Method and device for measuring interstage parameters of double-rotor turbine and method for obtaining matching characteristics

Abstract

The invention belongs to the field of power systems, and particularly relates to a double-rotor turbine interstage parameter measuring method and device and a matching characteristic obtaining method.The double-rotor turbine interstage parameter measuring method comprises the steps that a high-pressure turbine rotor test is conducted, a first measuring probe measures and obtains a first performance parameter, and a second measuring probe measures and obtains a second performance parameter; the second measuring probe measures to obtain a second performance parameter; obtaining a corresponding relation of inlet and outlet performance parameters of the high-pressure turbine according to the first performance parameter and the second performance parameter; a double-rotor turbine test is carried out, a fourth performance parameter is obtained through measurement of the first measurement probe, and a third performance parameter is obtained through measurement of the third measurement probe; according to the testing method, the corresponding relation between the parameters of the high-pressure turbine inlet and the interstage parameters is obtained through measurement, and therefore the accuracy of the obtained interstage parameters of the double-rotor turbine is improved.

Description

Technical Field

[0001] This invention belongs to the field of power systems, and specifically relates to a method, device, and method for obtaining matching characteristics of interstage parameters of a dual-rotor turbine. Background Technology

[0002] In power systems such as aero-engines and industrial gas turbines, dual-rotor turbines achieve efficient conversion of thermal energy into mechanical energy through the coordinated work of high-pressure turbine rotors and low-pressure rotors; therefore, obtaining the speed matching and efficiency characteristics of the high-pressure rotor and the low-pressure rotor is a key aspect of turbine system performance optimization.

[0003] Speed ​​matching and efficiency characteristics are closely related to the inlet and outlet performance parameters of the high-pressure turbine rotor and the low-pressure rotor. Most performance parameters need to be measured by setting corresponding probes at the inlet and outlet of the high-pressure turbine rotor and the low-pressure rotor. However, for a compact dual-rotor turbine, the axial distance between the high-pressure turbine rotor and the low-pressure rotor is extremely small, making it difficult to arrange probes and other measuring devices between the high-pressure turbine rotor and the low-pressure rotor. Therefore, it is difficult to accurately measure the interstage parameters of the dual-rotor turbine.

[0004] In view of this, the present invention is hereby proposed. Summary of the Invention

[0005] To address the technical problems existing in the prior art, this invention provides a method, apparatus, and method for obtaining matching characteristics of interstage parameters of a dual-rotor turbine. The experimental method of this invention improves the accuracy of the obtained interstage parameters of the dual-rotor turbine by obtaining the correspondence between the parameters at the high-pressure turbine inlet and the interstage parameters through measurement.

[0006] This invention includes the following technical solutions: The first aspect of this invention provides a method for measuring interstage parameters of a dual-rotor turbine, comprising the following steps: A high-pressure turbine is assembled in the flow channel of the casing; a first measuring probe is installed at the inlet of the high-pressure turbine rotor in the flow channel; a second measuring probe is installed at the outlet of the high-pressure turbine rotor in the flow channel; and a support baffle is assembled at the installation position of the low-pressure turbine rotor in the flow channel. A high-pressure turbine rotor test was conducted. The first measurement probe was used to measure and obtain the first performance parameter, and the second measurement probe was used to measure and obtain the second performance parameter. The correspondence between the inlet and outlet performance parameters of the high-pressure turbine is obtained based on the first and second performance parameters. Remove the support baffle and the second measuring probe, assemble the low-pressure turbine in the flow channel of the casing, and install the third measuring probe at the outlet of the low-pressure turbine rotor. A dual-rotor turbine test was conducted, and the fourth performance parameter was obtained by measuring the first measurement probe and the third performance parameter was obtained by measuring the third measurement probe. The interstage parameters of the dual-rotor turbine are obtained based on the aforementioned correspondence and the fourth performance parameter.

