A high-uniformity gas rectification structure and an engine

Abstract

The application discloses a high-uniform-flow gas rectification structure and an engine, and aims at solving the problem that the gas channel between a gas generator and a thrust chamber has no rectification effect, the rectification of high-speed and non-uniform flow gas is difficult to meet the uniform flow requirement, and the damping effect on pressure pulsation is weak. The application specifically comprises a rectification duct, a first rectification plate, a second rectification plate and a gas pre-injection cavity. The rectification duct inlet end is coaxially connected with the gas generator. The first rectification plate and the second rectification plate are coaxially arranged in the rectification duct in sequence from the rectification duct inlet to the rectification duct outlet, and the first rectification plate and the second rectification plate are both used for reducing the speed and uniformizing the gas. The gas pre-injection cavity is coaxially installed at the rectification duct outlet end and is used for being coaxially connected with the thrust chamber. Compared with the conventional rectification grid of the engine, the multilayer rectification structure with high uniform flow is suitable for higher flow speed, has better uniform flow effect for the uniformity of gas temperature, and has good damping effect on the flow gas pressure oscillation.

Description

Technical Field

[0001] This invention relates to a rectification structure, specifically to a high-flow-average gas rectification structure and engine. Background Technology

[0002] Liquid rocket engines have high gas pressure, high velocity, and poor gas temperature uniformity at the gas generator outlet. Before the gas enters the thrust chamber for afterburning, it needs to be depressurized, decelerated, and rectified to prevent problems such as thrust chamber erosion, performance deviation, and unstable combustion caused by total pressure distortion, eddies, uneven gas velocity and temperature, and pressure oscillation before gas injection.

[0003] In traditional afterburning cycle engines, the gas generator's gas flow rate is significantly reduced and the uniformity of gas temperature is effectively improved after the gas is mixed through the complex cavity of the turbine. The thrust chamber can achieve the rectification effect by using a single-layer rectifier plate structure. However, when the gas generator and thrust chamber are tested together, the gas passage between the two components does not have a rectification effect. The high-speed, non-uniform incoming gas cannot meet the flow uniformity requirements with a single-layer rectifier plate structure, and the damping effect on pressure pulsation is also weak. When testing the reliability of the thrust chamber's working cooling and combustion stability, supply problems that do not exist under the actual working conditions of the engine may be introduced. Summary of the Invention

[0004] The purpose of this invention is to provide a high-flow-average gas rectification structure and engine to solve the technical problems that, during the joint testing of the gas generator and thrust chamber, the gas passage between the two components has no rectification effect, the high-speed, non-uniform incoming gas is difficult to meet the flow-average requirements with a single-layer rectification plate structure, the damping effect on pressure pulsation is also weak, and the actual working conditions of the engine may not be met when evaluating the reliability of the thrust chamber's working cooling and combustion stability.

[0005] To achieve the above objectives, the present invention provides a high-flow-average gas rectification structure for use between a gas generator and a thrust chamber; its special feature is that it includes a rectification duct, a first rectification plate, a second rectification plate, and a gas injection inlet chamber;

[0006] The inlet end of the rectifier duct is coaxially connected to the gas generator;

[0007] The first rectifier plate and the second rectifier plate are coaxially arranged in the rectifier duct along the direction from the inlet to the outlet. Both the first rectifier plate and the second rectifier plate are used to decelerate and homogenize the combustion gas.

[0008] The gas injection inlet chamber is coaxially mounted at the outlet end of the rectifier duct for coaxial connection with the thrust chamber.

[0009] Furthermore, the rectifier conduit includes a first conical section, a first cylindrical section, a second conical section, and a second cylindrical section arranged sequentially from the inlet to the outlet.

[0010] The small end of the first conical section is the inlet end of the rectifier duct, which is used to be coaxially connected to the gas generator, and its large end is connected to one end of the first cylindrical section.

