Turbine simulation device and generator hot test run system
By designing a turbine simulation device, including a convergent section, throat and divergent section, the problem of complex connection between the turbine and the generator was solved, and efficient and accurate generator performance testing was achieved, which is suitable for hot testing of rocket engines.
Patent Information
- Application Number
- CN202510754757.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-06-06
- Publication Date
- 2025-09-26
AI Technical Summary
During the hot test of a rocket engine generator, existing technology requires the turbine and generator to be connected via a flange, which results in complicated operation, consumes a lot of manpower and time, and makes it difficult to quickly inspect the inner cavity of the generator.
A turbine simulation device is designed, including a convergent section, a throat and a divergent section, to simulate the process of gas flowing through the turbine. The throat area is the same as the total area of the turbine stator blades. It is small in size and light in weight. It only needs to be connected to the generator for hot testing, avoiding complex connections and allowing for quick inspection of the generator cavity.
It improves the efficiency of hot test, saves manpower and time, ensures the accuracy and consistency of generator performance test, and is suitable for performance comparison and parameter calibration of different models.
Smart Images
Figure CN120701485A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of liquid launch vehicles, and in particular to a turbine simulation device and a generator thermal test system. Background Art
[0002] When designing a rocket engine generator, the generator's throat area is equal to the sum of the turbine vane areas. The turbine vanes are considered the generator's throat during the design process. Therefore, to accurately assess generator performance, the generator and turbine must be flange-connected during hot testing. Summary of the Invention
[0003] The purpose of this application is to provide a turbine simulation device and a generator hot test system, which are used to replace the turbine for generator hot test and improve the efficiency of generator hot test.
[0004] In order to achieve the above-mentioned object, the present application provides the following technical solutions: a turbine simulator, the turbine simulator comprising a convergent section, a throat section, and a divergent section;
[0005] The convergent section and the throat are detachably connected, and the cross-sectional area of the convergent section gradually decreases along the flow direction of the gas;
[0006] One end of the throat is detachably connected to the convergent section, and the other end of the throat is detachably connected to the divergent section. The minimum cross-sectional area of the throat is the same as the sum of the stationary blade areas of the turbine.
[0007] Compared with the prior art, the turbine simulator provided by the present application simulates the process of gas flowing through the turbine by setting a convergent section, a throat section, and an expansion section, and the minimum cross-sectional area of the throat section is the same as the sum of the stationary blade areas of the turbine, so that the turbine simulator of the present application can replace the turbine and be connected to the generator for hot testing. Based on this, since the device of the present application is small in size and weight, it does not need to be fixed to the test bench. It only needs to be connected to the generator to meet the test requirements, avoiding the complicated connection and fixation between the test bench and the generator. After the generator test, the inner cavity of the generator can be quickly inspected, saving a lot of manpower and time, and improving work efficiency.
[0008] The present application also provides a generator test system, comprising a generator and the turbine simulation device described in the present application, wherein the generator and the turbine simulation device are connected.
[0009] Compared with the prior art, the beneficial effects of the generator test system provided in this application are the same as the beneficial effects of the turbine simulation device described in the above technical solution, and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS
[0010] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:
[0011] Figure 1 A schematic structural diagram of a turbine simulation device provided by an exemplary embodiment of the present application is shown;
[0012] Figure 2 A schematic structural diagram of a convergent section and / or an expansion section provided by an exemplary embodiment of the present application is shown;
[0013] Figure 3 A schematic structural diagram of a high-temperature resistant sealing ring provided by an exemplary embodiment of the present application is shown;
[0014] Figure 4 The structure of the convergence section provided by the exemplary embodiment of the present application is shown Figure 1 ;
[0015] Figure 5 The structure of the convergence section provided by the exemplary embodiment of the present application is shown Figure 2 .
[0016] Reference numerals:
[0017] 100-turbine simulation device; 110-convergent section; 111-first cavity; 120-throat; 130-expansion section; 140-multi-layer sleeve structure; 141-detachable sleeve; 142-high-temperature resistant sealing ring; 1421-sealing side; 1422-flow guide side; 150-elbow; 160-connector. DETAILED DESCRIPTION
[0018] In order to make the technical problems, technical solutions and beneficial effects to be solved by this application more clearly understood, this application 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 this application and are not intended to limit this application.
