Supercharger turbine rotating shaft for performance test and test method

Abstract

The invention discloses a supercharger turbine rotating shaft for a performance test and a test method, the supercharger turbine rotating shaft is applied to a turbine performance test, and the supercharger turbine rotating shaft comprises a turbine, a rotor shaft and a shaft end locking nut; the rotor shaft is connected with the rotor shaft through a shaft end locking nut; the turbine comprises a turbine hub; a central through hole is formed in the central position of the turbine hub; a plurality of turbine blades are distributed on the surface of the front side of the turbine hub; the rotor shaft front section and the rotor shaft middle section are provided with rotor shaft bodies; the front end of the rotor shaft body is provided with an external thread section and a mounting shaft section; the mounting shaft section is positioned on the rear side of the external thread section; the mounting shaft section penetrates through the turbine center through hole; the external thread section is matched with the shaft end locking nut to lock the turbine; a positioning step for positioning and supporting a turbine is arranged in the middle of the rotor shaft main body; the method is applied to a turbine performance test, and the design is beneficial to quickly and reliably obtaining turbine blade performance data, so that whether the turbine blade performance reaches a pre-required design index or not is quickly verified, and the turbine design and development timeliness is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of turbochargers, and particularly to a turbocharger turbine rotating shaft for performance tests and a test method. Background Art

[0002] In a traditional engine, power is generated by fuel combustion in a cylinder. Since the amount of fuel input is limited by the amount of air inhaled into the cylinder, the power generated by the engine is also limited. If more output power is desired, only by compressing more air into the cylinder to increase the fuel amount can the combustion work capacity be improved.

[0003] A turbocharger is a mechanical device that can increase the output power of an engine without changing the working efficiency, and at the same time, effectively reduce the fuel consumption rate of the engine. In recent years, engine supercharging technology has developed rapidly, and supercharging technology plays an important role in reducing emissions, increasing power, and restoring plateau performance.

[0004] For a turbocharger, the turbine impeller is the core component of the turbocharger. The turbine uses the energy of the engine exhaust gas to drive the rotation of the turbine rotating shaft. The turbine rotating shaft is a complex part formed by electron beam welding a cast high-temperature alloy turbine and a rotor shaft. Among them, the high-temperature alloy turbine is the key to generating aerodynamic performance, and different designed turbine blade structures will result in different turbine flow performances.

[0005] Currently, the traditional way to obtain turbine performance is through experiments, that is, it is required to manufacture a turbine rotating shaft including turbine blades, and then conduct physical experiments under the conditions of the entire turbocharger. The experiments usually use the engine exhaust gas temperature condition, and the test gas temperature is selected as 600 - 650°C. For the acquisition of experimental data, see Figure 7 As shown, the main work processes include: the first step, the design and manufacture of the turbine casting mold; the second step, based on the turbine blade design data, conduct the casting turbine structure design; the third step, the design and manufacture of the turbine precision casting mold; the fourth step, the precision casting production of the turbine casting; the fifth step, the welding process of the turbine rotating shaft; the sixth step, the shaft processing of the turbine rotating shaft; the seventh step, the whole machine assembly test of the turbine rotating shaft; the eighth step, the acquisition of turbine performance data.

[0006] It can be seen from the above steps that obtaining the performance of turbine blades requires huge time costs and high manufacturing production costs. If it is verified that the turbine blade performance does not meet the design index, a new round of manufacturing experiment cycle will be carried out, and the cost will increase exponentially.

[0007] Therefore, there is an urgent need to develop a technology that can solve the above technical problems. Summary of the Invention

[0008] The object of the present invention is to provide a supercharger turbine rotating shaft for performance testing and a testing method in view of the technical defects existing in the prior art.

