Nozzle test device

Abstract

The present invention discloses a nozzle test device, which relates to the field of aerospace technology and is used to solve the problem that a rocket engine test bench cannot simulate the change process of the flow field of the nozzle caused by the change of flight altitude. The nozzle test device includes an ejector sleeve and a drive device. The ejector sleeve is used to be installed on the peripheral side of the outlet of the tested nozzle, and an annular gap is formed between the ejector sleeve and the peripheral side of the outlet end of the tested nozzle; the drive device is arranged on the peripheral side of the ejector sleeve, and the drive end of the drive device is dynamically connected to the outer wall of the ejector sleeve. The drive device is used to drive the ejector sleeve to move axially relative to the tested nozzle to adjust the axial position of the ejector sleeve relative to the outlet end of the tested nozzle. The nozzle test device provided by the present invention is used to realize the gradual transition between the separation state and the full flow state of the nozzle, simulate the gradual change of the flow field in the nozzle of the engine when the flight altitude changes, and cooperate with the rocket engine test bench to realize the test of the nozzle.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a nozzle test device. Background Art

[0002] During the development of engines using altitude-compensating nozzles, it is essential to simulate the engine's actual flight process at varying altitudes to test the nozzle's performance and reliability. When operating under ground conditions, atmospheric pressure causes the air around the nozzle to backflow, causing the airflow to move inward, separating the nozzle's gas flow from the nozzle's sidewalls at the nozzle's exit. This creates a separated nozzle flow state. As the operating environment gradually increases, the atmospheric pressure decreases, reducing the effect on the nozzle's gas flow, allowing the gas flow to gradually adhere to the nozzle's sidewalls, resulting in a gradual transition to full flow. Therefore, the test bench must be able to simulate the transition from separated to full flow in the engine's nozzle under test, and this transition must be controllable to simulate the rate of change in flow field structure caused by changes in ambient pressure at different flight speeds.

[0003] For traditional rocket engine test benches, when the ejector sleeve is not installed, the back pressure at the nozzle outlet is the ambient pressure, which can simulate the working state of the engine on the ground; when the ejector sleeve is installed, it simulates the working state of the engine at high altitude, that is, a high-model test of the engine nozzle is carried out.

[0004] However, the ejector sleeve position of traditional rocket engine test benches is fixed. During the entire test process, the flow field structure in the nozzle of the test engine does not change with changes in external factors. Therefore, it can only simulate a single high-altitude full flow state, and cannot simulate the flow field change process caused by changes in flight altitude. Summary of the Invention

[0005] The purpose of the present invention is to provide a nozzle test device to realize the gradual transition of the flow separation state and the full flow state of the nozzle, thereby simulating the gradual change of the flow field in the nozzle of the engine when the flight altitude changes, and cooperating with the rocket engine test bench to realize the test of the nozzle.

[0006] In order to achieve the above object, the present invention provides a nozzle test device, comprising:

[0007] The ejector sleeve is used to be sleeved on the peripheral side of the outlet of the tested nozzle, and a radial annular gap is formed between the ejector sleeve and the peripheral side of the outlet end of the tested nozzle;

[0008] The driving device is arranged on the peripheral side of the ejector sleeve, and the driving end of the driving device is dynamically connected to the outer side wall of the ejector sleeve. The driving device is used to drive the ejector sleeve to move axially relative to the tested nozzle to adjust the axial position of the ejector sleeve relative to the outlet end of the tested nozzle.

