high-temperature alloy materials.
[0016] Compared with the prior art, the present invention has the following technical effects:
[0017] (Ⅰ) For the large-flow rectifying grid for the thrust chamber of the rocket engine proposed by the present invention, the through holes with equal apertures are evenly distributed in a concentric circle pattern in the concave section of the rectifying grid. The through holes are symmetrically radially distributed and have a neat structure, and the number of holes increases sequentially from the inside to the outside, greatly improving the uniformity of the total gas pressure distribution and effectively equalizing the gas; the recirculation zone formed by the area enclosed by the outer edge turning section of the rectifying grid and the gas bend pipe can increase the gas flow velocity at the edge area of the gas bend pipe, solving the technical problem of uneven gas flow velocity.
[0018] (Ⅱ) For the large-flow rectifying grid for the thrust chamber of the rocket engine proposed by the present invention, the penetration rate of the rectifying grid is 30% - 40%, which can ensure the uniform effect of the gas and reduce the total gas pressure loss.
[0019] (Ⅲ) For the large-flow rectifying grid for the thrust chamber of the rocket engine proposed by the present invention, the rectifying grid adopts oxidation-resistant high-temperature alloy, which can avoid the ablation of the rectifying grid in an oxygen-rich high-temperature environment. Description of the Drawings
[0020] Figure 1 It is a top view structural schematic diagram of the large-flow rectifying grid for the thrust chamber of the rocket engine.
[0021] Figure 2 It is a sectional structural schematic diagram at A-A of the large-flow rectifying grid for the thrust chamber of the rocket engine.
[0022] Figure 3 It is an overall sectional structural schematic diagram of the large-flow rectifying device for the rocket engine.
[0023] The meanings of the reference numerals in the figure are as follows: 1 - rectifying grid, 2 - gas elbow, 3 - injector, 4 - recirculation zone, 5 - hollow frustum base.
[0024] 101 - concave section, 102 - outer edge turning section, 103 - through hole.
[0025] 10101 - central through hole, 10102 - outer through hole.
[0026] The specific content of the present invention will be further explained in detail below in conjunction with embodiments. Specific Embodiments
[0027] It should be noted that the equipment and components used in the present invention, unless otherwise specified, are all the equipment and components known in the prior art.
[0028] In compliance with the above technical solutions, specific embodiments of the present invention are given below. It should be noted that the present invention is not limited to the following specific embodiments, and all equivalent transformations made on the basis of the technical solutions of this application fall within the protection scope of the present invention.
[0029] Embodiment 1:
[0030] This embodiment provides a large-flow rectifying grid for a rocket engine thrust chamber, as Figure 1 and Figure 2 shown. The rectifying grid 1 includes a concave section 10101, and the outer edge of the concave section 10101 is coaxially provided with an outer edge turning section 10102.
[0031] As Figure 1 and Figure 2 shown, a plurality of through holes 103 with equal apertures are opened on the concave section 10101. The through holes 10103 include a central through hole 10101 opened with the center point of the concave section 10101 as the center and a plurality of outer through holes 10102 symmetrically distributed with the central through hole 10101 as the center. The plurality of outer through holes 10102 are evenly distributed in a concentric circle pattern outward with the central through hole 10101 as the center, and the central axes of all the through holes 103 intersect at the center point of the concave section 101.
[0032] As a preferred solution of this embodiment, as Figure 1 shown, the number of layers of the through holes 103 increases sequentially from the center point of the concave section 101 outward. The central through hole 10101 is the first layer, and the number of through holes on the through hole layer of the outer through hole 10102 increases by 6(n - 1), where n is the number of layers of the through holes 103, and n > 1.
[0033] As a preferred solution of this embodiment, the penetration rate of the rectifying grid 1 is between 30% and 40%.
[0034] As a preferred solution of this embodiment, the turning angle of the outer edge turning section 102 is between 20° and 40°.
[0035] Embodiment 2:
[0036] This embodiment provides a large-flow rectifying device for a rocket engine, including a gas elbow 2. As Figure 3 shown, the gas elbow 2 is connected to the injector 3, and a rectifying grid 1 is arranged at the connection position of the gas elbow 2 and the injector 3. The rectifying grid 1 adopts the large-flow rectifying grid for the thrust chamber of the rocket engine given in Embodiment 1.