[0009] To this end, the present invention provides a supercharger turbine rotating shaft for performance testing, which is applied to turbine performance testing and includes a turbine, a rotor shaft and an end locking nut;

[0010] The rotor shaft is detachably and fixedly connected to the rotor shaft through the end locking nut;

[0011] Among them, the turbine includes a turbine hub;

[0012] The central position of the turbine hub has a central through hole longitudinally and distributively penetrating;

[0013] A plurality of turbine blades are distributively surrounded around the front side surface of the turbine hub;

[0014] Among them, the rotor shaft is of a stepped shaft structure;

[0015] The front section and the middle section of the rotor shaft have a rotor shaft main body;

[0016] The front end of the rotor shaft main body has an external thread section and a mounting shaft section;

[0017] The mounting shaft section is located behind the external thread section;

[0018] The mounting shaft section longitudinally penetrates through the central through hole of the turbine;

[0019] The external thread section is used to lock the turbine together with the end locking nut;

[0020] The middle part of the rotor shaft main body has a positioning step;

[0021] The positioning step is used to position and support the turbine.

[0022] It can be seen from the technical solutions provided by the present invention above that, compared with the prior art, the present invention provides a supercharger turbine rotating shaft for performance testing and a testing method, with scientific design. The present invention is applied to turbine performance testing. Through the design of the present invention, it is beneficial to quickly and reliably obtain the blade performance data of the turbine, and then quickly verify whether the turbine blade performance data meets the pre-required design indexes, significantly saving the time cost of design and development, improving the design and development efficiency of the turbine, and having great practical significance.

[0023] In addition, the present invention is a low-cost and fast technical solution for solving the acquisition of turbine blade performance testing. It can use a low-cost aluminum alloy turbine to replace the traditionally cast turbine to manufacture the turbine rotating shaft, thereby achieving the rapid acquisition of turbine blade performance through testing. Description of the Drawings

[0024] Figure 1 Schematic three-dimensional structure diagram of a supercharger turbine rotating shaft for performance testing provided by the present invention;

[0025] Figure 2 Partial sectional structure diagram of a supercharger turbine rotating shaft for performance testing provided by the present invention;

[0026] Figure 3 Schematic three-dimensional structure diagram of a turbine used in a supercharger turbine rotating shaft for performance testing provided by the present invention;

[0027] Figure 4a Schematic three-dimensional structure diagram of an end locking nut used in a supercharger turbine rotating shaft for performance testing provided by the present invention;

[0028] Figure 4b Front side structure diagram of an end locking nut used in a supercharger turbine rotating shaft for performance testing provided by the present invention;

[0029] Figure 4c Sectional structure diagram of an end locking nut used in a supercharger turbine rotating shaft for performance testing provided by the present invention;

[0030] Figure 5 Side view of a rotor shaft used in a supercharger turbine rotating shaft for performance testing provided by the present invention;

[0031] Figure 6 Working flow chart of a test method for a supercharger turbine rotating shaft for performance testing provided by the present invention;

[0032] Figure 7 Flow chart of a design production verification method for a traditional turbine rotating shaft;

[0033] In the figure, 1 is a turbine, 2 is a rotor shaft, and 3 is an end locking nut;

[0034] 11 is a turbine hub, 12 is a central through hole, 13 is a turbine blade, 14 is a vertical central axis, and 15 is a hub plane structure;

[0035] 131 is a blade inlet edge, and 132 is a blade outlet edge 132;

[0036] 20 is a rotor shaft main body, 21 is an external thread section, 22 is a positioning step, and 23 is an installation shaft section;

[0037] 31 is an end face plane structure, and 32 is an internal thread structure. Detailed implementation manner

[0038] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0039] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. It is 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 orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention.

[0040] In the description of this patent, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", "connected", "set" should be understood in a broad sense. For example, it can be fixedly connected and set, or detachably connected and set, or integrally connected and set. For those of ordinary skill in the art, the specific meanings of the above terms in this patent can be understood according to specific circumstances.

[0041] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality" means two or more unless otherwise specifically defined.

[0042] See Figures 1 to 3 、 Figures 4a to 4c 、 Figures 5 to 6 , the present invention provides a supercharger turbine rotating shaft for performance testing, which is applied to turbine performance testing. It includes a turbine 1, a rotor shaft 2, and an end locking nut 3;

[0043] The rotor shaft 2 is detachably and fixedly connected to the rotor shaft 2 through the end locking nut 3;

[0044] Among them, the turbine 1 includes a turbine hub 11;

[0045] The central position of the turbine hub 11 has a central through hole 12 longitudinally penetrating and distributed;

[0046] A plurality of turbine blades 13 are distributed around the front side surface of the turbine hub 11;