[0009] Compared with the prior art, the present invention provides a nozzle test device comprising an ejector sleeve and a driving device. The driving device can drive the ejector sleeve to move axially, thereby adjusting the axial position of the ejector sleeve relative to the nozzle. The ejector sleeve is first driven axially away from the nozzle by the driving device. Since the ejector sleeve is far away from the nozzle, it will not affect the airflow around the nozzle. Under the action of atmospheric pressure and the nozzle gas flow, the airflow around the nozzle will flow back into the nozzle, so that the nozzle is in a flow separation state. Then, the ejector sleeve is driven axially by the driving device. Gradually approach the nozzle until the end of the ejector sleeve close to the nozzle exceeds the outlet end of the nozzle. At this time, the ejector sleeve is located on the side of the nozzle, and the end of the ejector sleeve close to the nozzle is upstream of the airflow around the nozzle outlet. The airflow around the nozzle can only flow through the annular gap between the ejector sleeve and the nozzle side. The flow channel becomes smaller, the airflow speed increases, and the flow direction is consistent with the direction of the gas flow at the nozzle outlet, which hinders the development of backflow and the nozzle is in a full flow state. Therefore, when the driving device drives the ejector sleeve to gradually approach the nozzle along the axial direction, the flow separation of the nozzle The ejector sleeve is first driven axially toward the nozzle until the end of the ejector sleeve near the nozzle exceeds the nozzle outlet end. The end of the ejector sleeve near the nozzle is upstream of the airflow around the nozzle outlet. At this time, the nozzle is in a full flow state. Then, the ejector sleeve is driven axially away from the nozzle by the driving device. The ejector sleeve's influence on the airflow around the nozzle gradually decreases, and the flow separation of the nozzle gradually increases until a separation state is reached. Therefore, when the driving device drives the ejector sleeve axially away from the nozzle, the flow separation of the nozzle also gradually increases, thereby reaching a separation state similar to the ground working state, thereby simulating the nozzle working environment of the engine returning to the ground from high altitude. Of course, the driving device can flexibly control the ejector sleeve to move back and forth in the axial direction, thereby changing the airflow field environment around the nozzle, achieving an increase or decrease in the nozzle flow separation, and thus flexibly simulating the working environment of the engine nozzle when the flight altitude changes. Based on this, the present invention provides a nozzle test device that can realize the gradual reduction of the flow separation of the nozzle until it reaches a full flow state, thereby simulating the working environment of the engine nozzle flying from the ground to high altitude. At the same time, it can realize the nozzle starting from the full flow state and gradually increasing the flow separation until it reaches a flow separation state similar to that of the ground work, thereby simulating the working environment of returning from high altitude to the ground, and the driving device can flexibly control the axial reciprocating movement of the ejector sleeve, thereby flexibly simulating the working environment of the engine nozzle when the flight altitude changes; therefore, the embodiment of the present invention provides a nozzle test device that can change the flow state of the nozzle being tested, thereby simulating the change of the flow field in the nozzle when the flight altitude of the engine nozzle changes, and cooperate with the rocket engine test bench to realize the test of the nozzle.

[0010] Optionally, in the above-mentioned nozzle test device, the driving device includes:

[0011] A follower, which is arranged on the outside of the ejector sleeve and is fixedly connected to the ejector sleeve;

[0012] The drive assembly is arranged on the outside of the ejector sleeve. The drive assembly is used to be fixedly connected to the rocket engine test bench. The drive end of the drive assembly is fixedly connected to the follower. The drive assembly is also used to drive the follower to move axially along the ejector sleeve.

[0013] Optionally, in the above-mentioned nozzle test device, the drive assembly includes:

[0014] A driving member, the driving member is used to be fixedly connected to the rocket engine test bench;

[0015] The transmission mechanism is in transmission connection with the driving end of the driving member, and the driving end of the transmission mechanism is in power connection with the driven member, and is used to control the axial movement of the driven member along the ejector sleeve.

[0016] Optionally, in the above-mentioned nozzle test device, the transmission mechanism includes:

[0017] A driving shaft, the driving shaft being drivingly connected to the driving end of the driving member;

[0018] A transmission member, the transmission member is in transmission connection with the driving shaft, and the transmission member is fixedly connected with the driven member;

[0019] The driven shaft is in transmission connection with the transmission member and is used to support the transmission member.

[0020] Optionally, in the above-mentioned nozzle test device, the transmission member is a transmission hinge or a transmission belt.

[0021] Optionally, in the above-mentioned nozzle test device, the driving device further includes:

[0022] The support slide rod is used to be fixedly connected to the rocket engine test bench. A sliding hole is provided on the follower. The support slide rod extends into the sliding hole and is slidably connected to the follower.

[0023] Optionally, in the above-mentioned nozzle test device, the driving device further includes:

[0024] Two limiters are fixedly arranged at both ends of the supporting slide bar, and the limiters are used to limit the follower.

[0025] Optionally, in the above-mentioned nozzle test device, the driving device includes 2-4 driven parts.

[0026] Optionally, in the above-mentioned nozzle test device, the number of the driving devices is 2-4 groups, the multiple groups of driving devices are evenly arranged on the circumference of the ejector sleeve, and the multiple groups of driving devices are driven synchronously.

[0027] Optionally, in the above-mentioned nozzle test device, the nozzle test device further includes:

[0028] A cooling mechanism is provided on the ejector sleeve with a cooling channel, and the cooling mechanism is used to introduce and recover cooling liquid into the cooling channel.