[0007] Furthermore, the first measuring probe includes a pressure probe and a temperature probe; and / or the second measuring probe includes a pressure probe and a temperature probe; and / or the third measuring probe includes a pressure probe and a temperature probe.

[0008] Furthermore, multiple pressure probes are provided; and / or multiple temperature probes are provided.

[0009] Furthermore, the first measuring probe is disposed at the same cross section of the flow channel; and / or the second measuring probe is disposed at the same cross section of the flow channel; and / or the third measuring probe is disposed at the same cross section of the flow channel.

[0010] Furthermore, it also includes the following steps: A static pressure measurement hole is made on the outer wall of the casing, and a static pressure measurement probe is installed in the static pressure measurement hole; wherein, the position of the static pressure measurement hole corresponds to the position of the second measurement probe; During the high-pressure turbine rotor test: the first measuring probe measures the first performance parameter, the second measuring probe measures the second performance parameter, and the static pressure measuring probe measures the first interstage static pressure. The correspondence between the inlet and outlet performance parameters of the high-pressure turbine is obtained based on the first performance parameter, the second performance parameter, and the interstage static pressure. During the dual-rotor turbine test: the first measuring probe measures the fourth performance parameter, the third measuring probe measures the third performance parameter, and the static pressure measuring probe measures the second stage static pressure. The interstage parameters of the dual-rotor turbine are obtained based on the aforementioned correspondence, the fourth performance parameter, and the static pressure between the second stage.

[0011] A second aspect of the present invention provides a dual-rotor turbine stage parameter measuring device for implementing the measurement method described above. The measuring device includes a casing, a high-pressure turbine, a low-pressure turbine, and a support baffle. The casing includes a first casing, a second casing, a third casing, and a fourth casing that are sequentially detachably connected. The high-pressure turbine, the low-pressure turbine, and the support baffle are all installed inside the casing.

[0012] Furthermore, the detachable connection is achieved using bolts and nuts.

[0013] A third aspect of the present invention provides a method for obtaining matching characteristics of a dual-rotor turbine, comprising the measurement method described above, and further comprising the following steps: The matching characteristics of the dual-rotor turbine are obtained based on the fourth performance parameter, the third performance parameter, and the interstage parameters of the dual-rotor turbine.

[0014] Furthermore, the dual-rotor turbine matching characteristics include turbine efficiency and reduced rotational speed; Turbine efficiency includes high-pressure turbine efficiency, low-pressure turbine efficiency, and dual-rotor turbine efficiency; equivalent speed includes high-pressure turbine equivalent speed and low-pressure turbine equivalent speed.

[0015] Furthermore, the turbine efficiency is obtained based on the rotor's actual output power, airflow mass flow rate, adiabatic index, mechanical efficiency, gas constant, fourth performance parameter, third performance parameter, and interstage parameters of the dual-rotor turbine. The reduced rotational speed is obtained based on the fourth performance parameter, the interstage parameters of the dual-rotor turbine, and the physical rotational speed of the turbine rotor.

[0016] By adopting the above technical solution, the present invention has the following advantages: 1. The test method of the present invention improves the accuracy of the obtained interstage parameters of the dual-rotor turbine by obtaining the correspondence between the parameters of the high-pressure turbine inlet and the interstage parameters through measurement.

[0017] 2. This invention utilizes a modular design for the dual-rotor turbine test device, along with a segmented casing design, allowing for assembly and disassembly as needed. This enables single-rotor high-pressure turbine tests and dual-rotor counter-rotating turbine tests without altering the main structure, thereby obtaining accurate interstage parameters.

[0018] 3. This invention can obtain a quantitative relationship between the speed matching and efficiency characteristics of a dual-rotor turbine.

[0019] 4. This invention obtains the quantitative relationship between interstage pressure ratio parameters, high-pressure rotor and low-pressure rotor speed matching and efficiency characteristics, further enhancing the guiding significance for dual-rotor turbine design and effectively improving the design level.