[0047] The plurality of turbine blades 13 are equally spaced along the circumferential direction of the turbine hub 11 with the vertical central axis 14 of the turbine hub 11 as the center;

[0048] Among them, the rotor shaft 2 is a stepped shaft structure;

[0049] The front section and the middle section of the rotor shaft 2 have a rotor shaft main body 20;

[0050] The front end of the rotor shaft main body 20 has an external thread section 21 and a mounting shaft section 23;

[0051] The mounting shaft section 23 is located at the rear side of the external thread section 21;

[0052] The mounting shaft section 23 longitudinally penetrates through the central through hole 12 of the turbine 1;

[0053] The external thread section 21 is used to lock the turbine 1 together with the shaft end lock nut 3;

[0054] The middle part of the rotor shaft main body 20 has a positioning step 22;

[0055] The positioning step 22 is used to position and support the turbine 1.

[0056] In the present invention, specifically, the shapes and sizes of the plurality of turbine blades 13 are exactly the same;

[0057] In the present invention, specifically, for the turbine 1, on the side of each turbine blade 13 away from the turbine hub 11, there is a blade inlet edge 131;

[0058] The rear end of the blade inlet edge 131 is fixedly connected to the front side surface of the turbine hub 11;

[0059] On the side of each turbine blade 13 close to the front end face of the turbine hub 11, there is a blade outlet edge 132;

[0060] The inner end (i.e., the side facing the turbine hub 11) of the blade outlet edge 132 is fixedly connected to the front side surface of the turbine hub 11;

[0061] It should be noted that for the present invention, the turbine blade 13 is a three-dimensional blade with spatial twist, and each turbine blade 13 has a blade inlet edge 131 and a blade outlet edge 132;

[0062] Specifically, one embodiment can be: the blade inlet edge 131 serves as the turbine inlet leading edge, and its shape structure is a structure parallel to the vertical central axis (i.e., the rotation center line) 14 of the turbine hub 11;

[0063] In terms of specific implementation, another embodiment can be as follows: The blade inlet edge 131 serves as the turbine inlet leading edge, and its shape and structure are an inclined structure that is not parallel to the vertical central axis 14 (i.e., the rotation center line) of the turbine hub 11.

[0064] Furthermore, the included angle between the blade inlet edge 131 and the vertical central axis 14 (i.e., the rotation center line) of the turbine hub 11 is 0 to 40 degrees.

[0065] It should be noted that for the present invention, the blade inlet edge 131 serves as the turbine inlet leading edge, and its shape has a parallel or inclined structure along the vertical central axis (i.e., the rotation center line) 14, so that different inlet air flow angle conditions can be obtained.

[0066] In terms of specific implementation, the turbine 1 is preferably an aluminum alloy turbine; the material of the turbine 1 is aluminum alloy, and the processing method is five-axis machine milling. The specific material of the turbine 1 can be selected from high-strength aluminum alloys such as 2618 (2618A) or 2A70.

[0067] In terms of specific implementation, the front end face of the hub 11 is a hub plane structure 15;

[0068] The hub plane structure 15 is used to contact the end face plane structure 31 at the rear side of the shaft end locking nut 3 and the two are connected by a fixed torque.

[0069] In the present invention, in terms of specific implementation, for the rotor shaft 2, the external thread section 21 is used to cooperate with the shaft end locking nut 3 to lock the turbine 1 together. The specific structural design is as follows:

[0070] The external thread of the external thread section 21 is thread-fixedly connected to the internal thread structure 32 (i.e., the internal thread) of the shaft end locking nut 3;

[0071] In terms of specific implementation, the diameter of the positioning step 22 is larger than the diameter of the central through hole 12 of the turbine 1;

[0072] The front end face of the positioning step 22 is a plane.

[0073] In terms of specific implementation, the mounting shaft section 23 is fitted and installed with the central through hole 12 of the turbine 1;

[0074] The mounting shaft section 23 and the central through hole 12 of the turbine 1 are in an interference fit.

[0075] It should be noted that the dimensions of the mounting shaft section 23 and the dimensions of the central through hole 12 of the turbine 1 have an interference fit tolerance relationship.