[0029] Optionally, in the above-mentioned nozzle test device, the minimum radial distance between the inner surface of the ejector sleeve and the outer wall of the tested nozzle is 2 mm-50 mm. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0031] Figure 1 A schematic diagram of a nozzle test device provided in an embodiment of the present invention;

[0032] Figure 2 A cross-sectional view of a nozzle test device provided in an embodiment of the present invention;

[0033] Figure 3 A schematic diagram of an ejector sleeve and a cooling system provided in an embodiment of the present invention;

[0034] Figure 4 A schematic diagram of the gas field of a nozzle test device provided by an embodiment of the present invention when the axial distance Δd=Re (Re is the radius of the nozzle outlet end) between the end of the ejector sleeve close to the nozzle and the nozzle outlet end is in a state;

[0035] Figure 5 for Figure 4 Enlarged view at point A;

[0036] Figure 6 A schematic diagram of the gas field of a nozzle test device provided by an embodiment of the present invention, in a state where an ejector sleeve is arranged on the peripheral side of the nozzle outlet and the axial distance Δd=0.2Re between the ejector sleeve end close to the nozzle and the nozzle outlet end;

[0037] Figure 7 for Figure 6 Enlarged view at B.

[0038] Reference numerals:

[0039] 1- ejector sleeve; 11- cooling channel; 2- driving device; 21- driven member; 22- driving assembly; 221- driving member; 222- transmission mechanism; 2221- driving shaft; 2222- transmission member; 2223- driven shaft; 23- supporting slide rod; 3- cooling mechanism; 31- water supply pipe; 32- inlet liquid collecting ring; 33- water recovery pipe; 34- outlet liquid collecting ring; 4- nozzle. DETAILED DESCRIPTION

[0040] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0041] It should be noted that when an element is referred to as being “fixed on” or “disposed on” another element, it may be directly on the other element or indirectly on the other element. When an element is referred to as being “connected to” another element, it may be directly connected to the other element or indirectly connected to the other element.

[0042] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined. "Several" means one or more, unless otherwise specifically defined.

[0043] In the description of the present invention, it should be understood that the terms "up", "down", "front", "back", "left", "right", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention.

[0044] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and may encompass internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0045] The nozzle discharges the high-temperature, high-pressure combustion gases from the combustion chamber at high speed, generating the thrust required by the rocket. Its performance directly affects the engine's thrust, and thus the rocket's carrying capacity. Traditional fixed-area-ratio axisymmetric nozzles have only one design altitude, and their non-ideal expansion losses at off-design altitudes are severe, an order of magnitude higher than other losses. Altitude-compensating nozzles, such as the double-bell nozzle, plug nozzle, expansion-deflection nozzle, and slot nozzle, have multiple design altitudes. They effectively compensate for the performance losses of traditional nozzles caused by varying flight altitudes, bringing the nozzle outlet pressure closer to ambient atmospheric pressure, thereby improving engine performance at off-design altitudes.

[0046] During the development of engines using altitude-compensating nozzles, it is essential to simulate the engine's actual flight process at varying altitudes to test the nozzle's performance and reliability. When operating under ground conditions, atmospheric pressure causes the air around the nozzle to backflow, causing the airflow to move inward, separating the nozzle's gas flow from the nozzle's sidewalls at the nozzle's exit. This creates a state of flow separation. As the operating environment gradually increases, the atmospheric pressure decreases, reducing the effect on the nozzle's gas flow, allowing the gas flow to gradually adhere to the nozzle's sidewalls, resulting in a state of full flow. Therefore, the test bench must be able to simulate the transition from flow separation to full flow in the test engine's nozzle, and this transition must be controllable to simulate the rate of change in the flow field structure caused by changes in ambient pressure at different flight speeds.

[0047] For traditional rocket engine test benches, when the ejector sleeve is not installed, the nozzle outlet back pressure is the ambient pressure, which can simulate the working state of the engine on the ground; when the ejector sleeve is installed, the nozzle outlet back pressure is increased to simulate the working state of the engine at high altitude, that is, to conduct a high-model test on the engine nozzle.

[0048] However, the position of the ejector sleeve of the traditional test bench is fixed. During the entire test process, the flow field structure in the nozzle of the test engine does not change with changes in external factors. Therefore, it can only simulate a single high-altitude full flow state, and cannot simulate the change process of the flow field caused by changes in flight altitude.