[0020] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a flowchart illustrating a method for measuring interstage parameters of a dual-rotor turbine in an embodiment of the present invention. Figure 2 This is a schematic diagram of the structure of a dual-rotor turbine stage parameter measuring device according to an embodiment of the present invention. Figure 1 ; Figure 3 This is a schematic diagram of the structure of a dual-rotor turbine stage parameter measuring device according to an embodiment of the present invention. Figure 2 ; Figure 4 This is a schematic diagram of the supporting baffle in an embodiment of the present invention; Figure 5 This is a front view of the supporting baffle in an embodiment of the present invention; Figure 6 for Figure 5 Sectional view along axis AA; In the diagram, 10-casing, 11-first casing, 12-second casing, 13-third casing, 14-fourth casing, 20-high pressure turbine, 21-high pressure turbine shaft system, 22-high pressure turbine rotor, 30-low pressure turbine, 31-low pressure turbine shaft system, 32-low pressure turbine rotor, 40-support baffle, 41-bottom baffle, 42-side annular baffle. Detailed Implementation

[0023] The following description provides many different embodiments or examples for implementing various features of the invention. The elements and arrangements described in the specific examples below are only for concise expression of the invention and are merely examples, not intended to limit the invention.

[0024] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] The 1+1 / 2 counter-rotating turbine (1 refers to the turbine stage, which includes one guide vane and one moving vane; 1 / 2 refers to the absence of guide vanes and only one moving vane. This is a common structural form of dual-rotor turbines: the high-pressure turbine has both guide vanes and moving vanes, while the low-pressure turbine only has moving vanes and no guide vanes. This structure is very compact, making it impossible to place probes between stages). Due to the limited space between the high-pressure and low-pressure rotors, it is impossible to arrange measurement probes and measure the interstage parameters (including total temperature and total pressure parameters) between the high-pressure turbine rotor 22 and the low-pressure turbine rotor 32. To measure the interstage parameters, the distance between the high-pressure turbine rotor 22 and the low-pressure turbine rotor 32 can be increased, adding a measurement section between the stages. However, this method alters the original structure of the dual-rotor turbine, resulting in deviations between the experimental results and the actual design, leading to poor accuracy in the measured interstage parameters. Therefore, this invention provides a method for measuring interstage parameters of a dual-rotor turbine to improve the accuracy of the measured interstage parameters.

[0026] The first aspect of this embodiment provides a method for measuring interstage parameters of a dual-rotor turbine, including the following steps: A high-pressure turbine 20 is assembled in the flow channel of the casing 10; a first measuring probe is installed at the inlet of the high-pressure turbine rotor 22 in the flow channel; a second measuring probe is installed at the outlet of the high-pressure turbine rotor 22 in the flow channel; and a support baffle 40 is assembled at the location where the low-pressure turbine rotor 32 is installed in the flow channel. A high-pressure turbine rotor 22 test was conducted. The first performance parameter was obtained by measuring the first measuring probe, and the second performance parameter was obtained by measuring the second measuring probe. The correspondence between the inlet and outlet performance parameters of the high-pressure turbine 20 is obtained based on the first and second performance parameters; Remove the support baffle 40 and the second measuring probe, assemble the low-pressure turbine 30 in the flow channel of the casing 10, and install the third measuring probe at the outlet of the low-pressure turbine rotor 32. A dual-rotor turbine test was conducted, and the fourth performance parameter was obtained by measuring the first measurement probe and the third performance parameter was obtained by measuring the third measurement probe. The interstage parameters of the dual-rotor turbine are obtained based on the aforementioned correspondence and the fourth performance parameter.

[0027] In some embodiments, the first measuring probe includes a pressure probe and a temperature probe; and / or the second measuring probe includes a pressure probe and a temperature probe; and / or the third measuring probe includes a pressure probe and a temperature probe. When only a pressure probe and a temperature probe are provided, the correspondence between the inlet and outlet performance parameters of the high-pressure turbine 20, obtained based on the first and second performance parameters, is the correspondence between the pressure and temperature at the inlet and outlet of the high-pressure turbine 20.