[0019] 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.
[0020] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, "multiple" means two or more, unless otherwise clearly and specifically defined. "Several" means one or more, unless otherwise clearly and specifically defined.
[0021] In the description of this application, 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. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they should not be understood as limitations on this application.
[0022] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; they can refer to internal communication between two components or the interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.
[0023] When designing a rocket engine generator, the throat area of the generator is equal to the sum of the areas of the turbine stator blades. The design process considers the turbine stator blades to be the throat of the generator. Therefore, in order to accurately obtain the generator's performance, the generator and turbine need to be flange-connected for testing during the generator hot test. Due to the large size and weight of the turbine, connecting and fixing it to the generator and test bench is complex and difficult to operate. Furthermore, if you want to inspect the generator's inner cavity after the generator hot test to determine whether there is any ablation or damage, you usually need to disassemble the turbine, which consumes a lot of manpower and time.
[0024] To overcome these issues, the exemplary embodiments of this application provide a turbine simulator that replaces the traditional turbine-generator connection for hot testing. This device is compact and lightweight, requiring no test bench mounting; it can simply be connected to the generator to meet testing requirements, eliminating the need for complex connections and mounting to the test bench. Furthermore, after the generator test, the internal cavity can be quickly inspected, saving significant manpower and time and improving work efficiency.
[0025] Figure 1 FIG. 1 shows a schematic structural diagram of a turbine simulator provided by an exemplary embodiment of the present application. Figure 1As shown, the turbine simulation device 100 provided in the embodiment of the present application includes a convergent section 110 , a throat 120 and a divergent section 130 .
[0026] like Figure 1 As shown, the convergent section 110 and throat section 120 are detachably connected. The cross-sectional area of the convergent section 110 gradually decreases along the gas flow direction. This gradually decreasing cross-sectional area of the convergent section 110 simulates the convergent flow path of a turbine stator blade, effectively simulating the acceleration effect of the stator blade on the airflow, ensuring that the flow field in front of the throat section 120 is consistent with that of an actual turbine. This causes the high-speed gas flowing out of the generator to be accelerated due to the cross-sectional contraction as it flows through, reaching the speed of sound at the throat section 120 (the smallest cross-sectional area).
[0027] like Figure 1 As shown, one end of the throat 120 is detachably connected to the convergent section 110, and the other end of the throat 120 is detachably connected to the divergent section 130. The minimum cross-sectional area of the throat 120 is the same as the sum of the areas of the turbine stator blades. The throat 120 of the embodiment of the present application can be equivalent to the throat function of the turbine stator blades. The actual throat 120 of the turbine simulator 100 of the present application is constituted by the sum of the flow channels of the turbine stator blades. Therefore, the minimum area of the throat 120 directly replicates this key parameter, ensuring that the critical flow characteristics of the generator outlet are completely consistent with those when connected to a real turbine. In this case, the exhaust flow rate and mass flow rate of the generator during the hot test are the same as those in the actual working state, avoiding performance test deviations caused by flow differences. The critical flow state of the throat 120 determines the pressure distribution and outlet flow rate inside the generator, ensuring that the working back pressure and gas expansion characteristics of the generator during the hot test are consistent with those when connected to the turbine, thereby accurately verifying the performance parameters of the generator.
[0028] like Figure 1 As shown, the expansion section 130 of the present application is connected to the throat 120. By designing the cross-sectional area of the expansion section 130 to gradually expand, the combustion gas that has reached the speed of sound continues to accelerate to supersonic speed after the throat 120, forming a high-speed flow field similar to that of the turbine outlet, so as to avoid shock waves or flow separation caused by pressure changes in the air flow after the throat 120, ensure the stability of the air flow during the test, and accurately test the performance of the generator under high-speed flow conditions.