[0049] To solve the above problem, please refer to Figure 1 and Figure 2An embodiment of the present invention provides a nozzle test device, including an ejector sleeve 1 and a driving device 2. The ejector sleeve 1 is used to be sleeved on the peripheral side of the outlet of the tested nozzle 4, and a radial annular gap is defined between the ejector sleeve 1 and the peripheral side of the outlet end of the tested nozzle 4; the driving device 2 is arranged on the peripheral side of the ejector sleeve 1, and the driving end of the driving device 2 is dynamically connected to the outer side wall of the ejector sleeve 1. The driving device 2 is used to drive the ejector sleeve 1 to move axially relative to the tested nozzle 4 to adjust the axial position of the ejector sleeve 1 relative to the outlet end of the tested nozzle 4.

[0050] During the test of the nozzle 4, the ejector sleeve 1 is installed on the outlet side of the tested nozzle 4, and the axes of the ejector sleeve 1 and the tested nozzle 4 are ensured to coincide. When simulating the situation where the engine flies from the ground to a high altitude, the ejector sleeve 1 is first driven axially away from the nozzle 4 by the driving device 2 until the axial distance Δd ≥ Re between the end of the ejector sleeve 1 close to the nozzle 4 and the outlet end of the nozzle 4, where Re is the radius of the outlet end of the nozzle 4. At this time, the ejector sleeve 1 is far away from the nozzle 4 and will not affect the airflow around the nozzle 4, thereby simulating the flow separation state of the nozzle 4 when it is on the ground. Then, the ejector sleeve 1 is driven axially step by step close to the nozzle 4 by the driving device 2 until the ejector sleeve 1 is close to the nozzle 4. One end exceeds the outlet end of the nozzle 4, so that the flow separation of the nozzle 4 is gradually reduced until it reaches a full flow state; when simulating the situation where the engine returns to the ground from a high altitude, the ejector sleeve 1 is first driven by the driving device 2 to approach the nozzle 4 axially until the end of the ejector sleeve 1 close to the nozzle 4 exceeds the outlet end of the nozzle 4, that is, the end of the ejector sleeve 1 close to the nozzle 4 is on the peripheral side of the outlet end of the nozzle 4, and the axial distance Δd between the end of the ejector sleeve 1 close to the nozzle 4 and the outlet end of the nozzle 4 is ≥0.2Re, ensuring that the nozzle 4 is in a full flow state after starting, and then the ejector sleeve 1 is driven by the driving device 2 to gradually move away from the nozzle 4 axially, so that the flow separation of the nozzle 4 is gradually increased until it reaches a separation state.