[0011] The small end of the second conical segment is connected to the other end of the first cylindrical segment, and the large end is connected to one end of the second cylindrical segment;

[0012] The gas injection front cavity is coaxially mounted at the other end of the second cylindrical section;

[0013] The first rectifier plate is disposed inside the first cylindrical section;

[0014] The second rectifier plate is disposed inside the second cylindrical section.

[0015] Furthermore, the axial length of the first conical segment is 54mm to 64mm;

[0016] The axial length of the first cylindrical section is 190mm to 220mm, and its inner diameter is 70mm to 90mm.

[0017] The axial length of the second conical segment is 58mm to 68mm;

[0018] The axial length of the second cylindrical section is 12mm to 18mm, and its inner diameter is 135mm to 165mm.

[0019] The axial length of the gas injection front cavity is 25mm to 50mm.

[0020] Furthermore, the center of the first rectifier plate is bent towards the outlet direction of the rectifier duct, making its inner and outer surfaces spherical curved surfaces;

[0021] The first rectifier plate has an anti-ablation hole at its center to prevent the high-temperature area of ​​the incoming gas from directly contacting the first rectifier plate; a plurality of first flow passage holes are evenly distributed around the anti-ablation hole in the circumferential direction from the inside to the outside of the first rectifier plate.

[0022] Furthermore, the diameter of the anti-ablation hole is 15mm to 21mm.

[0023] Furthermore, the diameter of the first flow-through orifice on the first rectifier plate gradually increases radially from the inside out.

[0024] Furthermore, the second rectifier plate is flat and has a plurality of second flow holes evenly distributed on it.

[0025] Furthermore, the diameters of the second flow passage holes on the second rectifier plate are all the same.

[0026] Furthermore, the rectifier duct, the first rectifier plate, the second rectifier plate, and the gas injection inlet cavity are all made of nickel-based high-temperature alloy GH4202 or GH4169.

[0027] Meanwhile, the present invention also provides an engine, which is characterized by including a gas generator, a thrust chamber and the aforementioned high flow uniformity gas rectification structure;

[0028] The inlet end of the rectifier duct is coaxially connected to the gas generator;

[0029] The outlet end of the gas injection pre-cavity is coaxially connected to the thrust chamber.

[0030] The beneficial effects of this invention are:

[0031] 1. The gas rectification structure provided by the present invention, compared with the conventional engine rectifier grid, has a high flow uniformity multi-layer rectification structure that can adapt to the incoming flow velocity, has a better flow uniformity effect for adapting to the uniformity of gas temperature, and has a very good damping effect on the pressure oscillation of the incoming gas flow. It can realize the coaxial connection between the gas generator and the thrust chamber.

[0032] 2. A high-uniformity gas rectification structure is set between the gas generator and the thrust chamber. This structure can ensure the overall pressure drop value, enabling the gas generator outlet throat to reach sonic conditions. It can also effectively decelerate the high-temperature, high-pressure, and high-speed incoming gas and ensure its temperature and pressure are evenly distributed. Furthermore, the overall structure of the gas rectification structure is compact, has a high overall load-bearing capacity, and does not add burden to the overall structure of the joint test system.

[0033] 3. The gas rectification structure provided by the present invention has four deceleration and three rectification functions. The first and second rectifier plates are used to rectify and decelerate the gas twice, realizing the material exchange between different zones of gas in the rectifier duct. The temperature uniformity of the gas is significantly improved after mixing.

[0034] 4. In the gas rectification structure provided by the present invention, the rectification conduit is divided into a first conical section, a first cylindrical section, a second conical section and a second cylindrical section. Both the first conical section and the second conical section have a deceleration effect. In particular, the second conical section also utilizes gas recirculation to achieve gas flow equalization.

[0035] 5. In this invention, the center of the first rectifier plate is bent towards the outlet direction of the rectifier duct, making the surface a spherical curved surface. This can increase the contact area between the first rectifier plate and the gas, and its rectification effect, deceleration effect and pressure bearing capacity are all effectively improved.