[0028] In some embodiments, multiple pressure probes are provided; and / or multiple temperature probes are provided. It should be understood that multiple pressure and temperature probes can be provided for the first measuring probe, multiple pressure and temperature probes for the second measuring probe, and multiple pressure and temperature probes for the third measuring probe. Providing multiple pressure and temperature probes can improve the accuracy of the obtained parameters. For example, four pressure probes and four temperature probes are provided for the first, second, and third measuring probes. It should be noted that the number of pressure and temperature probes for the first, second, and third measuring probes is not limited to be equal. In some embodiments, the first measuring probes located on the same cross-section are arranged circumferentially, for example, one probe every 90°, four probes per circumference; the second measuring probes located on the same cross-section are arranged circumferentially, for example, one probe every 90°, four probes per circumference; the third measuring probes located on the same cross-section are arranged circumferentially, for example, one probe every 90°, four probes per circumference; this allows for more accurate measurement of all information within the flow channel, resulting in more accurate calculation results. It should be noted that the arrangement of setting one pressure probe for each of the first, second, and third measuring probes, and one temperature probe for each of the first, second, and third measuring probes, should also be within the scope of protection of this invention.

[0029] In some embodiments, the first measuring probe is disposed on the same cross-section of the flow channel; and / or the second measuring probe is disposed on the same cross-section of the flow channel; and / or the third measuring probe is disposed on the same cross-section of the flow channel. It should be understood that the pressure probe and temperature probe of the first measuring probe are both disposed on the same cross-section, the pressure probe and temperature probe of the second measuring probe are both disposed on the same cross-section, and the pressure probe and temperature probe of the third measuring probe are both disposed on the same cross-section. Distributing them on the same cross-section improves the accuracy of the quantization calculation. It should be noted that this cross-section is perpendicular to the axis of the high-pressure turbine 20 of the casing 10.

[0030] For example, such as Figure 2 , Figure 3 As shown, the first measuring probe is set at the 0-0 section position, the second measuring probe is set at the 1-1 section position, and the third measuring probe is set at the 2-2 section position.

[0031] Of course, methods where the probes are not placed on the same cross section should also be within the scope of protection of this invention. When they are not placed on the same cross section, the temperature probe and the pressure probe can be placed on two separate cross sections, with the two cross sections as close as possible and not too far apart. In summary, if the flow area of ​​the channel is large, they should be placed on the same cross section, so that the probe has little impact on the flow area of ​​the channel. If the flow area of ​​the channel is small, they should be arranged on two cross sections, but these two cross sections need to be very close. The purpose of both is to make the measurement results more accurate and to minimize interference with the flow channel.

[0032] Since only the turbine inlet temperature and pressure are measured, the turbine's state is not entirely unique; there is a situation where, under different turbine operating conditions, the turbine inlet temperature and pressure are the same, but the outlet temperature and pressure are different. Therefore, an additional parameter must be added to ensure the uniqueness of the state; thus, the following steps are also included: A static pressure measuring hole is made on the outer wall of the casing 10, and a static pressure measuring probe is installed in the static pressure measuring hole; wherein, the position of the static pressure measuring hole corresponds to the position of the second measuring probe; During the high-pressure turbine rotor 22 test: the first measuring probe measures the first performance parameter, the second measuring probe measures the second performance parameter, and the static pressure measuring probe measures the first interstage static pressure. The correspondence between the inlet and outlet performance parameters of the high-pressure turbine 20 is obtained based on the first performance parameter, the second performance parameter, and the interstage static pressure. During the dual-rotor turbine test: the first measuring probe measures the fourth performance parameter, the third measuring probe measures the third performance parameter, and the static pressure measuring probe measures the second stage static pressure. The interstage parameters of the dual-rotor turbine are obtained based on the aforementioned correspondence, the fourth performance parameter, and the second-stage interstage static pressure. Specifically, this refers to the correspondence between the inlet pressure and temperature of the high-pressure turbine 20 and the outlet pressure, temperature, and interstage static pressure.