[0051] Through the structure and specific implementation process of the above-mentioned nozzle test device, it can be known that a nozzle test device provided by an embodiment of the present invention includes an ejector sleeve 1 and a driving device 2. The driving device 2 can drive the ejector sleeve 1 to move axially, thereby adjusting the axial position of the ejector sleeve 1 relative to the nozzle 4. After the ejector sleeve 1 is driven axially away from the nozzle 4 by the driving device 2, because the ejector sleeve 1 is far away from the nozzle 4, it will not affect the airflow around the nozzle 4. Under the action of atmospheric pressure and the gas flow of the nozzle 4, the airflow around the nozzle 4 will flow back into the nozzle 4, so that the nozzle 4 is in a flow separation state. For example, Figure 4 and Figure 5As shown, when the axial distance Δd=Re between the end of the ejector sleeve close to the nozzle and the outlet end of the nozzle (Re is the radius of the outlet end of the nozzle), the nozzle 4 is in a flow separation state, and then the ejector sleeve 1 is driven by the driving device 2 to gradually approach the nozzle 4 in the axial direction until the end of the ejector sleeve 1 close to the nozzle 4 exceeds the outlet end of the nozzle 4. At this time, the ejector sleeve 1 is located on the side of the nozzle 4, and the end of the ejector sleeve 1 close to the nozzle 4 is upstream of the airflow on the side of the outlet of the nozzle 4. The airflow on the side of the nozzle 4 can only flow through the annular gap between the ejector sleeve 1 and the side of the nozzle 4. The flow channel becomes smaller, the airflow velocity increases, and the flow direction is consistent with the direction of the gas airflow at the outlet of the nozzle 4, which hinders the development of backflow. The nozzle 4 is in a full flow state. For example, as shown in FIG. Figure 6 and Figure 7As shown, when the ejector sleeve is arranged on the peripheral side of the nozzle outlet and the axial distance Δd between the end of the ejector sleeve close to the nozzle and the outlet end of the nozzle is 0.2Re, the nozzle 4 is in a full flow state. Therefore, when the driving device 2 drives the ejector sleeve 1 to gradually approach the nozzle 4 in the axial direction, the flow separation of the nozzle 4 is gradually reduced until it completely disappears, thereby achieving a full flow state, realizing the simulation of the working environment of the nozzle 4 when the engine flies from the ground to high altitude; in addition, the ejector sleeve 1 is first driven by the driving device 2 to axially approach the nozzle 4 until the end of the ejector sleeve 1 close to the nozzle 4 exceeds the outlet end of the nozzle 4, and the end of the ejector sleeve 1 close to the nozzle 4 is upstream of the airflow on the peripheral side of the nozzle 4 outlet. At this time, the nozzle 4 is in a full flow state, and then the ejector sleeve 1 is driven by the driving device 2 to gradually approach the nozzle 4 in the axial direction. The device 2 drives the ejector sleeve 1 to gradually move away from the nozzle 4 in the axial direction, and the influence of the ejector sleeve 1 on the airflow around the nozzle 4 gradually decreases, and the flow separation of the nozzle 4 gradually increases until it reaches a separation state. Therefore, when the driving device 2 drives the ejector sleeve 1 to gradually move away from the nozzle 4 in the axial direction, the flow separation of the nozzle 4 also gradually increases, thereby achieving a separation state similar to the ground working state, realizing the simulation of the working environment of the nozzle 4 when the engine returns to the ground from high altitude; of course, the driving device 2 can flexibly control the ejector sleeve 1 to move back and forth in the axial direction, thereby changing the airflow field environment around the nozzle 4, realizing the increase or decrease of the flow separation of the nozzle 4, and then flexibly simulating the working environment of the nozzle 4 when the engine nozzle 4 changes at different flight altitudes. Compared with the prior art, the nozzle test device provided in the embodiment of the present invention can realize that the flow separation of the nozzle 4 is gradually reduced until it reaches a full flow state, thereby simulating the working environment of the engine nozzle 4 flying from the ground to high altitude. At the same time, it can realize that the nozzle 4 starts from the full flow state and gradually increases the flow separation until it reaches a flow separation state similar to that of the ground operation, thereby simulating the working environment of returning from high altitude to the ground. Moreover, the driving device 2 can flexibly control the axial reciprocating movement of the ejector sleeve 1, thereby flexibly simulating the working environment of the nozzle 4 when the engine nozzle 4 changes at different flight altitudes. Therefore, the nozzle test device provided in the embodiment of the present invention can change the flow state of the nozzle 4 under test, thereby simulating the change of the flow field in the nozzle 4 when the flight altitude of the engine nozzle 4 changes, and cooperate with the rocket engine test bench to realize the test of the nozzle 4.

[0052] Specifically, in the above-mentioned nozzle test device, the drive device 2 includes a follower 21 and a drive assembly 22. The follower 21 is disposed outside the ejector sleeve 1 and is fixedly connected to the ejector sleeve 1. The drive assembly 22 is disposed outside the ejector sleeve 1 and is used to be fixedly connected to the rocket engine test bench. The driving end of the drive assembly 22 is fixedly connected to the follower 21. The drive assembly 22 is also used to drive the follower 21 to move axially along the ejector sleeve 1. The drive assembly 22 drives the follower 21, which is fixedly connected to the ejector sleeve 1, to reciprocate axially along the ejector sleeve 1, thereby driving the ejector sleeve 1 to reciprocate axially, thereby achieving changes in the flow field within the nozzle 4.

[0053] As an optional approach, in the above-mentioned nozzle test device, the drive assembly 22 includes a drive member 221 and a transmission mechanism 222. The drive member 221 is used to be fixedly connected to the rocket engine test bench. Exemplarily, the drive member 221 is an electric motor or a hydraulic motor. The transmission mechanism 222 is in driving connection with the driving end of the drive member 221. The driving end of the transmission mechanism 222 is in power connection with the follower 21, which is used to control the axial movement of the follower 21 along the ejector sleeve 1. The drive member 221 provides a power source, which controls the transmission mechanism 222 to drive the follower 21 to reciprocate along the axial direction of the ejector sleeve 1, ultimately achieving axial reciprocating motion of the ejector sleeve 1.