[0036] 6. In this invention, the rectifier duct is coaxially connected to the gas generator and the thrust chamber, respectively, which controls the overall length of the gas generator, the gas rectifier structure and the thrust chamber, reducing the complexity of the overall structure and the difficulty of installation.

[0037] 7. The gas rectifier structures in this application are all made of nickel-based high-temperature alloys (GH4202, GH4169), which have good oxidation resistance and high structural strength. Attached Figure Description

[0038] Figure 1 This is a schematic diagram of an embodiment of a high-flow-average gas rectification structure according to the present invention;

[0039] Figure 2 This is a side view of the first rectifier plate in an embodiment of the present invention;

[0040] Figure 3 This is a front view of the first rectifier plate in an embodiment of the present invention;

[0041] Figure 4 This is a front view of the second rectifier plate in an embodiment of the present invention;

[0042] Figure 5 This is a gas rectification Mach number distribution diagram in an embodiment of the present invention.

[0043] Icon labels:

[0044] 1-Rectifier duct, 11-First conical section, 12-First cylindrical section, 13-Second conical section, 14-Second cylindrical section, 2-First rectifier plate, 21-Anti-ablation hole, 22-First flow passage hole, 3-Second rectifier plate, 31-Second flow passage hole, 4-Gas injection front cavity. Detailed Implementation

[0045] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0046] This embodiment provides a high-flow-average gas rectification structure for use between the gas generator and the thrust chamber; such as Figure 1 As shown, it includes a rectifier duct 1, a first rectifier plate 2, a second rectifier plate 3, and a gas injection front cavity 4.

[0047] The rectifying conduit 1 includes a first conical section 11, a first cylindrical section 12, a second conical section 13, and a second cylindrical section 14 arranged sequentially from the inlet to the outlet. The small end of the first conical section 11 is coaxially connected to the gas generator, and its large end is coaxially connected to one end of the first cylindrical section 12. The small end of the second conical section 13 is coaxially connected to the other end of the first cylindrical section 12, and its large end is coaxially connected to one end of the second cylindrical section 14. The other end of the second cylindrical section 14 is coaxially connected to the gas injection pre-cavity 4. Specifically, the axial length of the first conical section 11 is 54mm to 64mm, specifically 59mm; the axial length of the first cylindrical section 12 is 190mm to 220mm, specifically 205mm, and its inner diameter is 70mm to 90mm, specifically 80mm; the axial length of the second conical section 13 is 58mm to 68mm, specifically 63mm; and the axial length of the second cylindrical section 14 is 12mm to 18mm, specifically 15mm, and its inner diameter is 135mm to 165mm, specifically 150mm.

[0048] The first rectifier plate 2 is coaxially arranged inside the first cylindrical section 12. For example... Figure 2 , Figure 3 As shown, the center of the first rectifier plate 2 is bent towards the outlet direction of the rectifier duct 1, making its surface a spherical curved surface, which increases the overall flow area of ​​the gas. The center of the first rectifier plate 2 is provided with an anti-ablation hole 21 to prevent the high-temperature area of ​​the incoming gas from directly contacting the first rectifier plate 2. Multiple first flow-through holes 22 are evenly distributed circumferentially around the anti-ablation hole 21 from the inside to the outside on the first rectifier plate 2. The diameter of the anti-ablation hole 21 is 15mm to 21mm, specifically 18mm. The anti-ablation hole 21 allows the high-temperature portion of the incoming gas to pass directly through, preventing direct contact with the first rectifier plate 2 and thus avoiding deformation or ablation. The multiple first flow-through holes 22 gradually increase in size from the inside to the outside along the radial direction of the first rectifier plate 2. The anti-ablation hole 21 and the first flow-through holes 22 distributed on the first rectifier plate 2 can effectively control the pressure drop (ΔP1 / P1) of the first rectifier plate 2. * =7%~12%, where ΔP1 is the pressure difference across the first rectifier plate 2, specifically 0.6MPa~1.4MPa; P1 * The pressure between the first rectifier plate 2 and the second rectifier plate 3 is 8MPa to 12MPa, which improves the load-bearing capacity of the first rectifier plate 2.