[0076] Specifically, the material of the rotor shaft 2 is alloy steel, and the specific material can be 40Cr or 42CrMo alloy steel. Its end has a threaded structure (i.e., the external thread section 21), and at the same time has a mounting shaft section 23 that matches the central through hole of the turbine and a positioning step 22 for mounting the turbine.

[0077] In the present invention, specifically, the shaft-end locking nut 3 includes an end face planar structure 31 at the rear side and an internal thread structure 32 at the central position.

[0078] The internal thread structure 32 is an internal thread hole and vertically penetrates through the shaft-end locking nut 3.

[0079] It should be noted that the internal thread structure 32 of the shaft-end locking nut 3 is locked and connected with the threaded structure (i.e., the external thread section 21) on the rotor shaft 2, so as to fix the turbine 1 passing through the rotor shaft 2.

[0080] Specifically, the material of the shaft-end locking nut 3 is alloy steel, and the specific material can be 40Cr or 42CrMo alloy steel. It has an end face planar structure 31, and by applying an axial rotation torque, an effective fixed position connection between the turbine and the rotor shaft can be achieved, meeting the requirement that there is no relative displacement between the turbine and the rotor shaft when the turbine rotating shaft rotates at a high speed.

[0081] It should be noted that the shaft-end locking nut 3 is locked and connected with the thread of the rotor shaft 2 (specifically the external thread section 21), so as to fix the turbine 1 with a central through hole passing through the rotor shaft, enabling the overall supercharger turbine rotating shaft to meet the requirement of high-speed rotation.

[0082] In the present invention, specifically, the present invention provides a supercharger turbine rotating shaft, which is applied to low-temperature performance tests. The test temperature range required for this low-temperature performance test is 50 - 200 °C.

[0083] See Figure 6 As shown, in order to verify the performance of a supercharger turbine rotating shaft provided by the present invention for performance tests, the present invention also provides a test method for the supercharger turbine rotating shaft for performance tests. This method is the working process for the design and production verification of the turbine rotating shaft, and it includes the following steps:

[0084] The first step is to construct the blade profile of the turbine blade 13 of the turbine 1; that is, the design of the turbine impeller blade profile.

[0085] The second step is to obtain a three-dimensional model of the turbine 1 made of aluminum alloy material based on the blade profile of the turbine blade 13 constructed in the first step; that is, based on the turbine blade design data, the aluminum turbine structure design is carried out.

[0086] It should be noted that in the first and second steps, specifically, a computer can be used to design the airfoil (i.e., the three-dimensional model) of the turbine blade 13 of the turbine 1 in the traditional manner and obtain the three-dimensional model of the turbine 1. For example, the conventional design method of a traditional turbine impeller can be as follows: First, according to the requirements of aerodynamic performance, design the control curves of the turbine shroud and the hub, and rotate to form the hub and shroud surfaces to meet the strength requirements of the turbine. Then, according to the aerodynamic performance of the turbine, design the corresponding turbine blades. The turbine blades are connected to the turbine hub surface, and the blade root and the hub surface are transitioned by an arc to finally form the overall structure of the turbine. Of course, other existing conventional design methods can also be used, which will not be elaborated here.

[0087] In the third step, according to the three-dimensional model of the turbine 1 obtained in the second step, the turbine 1 made of aluminum alloy material is obtained through milling, and the rotor shaft 2 and the shaft-end locking nut 3 are processed.

[0088] It should be noted that for the present invention, for the milling of the turbine made of aluminum alloy material, the turbine processing method is: five-axis machine tool milling, and the materials can be selected from high-strength aluminum alloys such as 2618 (2618A) or 2A70; the processing of the rotor shaft 2 and the processing operation of the shaft-end locking nut 3 can both adopt traditional machining methods, and the materials can be selected from alloy steels such as 40Cr or 42CrMo, which will not be elaborated here.

[0089] In the fourth step, the turbine 1 made of aluminum alloy material obtained by processing, the rotor shaft 2 obtained by processing, and the shaft-end locking nut 3 are assembled together to obtain the finished product of the supercharger turbine rotating shaft. Then, the supercharger turbine rotating shaft is assembled into a turbocharger, and the turbocharger is used as a low-temperature test machine for the turbocharger; that is, the fourth step is to complete the combined assembly of the turbine rotating shaft and the assembly of the turbine rotating shaft into the turbocharger.