[0054] In some embodiments, the transmission mechanism 222 includes a driving shaft 2221, a transmission member 2222, and a driven shaft 2223. The driving shaft 2221 is in driving connection with the driving end of the driving member 221; the transmission member 2222 is in driving connection with the driving shaft 2221, and the transmission member 2222 is fixedly connected to the driven member 21; the driven shaft 2223 is in driving connection with the transmission member 2222, and the driven shaft 2223 is used to support the transmission member 2222. The driving end of the driving member 221 drives the driving shaft 2221 to rotate, thereby driving the transmission member 2222 to move, and the transmission member 2222 in turn drives the driven member 21 to reciprocate along the axial direction of the ejector sleeve 1; at the same time, the driven shaft 2223 rotates in accordance with the movement of the transmission member 2222, supporting the transmission member 2222 while ensuring smooth operation.

[0055] Specifically, in the nozzle test device, the transmission member 2222 is a transmission hinge or a transmission belt, which has a simple structure and good economical efficiency.

[0056] As an optional embodiment, in the above-mentioned nozzle test device, the driving device 2 further includes a support slide 23, which is used to be fixedly connected to the rocket engine test bench. The follower 21 is provided with a sliding hole, and the support slide 23 extends into the sliding hole and is slidably connected to the follower 21. During operation, the support slide 23 is fixedly connected to the rocket engine test bench, and the follower 21 is mounted on the support slide 23 and slides along the support slide 23, thereby driving the ejector sleeve 1 to move. During this movement, the support slide 23 can provide support for the follower 21 and the ejector sleeve 1, ensuring the operating stability of the nozzle test device.

[0057] In some embodiments, the driving device 2 further includes two limiters, which are respectively fixedly disposed at both ends of the support slide bar 23. The limiters are used to limit the follower 21 to prevent the follower 21 from sliding out of the support slide bar 23.

[0058] As a possible implementation, in the nozzle test device described above, the drive device 2 includes 2-4 followers 21. For example, the drive device 2 includes 2, 3, or 4 followers 21. This arrangement improves the fixed connection between the multiple followers 21 and the ejector sleeve 1 and jointly drives the ejector sleeve 1 to move, ensuring connection reliability and operational stability.

[0059] In one optional embodiment, in the nozzle test apparatus described above, the number of drive devices 2 is 2-4 groups, and the multiple groups of drive devices 2 are evenly arranged around the ejector sleeve 1 and driven synchronously. For example, the number of drive devices 2 is 2, 3, or 4. The multiple groups of drive devices 2 jointly control the movement of the ejector sleeve 1, ensuring smooth movement of the ejector sleeve 1.

[0060] Specifically, see Figure 2 and Figure 3 The nozzle test apparatus described above also includes a cooling mechanism 3. The ejector sleeve 1 is provided with a cooling channel 11. The cooling mechanism 3 is used to introduce and recover cooling liquid into the cooling channel 11. The high temperature of the gas flow within the nozzle 4 causes the heat to be transferred to the ejector sleeve 1, raising its temperature. The cooling mechanism 3 reduces the temperature of the ejector sleeve 1, thereby extending its service life.

[0061] As a possible implementation, the cooling mechanism 3 includes a water supply pipe 31, an inlet liquid collecting ring 32, a recovery water pipe 33, and an outlet liquid collecting ring 34. The inlet liquid collecting ring 32 is arranged at the end of the ejector sleeve 1 away from the nozzle 4 and is connected to each cooling channel 11 of the ejector sleeve 1. The outlet liquid collecting ring 34 is arranged at the end of the ejector sleeve 1 close to the nozzle 4 and is connected to each cooling channel 11 of the ejector sleeve 1. The water supply pipe 31 is connected to the inlet liquid collecting ring 32, and the recovery water pipe 33 is connected to the outlet liquid collecting ring 34. During operation, cooling liquid is introduced into the water supply pipe 31, and the cooling liquid flows to the inlet liquid collecting ring 32, the cooling channel 11, and the outlet liquid collecting ring 34 in sequence, and finally flows out through the recovery water pipe 33, thereby cooling the ejector sleeve 1.

[0062] In some embodiments, the water supply pipe 31 and the water recovery pipe 33 are both metal hoses. Such an arrangement facilitates the water supply pipe 31 and the water recovery pipe 33 to move along with the movement of the ejector sleeve 1.