[0049] The second rectifier plate 3 is coaxially disposed within the second cylindrical section 14. For example... Figure 4 As shown, the second rectifier plate 3 is flat, with multiple second flow passages 31 evenly distributed on it. All the second flow passages 31 on the second rectifier plate 3 have the same diameter. The second rectifier plate 3 employs a low flow resistance (ΔP2 / P2). *=3%~6%, where ΔP2 is the pressure difference across the second rectifier plate 3, specifically 0.25MPa~0.50MPa, P2 * The pressure inside the gas injection cavity 4 is 7-11 MPa. The small flow channel slows down the gas, and the gas in the central and side areas mixes with each other. At the same time, the gas pressure, velocity and temperature are highly uniform under the condition that the axial length of the gas injection cavity 4 after rectification is not large (25mm-50mm).

[0050] Both the first rectifier plate 2 and the second rectifier plate 3 are used for deceleration and uniform combustion; such as Figure 5 As shown, the first conical section 11 decelerates the gas for the first time, the first rectifier plate 2 decelerates the gas for the second time, and the umbrella-shaped distribution of the first flow-through orifices 22 achieves the first strong mixing of the gas in the central and peripheral regions. A second conical section 13 is set between the first rectifier plate 2 and the second rectifier plate 3, causing the gas to decelerate for the third time before passing through the second rectifier plate 3. The gas then flows back within the second conical section 13 for the second mixing, further reducing the stress caused by uneven pressure and temperature on the second rectifier plate 3. The gas then undergoes a fourth deceleration at the second rectifier plate 3 and a third mixing within the gas injection pre-cavity 4. This achieves four decelerations and three mixings of the gas, improving its flow uniformity and damping effect on the pressure oscillations of the incoming gas flow.

[0051] The gas injection inlet chamber is coaxially mounted at the outlet end of the rectifier duct 1 for coaxial connection with the thrust chamber.

[0052] The high-flow-average gas rectifier structure uses nickel-based high-temperature alloys (GH4202, GH4169), which have good oxidation resistance and high structural strength.

[0053] This invention relates to a design for a high-uniformity gas rectification structure between the gas generator and the thrust chamber during a test of the core components of a room-temperature propellant oxygen-enriched staged combustion cycle engine. The gas generated by the room-temperature propellant high-oxygen-enrichment gas generator exhibits a significant difference in the mixing ratio between the central and peripheral regions. The peripheral region also has a mixing ratio distribution structure depending on the injector arrangement. Without sufficient mixing, the temperature distribution uniformity is poor. Before entering the thrust chamber, a structure is needed to generate vortices between the central and peripheral regions, and circumferentially between the peripheral regions, to ensure thorough mixing of the high and low temperature gases and improve temperature distribution uniformity. To control the overall length and reduce structural complexity and installation difficulty, the gas generator, rectification structure, and thrust chamber are coaxially connected. After the gas generator outlet gas passes through the sonic nozzle, the supersonic gas, under axial pipe flow conditions, does not have the conditions to generate vortices. The rectifying structure provided in this invention not only ensures that the overall pressure drop value reaches the sonic conditions at the gas generator outlet throat, but also effectively decelerates the high-temperature, high-pressure, and high-speed incoming flow and achieves uniform temperature and pressure distribution, while also being compact in structure. Under high-temperature, high-pressure, and high-speed gas conditions, temperature non-uniformity and eddies generated by rectification result in large thermal and impact loads on the rectifying structure, requiring the rectifying structure to also have a high strength margin.