[0090] It should be noted that for the present invention, the turbine rotating shaft with an aluminum alloy turbine is used to replace the installation position of the traditional turbine rotating shaft in the original turbocharger to complete the assembly of the low-temperature performance supercharger test machine.

[0091] In the fifth step, a turbocharger low-temperature test bench is used to test the performance of the supercharger turbine rotating shaft in the turbocharger low-temperature test machine to obtain the performance data of the supercharger turbine rotating shaft.

[0092] It should be noted that a turbocharger low-temperature test bench is used to test the supercharger turbine rotating shaft in the turbocharger low-temperature test machine by using the mature and conventional test methods of the existing technology. Since the test machine is equipped with a turbine rotating shaft with an aluminum alloy turbine, the laboratory data of the turbine performance is finally obtained.

[0093] It should be noted that here, the turbine performance test referred to in the present invention is a turbine flow characteristic test. This test measures the physical property data of the gas before and after passing through the turbine blade channels (including: gas temperature at the inlet position, gas pressure at the inlet position, gas temperature at the outlet position, gas pressure at the outlet position, mass flow rate of the gas passing through the channel, etc.). Through thermodynamic formula calculation, parameters reflecting the turbine performance such as expansion ratio, similarity flow rate, and efficiency passing through the turbine can be obtained, which can be used to evaluate the performance of different turbines. Furthermore, it can be used as the basis for the design optimization of turbine blades.

[0094] In the present invention, the low-temperature performance test is different from the traditional high-temperature performance test (600 - 650 °C). The test temperature is selected as (50 - 200 °C). Under this temperature condition, the aluminum alloy turbine can operate normally, and the turbine flow characteristic test can be completed to obtain turbine performance data.

[0095] Specifically, the turbine performance test is completed on a dedicated supercharger performance test bench that is mature and well-known in the prior art. The test bench can precisely control the turbine inlet temperature, use hot air to drive the turbine, and at the same time, the test bench is equipped with corresponding sensors at the inlet and outlet of the turbine channel to measure parameters such as temperature, pressure, and flow rate. The turbine inlet meets the requirements of the low-temperature test inlet temperature, and the low-temperature inlet condition can be obtained by using an electric heating air warming device or natural gas combustion heating temperature control, etc. The turbine performance test is completed using a stable low-temperature inlet condition.

[0096] Specifically, the turbine performance test is carried out under preset rotational speed conditions. The test rotational speeds are selected from 5 to 6 equal rotational speed lines from low to high. The measurement points at different rotational speeds are selected between the maximum flow rate point (close to the choking flow rate) and the minimum flow rate point (close to the surge flow rate) of the compressor. For each rotational speed line, 6 - 7 points are evenly selected according to the flow rate size, and parameters such as temperature, pressure, and mass flow rate at the inlet and outlet of the turbine are measured. Finally, turbine performance parameters such as expansion ratio, similarity flow rate, and efficiency are calculated and obtained.

[0097] For the present invention, specifically, by analyzing and comparing the low-temperature performance data of different turbine blades, the performance advantages and disadvantages of different turbines can be conveniently confirmed, which can be used as an important basis for the design of turbine blades.

[0098] Compared with the prior art, the supercharger turbine shaft and test method for performance test provided by the present invention can realize the low-cost acquisition of turbine blade performance experiments and have the following beneficial effects:

[0099] 1. The turbine shaft of the present invention can use the same turbine blade design data as the turbine shaft manufactured by traditional casting turbines to process the aluminum alloy impeller. The test performance of the aluminum alloy blades can replace the test performance of the casting turbines;

[0100] 2. The turbine rotating shaft of the present invention can replace the original turbine rotating shaft for supercharger assembly without any modification and can be replaced in situ.

[0101] 3. The turbine rotating shaft of the present invention uses an aluminum alloy turbine for low-temperature performance tests. Since the aluminum alloy has a relatively low service temperature, the temperature for turbine performance testing needs to be below 250°C. Usually, the turbine test temperature is selected between 50 - 200°C. According to the principle of thermodynamic fluid similarity, the performance of the turbine blades is the same during high-temperature and low-temperature tests. Therefore, the aluminum alloy turbine rotating shaft for low-temperature testing of the present invention can replace the conventionally cast turbine rotating shaft for high-temperature testing.