[0033] By measuring the interstage static pressure, the turbine's operating state is uniquely determined given that the turbine inlet temperature, pressure, and interstage static pressure are fixed; this can further improve the accuracy of the final obtained interstage parameters of the dual-rotor turbine.

[0034] The second aspect of this embodiment provides a dual-rotor turbine stage parameter measuring device for implementing the measurement method described above, such as... Figure 2 , Figure 3 As shown, the measuring device includes a housing 10, a high-pressure turbine 20, a low-pressure turbine 30, and a support baffle 40; the housing 10 includes a first housing 11, a second housing 12, a third housing 13, and a fourth housing 14 that are connected in sequence and can be detached from each other, and the high-pressure turbine 20, the low-pressure turbine 30, and the support baffle 40 are all used to be installed inside the housing 10.

[0035] For example, such as Figure 1 As shown, the high-pressure turbine 20 includes a high-pressure turbine shaft system 21 and a high-pressure turbine rotor 22, and the low-pressure turbine 30 includes a low-pressure turbine shaft system 31 and a low-pressure turbine rotor 32. During the high-pressure turbine rotor 22 test, the low-pressure turbine 30 is not installed. However, without the low-pressure turbine 30 structure installed, gas will flow towards... Figure 2 The airflow flows in the direction of the arrow, which will affect the accuracy of the measurement. Therefore, a support baffle 40 is installed at the position where the low-pressure turbine rotor 32 is installed so that the airflow will only flow along the original flow path.

[0036] In some embodiments, the detachable connection is achieved using bolts and nuts. This facilitates installation and disassembly during testing, and has the advantage of improving testing convenience and efficiency. Examples include... Figure 1 , Figure 2 As shown, the connection positions of the first casing 11, the second casing 12, the third casing 13 and the fourth casing 14 are all provided with flanges, which are fixedly connected by bolts and nuts.

[0037] For example, such as Figures 4-5 As shown, Figure 4 A schematic diagram of the structure supporting the baffle 40; Figure 5 Front view of the supporting baffle 40; Figure 6 This is a cross-sectional view of the support baffle 40; as shown in the figure, the support baffle 40 is provided with a ring of threaded holes, which can ensure that the support baffle 40 and the housing 10 are fixedly connected by bolts. Figure 6 In the middle, the cross-section of the support baffle 40 is a U-shaped structure, that is, the support baffle 40 includes a bottom baffle 41 and a side annular baffle 42; this makes the airflow flow only along the original flow channel.

[0038] The third aspect of this embodiment provides a method for obtaining matching features of a dual-rotor turbine, including the measurement method described above, and further including the following steps: The matching characteristics of the dual-rotor turbine are obtained based on the fourth performance parameter, the third performance parameter, and the interstage parameters of the dual-rotor turbine.

[0039] In some embodiments, the dual-rotor turbine matching characteristics include turbine efficiency and reduced rotational speed; Among them, turbine efficiency includes high-pressure turbine 20 efficiency, low-pressure turbine 30 efficiency and dual-rotor turbine efficiency; equivalent speed includes high-pressure turbine 20 equivalent speed and low-pressure turbine 30 equivalent speed.

[0040] In some embodiments, the turbine efficiency is obtained based on the rotor's actual output power, airflow mass flow rate, adiabatic index, mechanical efficiency, gas constant, fourth performance parameter, third performance parameter, and interstage parameters of the dual-rotor turbine. The reduced rotational speed is obtained based on the fourth performance parameter, the interstage parameters of the dual-rotor turbine, and the physical rotational speed of the turbine rotor.

[0041] In some embodiments, the turbine efficiency is expressed by the formula The equivalent rotational speed is expressed by the formula. express.

[0042] in, For airflow mass flow rate, The gas constant is... The adiabatic index, For mechanical efficiency.