[0029] As can be seen from the above, by using the turbine simulation device provided in the embodiment of the present application, the core functions of a real turbine can be replaced. There is no need to use a real turbine that is large in size and heavy in weight. Only by designing the minimum area of the throat, the aerodynamic characteristics of the turbine throat can be simulated, avoiding the complex mechanical connection, fixation and sealing problems between the turbine and the test bench. It is also convenient for quick disassembly and inspection. After the hot test, it is only necessary to remove the small and simple structure of this device to directly inspect the inner cavity of the generator, eliminating the tedious steps of disassembling the turbine, greatly saving manpower and time, and improving test efficiency. At the same time, since the fixed throat area of the present application provides a unified boundary condition for the test, it is convenient for performance comparison and parameter calibration of generators of different batches and different models.
[0030] As a possible implementation, Figure 1 As shown, the convergence angle of the convergent section 110 is 15°-30°. For example, the convergence angle of the convergent section 110 can be 15°, 17°, 25°, or 30°, etc., but is not limited thereto. By setting the convergence angle of the convergent section 110 to meet these requirements, the phenomenon of airflow separation caused by too slow contraction due to a too small angle can be avoided.
[0031] In practical applications, the length of the convergent section has a great influence on the test results of the device. If the convergent section is too short, the airflow will accelerate too quickly, which may cause boundary layer separation or local shock waves, destroying the critical flow state; if it is too long, it will increase the flow resistance and the weight of the device.
[0032] In some embodiments, to overcome the above problems, Figure 1 As shown, the length of the converging section 110 can be determined by the convergence angle and the diameter of the throat 120. For example, the length of the converging section 110 can be calculated using a trigonometric function of the throat 120 diameter and the half-convergence angle. This ensures that the airflow is in a stable subsonic acceleration process before reaching the throat 120, and that the cross-section of the throat 120 is strictly the minimum area, thereby avoiding local contraction upstream of the throat 120 due to insufficient length, which could prematurely form a critical cross-section. It should be understood that the length of the converging section 110 here refers to the distance from the entrance of the converging section 110 to the throat 120.
[0033] In some embodiments, as Figure 1 As shown, the expansion angle of the expansion section 130 is 10°-15°, so as to avoid the occurrence of unstable airflow due to a too large angle.
[0034] In practical applications, the length of the expansion section has a great influence on the test results of the device. If the expansion section is too short, the airflow will not expand sufficiently, and the outlet flow velocity will not reach the target supersonic speed, resulting in the back pressure being inconsistent with the actual turbine outlet; if it is too long, it will increase the flow resistance and device weight, and may affect the effective flow area due to the thickening of the boundary layer.
[0035] In some embodiments, as Figure 1 As shown, to overcome the above-mentioned problems, the length of the diverging section 130 can be determined by the diverging angle and the diameter of the gas outlet of the diverging section 130. For example, the length of the diverging section 130 can be calculated as a trigonometric function of the diameter of the gas outlet of the diverging section 130 and the half-diverging angle. This ensures that the airflow is smoothly accelerated from the throat 120 (sonic speed) to supersonic speed and simulates the flow field characteristics of the turbine outlet. It should be understood that the length of the diverging section 130 refers to the distance from the throat 120 to the outlet of the diverging section 130.
[0036] It should be noted that if Figure 1 As shown, the turbine simulator 100 provided in the exemplary embodiment of the present application includes a removable convergent section 110, a throat section 120, and a divergent section 130. This is done to reduce the service life of components due to the high temperatures of hot runs. This removable design facilitates replacement of damaged components, thus reducing costs. Furthermore, given the varying throat sizes of turbines of different models, the removable throat section 120 allows replacement of different-sized throats based on the turbine's throat size, thereby improving the adaptability of the turbine simulator 100.