[0102] 4. The turbine rotating shaft of the present invention uses a combination of an aluminum alloy turbine and a shaft-end nut connection method for the turbine rotating shaft, reducing time-consuming and costly manufacturing processes such as the manufacture of the casting turbine mold, the precision casting process of the turbine, and the welding process of the turbine rotating shaft. The production cost is low, and the manufacturing cycle is significantly shortened. This can well meet the need to save the actual performance verification time of the turbine blades, accelerate the performance development process of the turbine blades, reduce the production and manufacturing cost of the turbine. Compared with the traditional turbine verification cycle, the development efficiency of the turbine of the present invention is increased by 80%, and the verification cost is reduced by 90%. The turbine blades verified by the aluminum alloy turbine rotating shaft can be used for the production of the turbine rotating shaft for the final production of superalloys casting turbines.

[0103] 5. The turbine rotating shaft of the present invention is mainly used for obtaining turbine blade performance data and during the turbine blade performance verification stage. Due to the service temperature limitation of the aluminum alloy turbine, it cannot replace the turbine rotating shaft of the conventionally cast turbine for the final use of the supercharger. The turbine of the present invention can be used for low-temperature performance tests, accelerating the performance design progress of the supercharger, and is a means to improve the design cycle of the supercharger turbine performance.

[0104] 6. As an extension of the present invention, the aluminum alloy turbine can be processed with titanium aluminide. The use of a titanium aluminide processed turbine further expands the application value of the turbine rotating shaft structure of the present invention. Since the titanium aluminide has a high service temperature and can meet the use under high-temperature conditions, it can replace the entire turbine rotating shaft and has the technical advantages of light weight and small moment of inertia. Therefore, in some product application scenarios, the titanium aluminide turbine rotating shaft has further application value, and these applications also reflect the extended value of the present invention.

[0105] In summary, compared with the prior art, the present invention provides a supercharger turbine rotating shaft and a test method for performance tests, with scientific design, which is conducive to quickly and reliably obtaining the blade performance data of the turbine, and then quickly verifying whether the turbine blade performance data meets the pre-set design indicators, significantly saving time costs, improving the design and development efficiency of the turbine, and having great practical significance.

[0106] In addition, the present invention is a low-cost and fast technical solution for obtaining the performance test of turbine blades. It can use a low-cost aluminum alloy turbine to replace the conventionally cast turbine to manufacture the turbine rotating shaft, thereby achieving the rapid acquisition of the performance of turbine blades through tests.

[0107] Therefore, a supercharger turbine rotating shaft provided by the present invention has an aluminum alloy turbine, can replace the turbine rotating shaft of the conventional design, is used for the performance test of low-temperature turbines, has a low production cost and a short production cycle, can significantly improve the development progress of the performance of turbine blades, and has great economic benefits.

[0108] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. A supercharger turbine shaft for performance testing, characterized in that, Applied in the turbine performance test, it includes a turbine (1), a rotor shaft (2) and an end locking nut (3); The rotor shaft (2) is detachably and fixedly connected to the rotor shaft (2) through the end locking nut (3); Among them, the turbine (1) includes a turbine hub (11); The central position of the turbine hub (11) has a central through hole (12) longitudinally penetrating and distributed; A plurality of turbine blades (13) are distributed around the front side surface of the turbine hub (11); Among them, the rotor shaft (2) is a stepped shaft structure; The front section and the middle section of the rotor shaft (2) have a rotor shaft main body (20); The front end of the rotor shaft main body (20) has an external thread section (21) and a mounting shaft section (23); The mounting shaft section (23) is located at the rear side of the external thread section (21); The mounting shaft section (23) longitudinally penetrates through the central through hole (12) of the turbine (1); The external thread section (21) is used to lock the turbine (1) together with the end locking nut (3); The middle part of the rotor shaft main body (20) has a positioning step (22); The positioning step (22) is used to position and support the turbine (1).