[0054] This embodiment also provides an engine, including a gas generator, a thrust chamber, and the aforementioned high-flow-uniformity gas rectification structure; the inlet end of the rectification duct 1 is coaxially connected to the gas generator; the outlet end of the gas injection pre-cavity 4 is coaxially connected to the thrust chamber. Compared with conventional engine rectification grids, this engine's high-flow-uniformity multi-layer rectification structure adapts to higher incoming flow velocities, has better flow uniformity for gas temperature, and provides excellent damping for incoming gas pressure oscillations, enabling coaxial connection between the gas generator and the thrust chamber.

[0055] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present invention should be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A high-flow-average gas rectification structure for use between a gas generator and a thrust chamber; characterized in that: It includes a rectifier duct (1), a first rectifier plate (2), a second rectifier plate (3), and a gas injection front cavity (4); The rectifier conduit (1) includes a first conical section (11), a first cylindrical section (12), a second conical section (13), and a second cylindrical section (14) arranged sequentially from the inlet to the outlet. The small end of the first conical section (11) is the inlet end of the rectifier conduit (1) and is used to connect coaxially with the gas generator. Its large end is connected to one end of the first cylindrical section (12). The small end of the second conical section (13) is connected to the other end of the first cylindrical section (12), and its large end is connected to one end of the second cylindrical section (14). The first rectifier plate (2) is disposed inside the first cylindrical section (12); the second rectifier plate (3) is disposed inside the second cylindrical section (14); both the first rectifier plate (2) and the second rectifier plate (3) are used for deceleration and uniform combustion. The gas injection chamber (4) is coaxially mounted at the other end of the second cylindrical section (14) for coaxial connection with the thrust chamber.

2. The high flow uniformity gas rectification structure according to claim 1, characterized in that: The axial length of the first conical segment (11) is 54mm to 64mm; The axial length of the first cylindrical section (12) is 190mm to 220mm, and its inner diameter is 70mm to 90mm. The axial length of the second conical segment (13) is 58mm to 68mm; The axial length of the second cylindrical section (14) is 12mm to 18mm, and its inner diameter is 135mm to 165mm. The axial length of the gas injection pre-cavity (4) is 25mm to 50mm.

3. The high flow uniformity gas rectification structure according to claim 1 or 2, characterized in that: The center of the first rectifier plate (2) is bent toward the outlet direction of the rectifier duct (1), so that its inner and outer surfaces are spherical curved surfaces; The first rectifier plate (2) has an anti-ablation hole (21) in the center to prevent the high temperature area of ​​the incoming gas from directly contacting the first rectifier plate (2); a number of first flow passage holes (22) are evenly distributed around the anti-ablation hole (21) from the inside to the outside along the circumference of the first rectifier plate (2).

4. The high flow uniformity gas rectification structure according to claim 3, characterized in that: The diameter of the anti-ablation hole (21) is 15mm to 21mm.

5. The high flow uniformity gas rectification structure according to claim 4, characterized in that: The diameter of the first flow-through hole (22) on the first rectifier plate (2) gradually increases radially from the inside to the outside.

6. The high flow uniformity gas rectification structure according to claim 5, characterized in that: The second rectifier plate (3) is flat and has multiple second flow holes (31) evenly distributed on it.

7. The high-flow-average gas rectification structure according to claim 6, characterized in that: The second flow passage (31) on the second rectifier plate (3) has the same diameter.

8. The high flow uniformity gas rectification structure according to claim 7, characterized in that: The rectifier duct (1), the first rectifier plate (2), the second rectifier plate (3) and the gas injection front cavity (4) are all made of nickel-based high-temperature alloy GH4202 or GH4169.

9. An engine, characterized in that: It includes a gas generator, a thrust chamber, and a high-flow-average gas rectification structure as described in any one of claims 1-8; The inlet end of the rectifier duct (1) is coaxially connected to the gas generator; The outlet end of the gas injection chamber (4) is coaxially connected to the thrust chamber.

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