[0037] Figure 2 The structure diagram of the convergence section and / or expansion section provided by the exemplary embodiment of the present application is shown. Figure 1 and Figure 2 As shown, in order to adapt to throats 120 of different sizes, the convergent section 110 and / or divergent section 130 of the turbine simulator 100 of the present application can include a multi-layer sleeve structure 140, one end of which is connected to the generator and the other end is connected to the throat 120. The multi-layer sleeve structure 140 also includes multiple detachable sleeves 141 and high-temperature resistant sealing rings 142. The multiple detachable sleeves 141 are sleeved together along the flow direction of the gas. The size of the air inlet or outlet of each detachable sleeve 141 is different, and the inner wall seam of two adjacent detachable sleeves 141 is fixed with a high-temperature resistant sealing ring 142. By providing the multi-layer sleeve structure 140, the convergent section 110 and / or divergent section 130 of the turbine simulator 100 of the present application can adapt to more throats 120 of different sizes.
[0038] For example, when the multi-layer sleeve structure includes a first sleeve and a second sleeve, the first sleeve is connected to the throat, the second sleeve is connected to the generator, and the first sleeve and the second sleeve are stacked together, the first sleeve is sleeved inside the second sleeve, and the first sleeve and the second sleeve can slide relative to each other in the flow direction of the gas. The gas flowing out of the generator enters from the air inlet of the second sleeve, flows through the air outlet of the second sleeve and the air inlet of the first sleeve, and then flows out through the air outlet of the first sleeve. At this time, the air outlet and the throat of the first sleeve are detachably connected. There are many ways to fix the first sleeve and the second sleeve. For example, a fixing method of a slot and a block, a fixing method of bolt fastening, a threaded connection method, and a wedge block fixing method can be used, which are not limited here.
[0039] It should be noted that the diameter of the sleeve to be connected to the throat can be selected based on the diameter of the throat. If the diameter of the smallest sleeve included in the sleeve is smaller than the diameter of the throat, one or more sleeves smaller than the throat diameter can be removed to adapt to throats of different sizes. In addition, since the sleeve structure of the present application is a multiple sleeve arrangement, disassembly is simpler and more efficient.
[0040] Considering that the multi-layer sleeve structure includes two adjacent sleeves, for example, a tiny protrusion will be formed in the contact area between the outer wall of the inner sleeve or the inner wall of the outer sleeve, air flow separation will occur at the protrusion, forming small vortices, which will affect the test results.
[0041] In order to overcome the above problems, in some instances, Figure 3 The schematic diagram of the structure of the high temperature resistant sealing ring provided by the exemplary embodiment of the present application is shown. Figures 1 to 3 As shown, the high temperature resistant sealing ring 142 of the embodiment of the present application includes a sealing side 1421 and a guide side 1422, wherein the guide side 1422 has a slope, and the radial height of the guide side 1422 of the high temperature resistant sealing ring 142 gradually decreases along the opposite direction of the gas flow.
[0042] As a possible implementation, Figure 1 As shown, the turbine simulator 100 may further include an elbow 150, which is detachably connected to the convergent section 110. By designing the elbow 150 to change the direction of the gas flowing out of the generator, the process of gas passing through the generator and entering the turbine is simulated, so that the test results of the turbine simulator 100 of the present application are closer to the test results of the generator and turbine connection.
[0043] In some embodiments, as Figure 1As shown, the turbine simulator 100 further includes a connector 160, which is detachably connected to the elbow 150. The connector 160 can be a flange or other suitable connector 160, without limitation. By using the connector 160 to connect the turbine simulator 100 and the generator, the complex connection, fixing, and disassembly issues associated with using a real turbine are avoided, significantly improving efficiency.
[0044] In some embodiments, according to the above description, during the hot test of the generator, the service life of each component is reduced due to the high gas temperature. Based on this, in order to overcome this problem, Figure 4 The structure of the convergence section provided by the exemplary embodiment of the present application is shown Figure 1 .like Figures 1 to 4 As shown, the convergent section 110 includes a first cavity 111 located within the sidewall of the convergent section 110. A phase change material is disposed within the first cavity 111. The phase change material absorbs heat to reduce the temperature of the convergent section during the generator hot test, thereby increasing the service life of the convergent section 110.
[0045] In some examples, Figure 5 The structure of the convergence section provided by the exemplary embodiment of the present application is shown Figure 2 .like Figures 1 to 5 As shown, the first cavity 111 surrounds the sidewall of the converging section 110 along the direction of gas flow. Alternatively, the first cavity 111 can surround the sidewall of the converging section 110 in a direction parallel to the gas flow direction. Furthermore, a carbon nanotube thermal conductive coating can be sprayed on the inner wall of the converging section 110 to quickly direct heat to the first cavity 111.