2. The supercharger turbine rotating shaft for performance test according to claim 1, characterized in that, The shapes and sizes of the plurality of turbine blades (13) are exactly the same; For the turbine (1), each turbine blade (13) is provided with a blade inlet edge (131) on the side far from the turbine hub (11); The rear end of the blade inlet edge (131) is fixedly connected to the front side surface of the turbine hub (11); Each turbine blade (13) is provided with a blade outlet edge (132) on the side close to the front end face of the turbine hub (11); The inner end of the blade outlet edge (132) is fixedly connected to the front side surface of the turbine hub (11).

3. The supercharger turbine rotating shaft for performance testing according to claim 2, characterized in that, The blade inlet edge (131) serves as the turbine inlet leading edge, and its shape structure is a structure parallel to the vertical central axis (14) of the turbine hub (11); Or, The blade inlet edge (131) serves as the turbine inlet leading edge, and its shape structure is an inclined structure not parallel to the vertical central axis (14) of the turbine hub (11); The included angle between the blade inlet edge (131) and the vertical central axis (14) of the turbine hub (11) is 0 to 40 degrees.

4. The supercharger turbine shaft for performance testing according to claim 1, wherein The material of the turbine (1) is aluminum alloy, and the processing method is five-axis machine tool milling; The material of the rotor shaft (2) is alloy steel; The material of the end locking nut (3) is alloy steel; The supercharger turbine rotating shaft is applied in the low-temperature performance test, and the test temperature range required by this low-temperature performance test is 50 to 200 °C.

5. The supercharger turbine rotating shaft for performance test according to claim 4, characterized in that, The material of the turbine (1) is selected from 2618 or 2A70 aluminum alloy; The material of the rotor shaft (2) is selected from 40Cr or 42CrMo alloy steel; The material of the end locking nut (3) is selected from 40Cr or 42CrMo alloy steel.

6. The supercharger turbine rotating shaft for performance test according to claim 1, wherein The front end face of the hub (11) is a hub plane structure (15); The hub plane structure (15) is used to contact the end face plane structure (31) at the rear side of the end locking nut (3) and the two are connected with a fixed torque.

7. The supercharger turbine rotating shaft for performance test according to claim 1, wherein For the rotor shaft (2), the external thread section (21) is used to lock the turbine (1) together with the end locking nut (3), and the specific structural design is as follows: The external thread section (21) has an external thread that is threadedly and fixedly connected to the internal thread structure (32) of the shaft end locking nut (3).

8. The supercharger turbine rotating shaft for performance testing according to claim 7, characterized in that, The diameter of the positioning step (22) is greater than the diameter of the central through hole (12) of the turbine (1); The front end face of the positioning step (22) is a flat surface; The mounting shaft section (23) is fitted and mounted with the central through hole (12) of the turbine (1); The mounting shaft section (23) and the central through hole (12) of the turbine (1) are in an interference fit.

9. The supercharger turbine rotating shaft for performance test according to claim 1, characterized in that, The shaft end locking nut (3) includes an end face flat structure (31) at the rear side and an internal thread structure (32) at the central position; The internal thread structure (32) is an internal thread hole and vertically penetrates through the shaft end locking nut (3).

10. A test method for a supercharger turbine shaft for performance testing according to any one of claims 1 to 9, characterized in that, It includes the following steps: First step, construct the blade profile of the turbine blade (13) of the turbine 1; Second step, based on the blade profile of the turbine blade (13) of the turbine (1) constructed in the first step, obtain the three-dimensional model of the turbine (1) made of aluminum alloy material; Third step, according to the three-dimensional model of the turbine (1) obtained in the second step, obtain the turbine (1) made of aluminum material through milling, and process to obtain the rotor shaft (2) and the shaft end locking nut (3); Fourth step, assemble the processed turbine (1) made of aluminum alloy material, the processed rotor shaft (2) and the shaft end locking nut (3) together to obtain the finished turbocharger turbine rotating shaft, then assemble this turbocharger turbine rotating shaft into a turbocharger, and use this turbocharger as a turbocharger low-temperature test machine; Fifth step, use the turbocharger low-temperature test bench to conduct performance tests on the turbocharger turbine rotating shaft in the turbocharger low-temperature test machine to obtain the performance data of the turbocharger turbine rotating shaft.

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