[0037] As Figure 3 shown, the outer edge turning section 102 is fixedly connected to the inner wall joints of the gas elbow 2 and the injector 3, and the area surrounded by the outer edge turning section 102 and the inner wall surface of the gas elbow 2 forms a recirculation zone 4.
[0038] As a preferred solution of this embodiment, as Figure 3 shown, the outer edge turning section 102 is integrally arranged with the hollow frustum base 5. The hollow frustum base 5 is located below the concave section 101, and the concave section 101 exactly corresponds to the hollow part of the hollow frustum base 5.
[0039] As a preferred solution of this embodiment, both the rectifying grid 1 and the gas elbow 2 are made of an oxidation-resistant high-temperature alloy material, which can prevent the rectifying grid 1 from being ablated in an oxygen-rich high-temperature environment.
[0040] The working process of the large-flow rectifying device for the rocket engine in this embodiment is as follows: When the rocket engine is working, the gas passes through the rectifying grid 1 from the gas elbow 2 and enters the injector 3. After the gas with complex flow passes through the central through holes 10101 and outer through holes 10102 uniformly distributed in the concave section 101 of the rectifying grid 1, the pressure distribution uniformity is greatly improved, and the mass and mixing ratio distribution of the propellant participating in combustion are made uniform. The gas flow velocity in the central area of the gas elbow 2 is relatively high, while the gas flow velocity in the edge area is relatively low. Therefore, an outer edge turning section 102 is arranged on the rectifying grid 1, and the area surrounded by the outer edge turning section 102 and the inner wall surface of the gas elbow 2 forms a recirculation zone 4. The recirculation zone 4 can increase the gas flow velocity in the edge area of the gas elbow 2, and then mix with the gas in the central area of the gas elbow 2 and pass through the rectifying grid 1 to improve the gas uniformity.
Claims
1. A large flow rectifier grid for a rocket engine thrust chamber, characterized in that: The rectifying grid (1) comprises an inner concave section (101), and an outer edge turning section (102) is coaxially arranged on the outer edge of the inner concave section (101); The concave section (101) is provided with a plurality of through holes (103) of equal aperture, wherein the through holes (103) include a central through hole (10101) formed with the center point of the concave section (101) as the center of the circle and a plurality of outer through holes (10102) symmetrically distributed with the central through hole (10101) as the center, wherein the plurality of outer through holes (10102) are uniformly arranged outward in a concentric circle manner with the central through hole (10101) as the center, and the central axes of all the through holes (103) intersect at the center point of the concave section (101).
2. The rocket engine thrust chamber high flow rectifier grid as claimed in claim 1, characterized in that: The number of through hole layers of the through hole (103) increases from the center point of the inner concave section (102) outwards, the central through hole (10101) is the first layer, and the number of through holes on the through hole layer of the outer through hole (10102) increases by 6(n-1), n is the number of through hole layers of the through hole (103), and n>1.
3. The rocket engine thrust chamber high flow rectifier grid as claimed in claim 1, characterized in that: The transmittance of the rectifying grid (1) is between 30% and 40%.
4. The rocket engine thrust chamber high flow rectifier grid as claimed in claim 1, characterized in that: The turning angle of the outer edge turning section (102) is between 20° and 40°.
5. A rocket engine high flow rectifying device, comprising a gas elbow (2), the gas elbow (2) being connected to an injector (3), a rectifying grid (1) being arranged at the position where the gas elbow (2) and the injector (3) are connected, characterized in that: The rectifier grid (1) adopts the rocket engine thrust chamber large flow rectifier grid as claimed in any one of claims 1 to 4; The outer edge turning section (102) is fixedly connected to the inner wall connection of the gas elbow (2) and the injector (3), and the area enclosed by the outer edge turning section (102) and the inner wall surface of the gas elbow (2) forms a reflow zone (4).
6. The rocket engine high flow rectifying device as claimed in claim 5, characterized in that: The outer edge turning section (102) is integrated with the hollow truncated cone base (5), the hollow truncated cone base (5) is located below the inner concave section (101), and the inner concave section (102) corresponds to the hollow part of the hollow truncated cone base (5).
7. The rocket engine high flow rectifying device as claimed in claim 5, characterized in that: The rectifier grid (1) and the gas elbow (2) are both made of oxidation-resistant high-temperature alloy materials.