[0046] In actual applications, when the generator undergoes a hot run, the high temperature (1000°C) in the convergent section is transferred through the tube wall to the phase change material, causing it to melt from solid to liquid and absorb a large amount of heat (a single cavity can maintain a throat temperature below 800°C for 30 minutes). After the run, the phase change material cools and solidifies naturally.
[0047] In some embodiments, as Figures 1 to 5 As shown, the throat 120 includes a second cavity located in the sidewall of the throat 120. The second cavity contains a phase change material. The second cavity of the throat 120 can be described with reference to the above description of the convergent section 110 and will not be repeated here.
[0048] In some embodiments, as Figures 1 to 5As shown, the expansion section 130 includes a third cavity located within the sidewall of the expansion section 130. The third cavity contains a phase change material. The third cavity of the expansion section 130 can be described with reference to the arrangement of the convergence section 110 described above and will not be repeated here.
[0049] In some embodiments, the phase-change material includes one or more of a gallium-based alloy phase-change material, an aluminum-based alloy phase-change material, or a composite phase-change material. For example, the phase-change material may be a gallium-based alloy phase-change material, an aluminum-based alloy phase-change material, a composite phase-change material, or a gallium-based alloy phase-change material, an aluminum-based alloy phase-change material, or a composite phase-change material, etc., but is not limited thereto. The phase-change materials used in the convergent section, throat section, and divergent section may be the same or different.
[0050] An exemplary embodiment of the present application also provides a generator test system, including a generator and a turbine simulation device provided in the present application, wherein the generator and the turbine simulation device are connected.
[0051] Compared with the prior art, the beneficial effects of the generator test system provided in the embodiment of the present application are the same as those of the above-mentioned turbine simulation device, which will not be elaborated here.
[0052] 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.
[0053] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of this application. Therefore, the scope of protection of this application should be based on the scope of protection of the claims.
Claims
1. A turbine simulation device, characterized in that: The turbine simulation device includes a convergent section, a throat section and a divergent section; The convergent section and the throat are detachably connected, and the cross-sectional area of the convergent section gradually decreases along the flow direction of the gas; One end of the throat is detachably connected to the convergent section, and the other end of the throat is detachably connected to the divergent section. The minimum cross-sectional area of the throat is the same as the sum of the stationary blade areas of the turbine.
2. The turbine simulator according to claim 1, characterized in that: The convergence angle of the convergence section is 15°-30°; and / or, The length of the convergent section is determined by the convergence angle and the diameter of the throat.
3. The turbine simulator according to claim 1, characterized in that: The expansion angle of the expansion section is 10°-15°; and / or, The length of the expansion section is determined by the expansion angle and the diameter of the gas outlet of the expansion section.
4. The turbine simulator according to claim 1, characterized in that: The turbine simulation device further includes an elbow, and the elbow and the convergent section are detachably connected.
5. The turbine simulator according to claim 4, characterized in that: The turbine simulation device further comprises a connecting piece, and the connecting piece and the elbow are detachably connected.
6. The turbine simulator according to claim 1, characterized in that: The convergent section includes a first cavity, the first cavity is located in a side wall of the convergent section, and a phase change material is arranged in the first cavity.
7. The turbine simulator according to claim 1, characterized in that: The throat portion includes a second cavity located in a side wall of the throat portion, and a phase change material is disposed in the second cavity.
8. The turbine simulator according to claim 1, characterized in that: The expansion section includes a third cavity, the third cavity is located in the side wall of the expansion section, and a phase change material is arranged in the third cavity.
9. The turbine simulator according to any one of claims 6 to 8, characterized in that: The phase change material includes one or more of a gallium-based alloy phase change material, an aluminum-based alloy phase change material, or a composite phase change material.
10. A generator commissioning system, characterized in that: It comprises a generator and the turbine simulation device according to any one of claims 1 to 9, wherein the generator and the turbine simulation device are connected.