[0043] For example, when you want to obtain the turbine efficiency and equivalent speed of a high-pressure turbine: This represents the actual output power of the high-pressure turbine. The inlet temperature of the high-pressure turbine (i.e., the temperature or average temperature in the fourth performance parameter; when multiple temperature probes are set, the inlet temperature of the high-pressure turbine is the average value of the probe values ​​of the multiple temperature probes). It is the ratio of the total inlet pressure to the total outlet pressure (i.e., the ratio of the pressure or average pressure in the fourth performance parameter to the pressure or average pressure in the interstage parameters of the dual-rotor turbine). This represents the physical rotational speed of the high-pressure turbine.

[0044] For example, when obtaining the turbine efficiency and equivalent speed of a low-pressure turbine: This represents the actual output power of the low-pressure turbine. The inlet temperature of the low-pressure turbine (i.e., the temperature or average value in the interstage parameters of the dual-rotor turbine; when multiple temperature probes are set, the inlet temperature of the low-pressure turbine is the average value of the probe values ​​of the multiple temperature probes). It is the ratio of the total inlet pressure to the total outlet pressure (i.e., the ratio of the pressure or average value in the interstage parameters of the dual-rotor turbine to the pressure or average value in the third performance parameter). This refers to the physical rotational speed of the low-pressure turbine.

[0045] For example, when you want to obtain the turbine efficiency of a dual-rotor turbine: This represents the actual output power of the high-pressure turbine and the low-pressure turbine. The inlet temperature of the high-pressure turbine (i.e., the temperature or average temperature in the fourth performance parameter; when multiple temperature probes are set, the inlet temperature of the high-pressure turbine is the average value of the probe values ​​of the multiple temperature probes). It is the ratio of the total inlet pressure to the total outlet pressure (i.e., the ratio of the pressure or average pressure in the fourth performance parameter to the pressure or average pressure in the third performance parameter).

[0046] This invention uses measurement methods to obtain accurate interstage parameters, fourth performance parameters, and third performance parameters of a dual-rotor turbine, enabling quantitative calculation of the matching characteristics of the dual-rotor turbine and thus obtaining accurate quantitative relationships.

[0047] In some instances, during the dual-rotor turbine test, the high-pressure turbine rotor 22 and the low-pressure turbine rotor 32 are controlled by a high-pressure dynamometer and a low-pressure dynamometer, respectively, and the actual output power of the high-pressure turbine 20 and the low-pressure turbine 30 are obtained through the speed and torque.

[0048] In some embodiments, by changing the inlet parameters and rotational speed (including the high-pressure turbine 20 and the low-pressure turbine 30), different third performance parameters, fourth performance parameters, and inter-stage parameters of the dual-rotor turbine are obtained under different inlet and outlet conditions and at different rotational speeds. This allows for the acquisition of quantitative relationships under different inlet and outlet conditions and at different rotational speeds.

[0049] The terms "first," "second," etc., used in the specification and claims of this invention are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such use of data can be interchanged where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and the number of objects is not limited; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0050] In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0051] All terms used in this invention (including technical or scientific terms) have the same meaning as understood by one of ordinary skill in the art to which this invention pertains, unless otherwise specifically defined. It should also be understood that terms defined in general dictionaries should be interpreted as having meanings consistent with their meanings in the context of the relevant art, and not as idealized or highly formalized, unless expressly defined herein.

[0052] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for measuring interstage parameters of a dual-rotor turbine, characterized in that, Includes the following steps: A high-pressure turbine is assembled in the flow channel of the casing; a first measuring probe is installed at the inlet of the high-pressure turbine rotor in the flow channel; a second measuring probe is installed at the outlet of the high-pressure turbine rotor in the flow channel; and a support baffle is assembled at the installation position of the low-pressure turbine rotor in the flow channel. A high-pressure turbine rotor test was conducted. The first measurement probe was used to measure and obtain the first performance parameter, and the second measurement probe was used to measure and obtain the second performance parameter. The correspondence between the inlet and outlet performance parameters of the high-pressure turbine is obtained based on the first and second performance parameters. Remove the support baffle and the second measuring probe, assemble the low-pressure turbine in the flow channel of the casing, and install the third measuring probe at the outlet of the low-pressure turbine rotor. A dual-rotor turbine test was conducted, and the fourth performance parameter was obtained by measuring the first measurement probe and the third performance parameter was obtained by measuring the third measurement probe. The interstage parameters of the dual-rotor turbine are obtained based on the aforementioned correspondence and the fourth performance parameter.