[0063] Specifically, in the nozzle test apparatus described above, the minimum radial distance between the inner surface of the ejector sleeve 1 and the outer wall of the nozzle 4 under test is 2 mm to 50 mm. For example, the minimum radial distance between the inner surface of the ejector sleeve 1 and the outer wall of the nozzle 4 under test is 2 mm, 10 mm, 20 mm, 30 mm, 40 mm, 50 mm, etc. This arrangement ensures that the annular gap between the ejector sleeve 1 and the outlet end of the nozzle 4 can affect the airflow outside the nozzle 4, allowing the nozzle 4 to reach a full flow state.

[0064] In some embodiments, the thickness of the ejector sleeve 1 is 10 mm to 20 mm. For example, the thickness of the ejector sleeve 1 is 10 mm, 12 mm, 15 mm, 18 mm, 20 mm, etc. This configuration ensures the rigidity of the ejector sleeve 1 while reducing its mass, thereby facilitating the axial reciprocating motion of the ejector sleeve 1.

[0065] In some embodiments, the length of the ejector sleeve 1 is 5-7 times the radius of the outlet end of the nozzle 4. For example, the length of the ejector sleeve 1 is 5 times, 5.5 times, 6 times, 6.5 times, 7 times, etc. the radius of the outlet end of the nozzle 4.

[0066] In the description of the above embodiments, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0067] 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 modifications or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. A nozzle test device, characterized in that: include: An ejector sleeve, the ejector sleeve being used to be sleeved on the peripheral side of the outlet of the tested nozzle, and having a radial annular gap between the ejector sleeve and the peripheral side of the outlet end of the tested nozzle; a driving device, the driving device being disposed on a circumferential side of the ejector sleeve, the driving end of the driving device being dynamically connected to an outer side wall of the ejector sleeve, the driving device being used to drive the ejector sleeve to perform axial movement relative to the nozzle under test, so as to adjust the axial position of the ejector sleeve relative to the outlet end of the nozzle under test; The nozzle test device can change the flow state of the nozzle being tested, thereby simulating the change of the flow field inside the nozzle of the engine when the flight altitude changes.

2. The nozzle test device according to claim 1, characterized in that: The driving device comprises: A follower, the follower being arranged on the outside of the ejector sleeve and fixedly connected to the ejector sleeve; A drive assembly is arranged on the outside of the ejector sleeve, and the drive assembly is used to be fixedly connected to the rocket engine test bench. The drive end of the drive assembly is fixedly connected to the follower, and the drive assembly is also used to drive the follower to move axially along the ejector sleeve.

3. The nozzle test device according to claim 2, characterized in that: The drive assembly includes: a driving member, the driving member being configured to be fixedly connected to the rocket engine test bench; A transmission mechanism is in transmission connection with the driving end of the driving member, and the driving end of the transmission mechanism is in power connection with the driven member, and is used to control the axial movement of the driven member along the ejection sleeve.

4. The nozzle test device according to claim 3, characterized in that: The transmission mechanism comprises: A driving shaft, the driving shaft being drivingly connected to the driving end of the driving member; A transmission member, the transmission member is in transmission connection with the driving shaft, and the transmission member is fixedly connected to the driven member; A driven shaft is in driving connection with the transmission member, and the driven shaft is used to support the transmission member.

5. The nozzle test device according to claim 4, characterized in that: The transmission member is a transmission hinge or a transmission belt.

6. The nozzle test device according to claim 2, characterized in that: The driving device further comprises: A supporting slide rod is used to be fixedly connected to the rocket engine test bench. A sliding hole is provided on the follower. The supporting slide rod extends into the sliding hole and is slidably connected to the follower.

7. The nozzle test device according to claim 6, characterized in that: The driving device further comprises: Two limiters are fixedly arranged at both ends of the supporting slide bar, and the limiters are used to limit the follower.

8. The nozzle test device according to claim 2, characterized in that: The driving device includes 2-4 driven members.

9. The nozzle test device according to claim 1, characterized in that: The number of the driving devices is 2-4 groups, and the multiple groups of driving devices are evenly arranged on the circumference of the ejection sleeve, and the multiple groups of driving devices are driven synchronously.

10. The nozzle testing device according to claim 1, characterized in that: The nozzle test device also includes: A cooling mechanism is provided on the ejector sleeve, and the cooling mechanism is used to introduce and recover cooling liquid into the cooling channel.

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