2. The method for measuring interstage parameters of a dual-rotor turbine according to claim 1, characterized in that, The first measuring probe includes a pressure probe and a temperature probe; and / or the second measuring probe includes a pressure probe and a temperature probe; and / or the third measuring probe includes a pressure probe and a temperature probe.

3. The method for measuring interstage parameters of a dual-rotor turbine according to claim 2, characterized in that, Multiple pressure probes are provided; and / or multiple temperature probes are provided.

4. The method for measuring interstage parameters of a dual-rotor turbine according to claim 1, characterized in that, The first measuring probe is positioned at the same cross-section of the flow channel; and / or the second measuring probe is positioned at the same cross-section of the flow channel; and / or the third measuring probe is positioned at the same cross-section of the flow channel.

5. The method for measuring interstage parameters of a dual-rotor turbine according to claim 1, characterized in that, It also includes the following steps: A static pressure measurement hole is made on the outer wall of the casing, and a static pressure measurement probe is installed in the static pressure measurement hole; wherein, the position of the static pressure measurement hole corresponds to the position of the second measurement probe; During the high-pressure turbine rotor test: the first measuring probe measures the first performance parameter, the second measuring probe measures the second performance parameter, and the static pressure measuring probe measures the first interstage static pressure. The correspondence between the inlet and outlet performance parameters of the high-pressure turbine is obtained based on the first performance parameter, the second performance parameter, and the interstage static pressure. During the dual-rotor turbine test: the first measuring probe measures the fourth performance parameter, the third measuring probe measures the third performance parameter, and the static pressure measuring probe measures the second stage static pressure. The interstage parameters of the dual-rotor turbine are obtained based on the aforementioned correspondence, the fourth performance parameter, and the static pressure between the second stage.

6. A dual-rotor turbine stage parameter measuring device, characterized in that, For implementing the measurement method as described in any one of claims 1-5, the measuring device includes a casing, a high-pressure turbine, a low-pressure turbine, and a support baffle; the casing includes a first casing, a second casing, a third casing, and a fourth casing that are sequentially detachable, and the high-pressure turbine, the low-pressure turbine, and the support baffle are all used to be installed inside the casing.

7. The dual-rotor turbine stage parameter measuring device according to claim 6, characterized in that, The detachable connection is achieved using bolts and nuts.

8. A method for obtaining matching features of a dual-rotor turbine, characterized in that, The measurement method according to any one of claims 1-5 further includes the following steps: The matching characteristics of the dual-rotor turbine are obtained based on the fourth performance parameter, the third performance parameter, and the interstage parameters of the dual-rotor turbine.

9. The method for obtaining matching features of a dual-rotor turbine according to claim 8, characterized in that, The dual-rotor turbine matching characteristics include turbine efficiency and reduced rotational speed; Turbine efficiency includes high-pressure turbine efficiency, low-pressure turbine efficiency, and dual-rotor turbine efficiency; equivalent speed includes high-pressure turbine equivalent speed and low-pressure turbine equivalent speed.

10. The method for obtaining matching features of a dual-rotor turbine according to claim 9, characterized in that, The turbine efficiency is obtained based on the rotor's actual output power, airflow mass flow rate, adiabatic index, mechanical efficiency, gas constant, fourth performance parameter, third performance parameter, and interstage parameters of the dual-rotor turbine. The reduced rotational speed is obtained based on the fourth performance parameter, the interstage parameters of the dual-rotor turbine, and the physical rotational speed of the turbine rotor.

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