A method for designing turbine rotor-stator spacing to suppress wave train interference

Abstract

The application discloses a turbine rotating-static spacing design method for inhibiting wave system interference, and the method comprises the following steps: obtaining turbine overall design input parameters; establishing a rotating-static axial spacing quantitative calculation model based on the input parameters; satisfying supersonic airflow local blockage conditions; and inhibiting wave system interference through induced shock waves. The optimal spacing is calculated by using the model, so that the rotor blade is swept by three times of extended, reflected and induced shock waves when passing through the guide vane channel, and aerodynamic excitation spectrum is widely distributed. The spacing is output to the turbine stage axial layout design. The application optimizes the axial distance between the rotor blade and the stator guide vane, directly reduces the turbine stage axial size, and through the accurate control of the axial spacing, the rotor blade is swept by three times of extended, reflected and induced shock waves when passing through the guide vane channel, the wide distribution of the aerodynamic excitation energy spectrum is realized, and the aerodynamic excitation on the turbine rotor blade is significantly reduced.

Description

Technical Field

[0001] This invention relates to the field of turbine-to-static distance design technology for aero-engines, and in particular to a method for designing turbine-to-static distance to suppress wave interference. Background Technology

[0002] Turbine blades are core components of aero-engines, and high-cycle fatigue fracture is one of the most common failure modes. During operation, turbine blades are subjected to complex loads from the airflow, commonly referred to as aerodynamic excitation, which is one of the primary causes of high-cycle fatigue fracture. Aerodynamic excitation originates from periodic disturbances in the flow field, particularly flow structures such as shock waves, wakes, and secondary flows formed within the turbine passage. Shock wave disturbances are especially prominent in the high-load, high-pressure turbines of modern aero-engines, directly impacting the blade surface and causing intense pressure fluctuations.

[0003] In the design of modern advanced turbines, turbine loads are constantly increasing, and the aerodynamic excitation experienced by the blades is also becoming increasingly stronger. This makes aerodynamic excitation suppression one of the key technologies for improving turbine reliability and extending blade life. The axial distance between the turbine rotor and stator has a significant impact on the evolution of the flow structure. As the rotor-stator distance increases, the intensity of the flow structure formed in the guide vane passage acting on the rotor blades continuously decreases, resulting in a more uniform flow field distribution at the rotor inlet, which is beneficial for reducing the aerodynamic excitation experienced by the rotor. However, this contradicts the development trend of a more compact turbine rotor-stator spacing. Therefore, how to balance turbine reliability with the distance between the turbine rotor and stator has become an urgent problem to be solved.

[0004] Most existing technologies involve numerically simulating a series of turbine stage examples with different rotor-stator axial spacings based on the turbine's operating environment. This allows for the evaluation of the aerodynamic excitation or vibration stress variation with the axial spacing, thereby determining the appropriate turbine axial position. However, this approach has limitations: it requires a large number of unsteady numerical simulations, consuming significant computational resources, and is not suitable for the rapid iterative processes in turbine design, severely slowing down turbine design efficiency. Summary of the Invention

[0005] This invention provides a turbine rotor-stator spacing design method for suppressing wave system interference, in order to solve the technical problems of how to reduce the axial spacing between the rotor and stator while efficiently suppressing wave system interference at the guide vane outlet, and how to provide technical support for turbine aerodynamic excitation suppression.

[0006] In view of the above technical problems, embodiments of the present invention provide a turbine rotor-to-stationary distance design method for suppressing wave system interference, comprising:

[0007] S1. Obtain the overall design input parameters of the turbine, including the mass flow rate of the airflow passing through a single guide vane passage, the total pressure of the airflow at the guide vane outlet, the total temperature of the airflow at the guide vane outlet, the radius of the guide vane outlet casing, the radius of the guide vane outlet hub, and gas physical property parameters.

[0008] S2. Based on the input parameters, establish a quantitative calculation model for the distance between the rotating and stationary axes. The quantitative calculation model satisfies the local blockage condition of supersonic airflow and is used to generate induced shock waves to suppress wave system interference.

[0009] S3. The optimal rotor-stationary axis spacing is calculated using the quantitative calculation model, so that the rotor blades are subjected to three shock wave sweeps in sequence by the extended shock wave, the reflected shock wave and the induced shock wave as they rotate through a guide vane channel, thereby achieving a broad distribution of the aerodynamic excitation energy spectrum.

[0010] S4. Output the optimal axial spacing between the rotor and stationary axes for turbine stage axial layout design.

[0011] Optionally, step S1 further includes the following sub-steps:

[0012] S101. Define a standardized format for input parameters, converting the parameters provided by the overall design into a format that can be directly read by the one-dimensional model, wherein the parameter naming and units are consistent with the turbine overall design platform.

[0013] S102. Determine the turbine's operating status and confirm that the airflow at the guide vane outlet is at Mach number and in a supersonic flow state.

[0014] Optionally, the mathematical expression of the quantitative calculation model in step S2 is:

[0015]

[0016] in, This indicates the axial spacing between the rotor blades and guide vanes of a high-load, high-pressure turbine. This represents the mass flow rate of the airflow passing through a single guide vane channel. This indicates the total pressure of the airflow at the guide vane outlet. Indicates the radius of the guide vane exit casing. Indicates the radius of the guide vane outlet hub. This indicates the total temperature of the airflow at the guide vane outlet. Represents the gas constant. This indicates the specific heat ratio of the airflow.

[0017] Optionally, step S3 further includes the following sub-steps:

[0018] S301. Establish an evaluation function for the aerodynamic excitation suppression effect, with a primary objective of reducing the amplitude of the first-order aerodynamic excitation of the rotor blades by 60%, and the rotation-stationary axial spacing as the primary objective. Minimization is the secondary objective;

[0019] S302. Set engineering constraints, including the distance between the rotating and stationary axes. The value range is 0.25 to 0.50 times the axial chord length of the guide vane, and the rotor blades and guide vanes do not interfere with each other mechanically;

[0020] S303, Solve the equations satisfying steps S301 and S302 using the quantitative calculation model. The value ensures that the induced shock wave forms a local airflow blockage precisely when the rotor blades rotate to a specific circumferential position.

[0021] Optionally, the maximum Mach number of the guide vane outlet airflow in step S102 is higher than 1.4.

[0022] Optionally, the optimal axis spacing between the rotating and stationary axes calculated in step S303 is: The axial chord length of the guide vane is 0.36 times the dimensionless axial chord length of the guide vane.

[0023] This invention also provides a turbine rotor-to-station pitch design system for suppressing wave system interference, implemented using the turbine rotor-to-station pitch design method for suppressing wave system interference as described above, including:

[0024] The overall parameter input module is used to obtain the overall design input parameters of the turbine. The input parameters include the mass flow rate of the airflow passing through a single guide vane channel, the total pressure of the airflow at the guide vane outlet, the total temperature of the airflow at the guide vane outlet, the radius of the guide vane outlet casing, the radius of the guide vane outlet hub, and gas physical property parameters.

[0025] The spacing calculation module is used to establish a quantitative calculation model of the spacing between the rotating and stationary axes based on the input parameters. The quantitative calculation model satisfies the local blockage condition of supersonic airflow and is used to generate induced shock waves to suppress wave system interference.

[0026] The shock wave interferometry analysis module is used to calculate the optimal rotor-stationary axis spacing using the quantitative calculation model, so that the rotor blades are subjected to three shock wave sweeps in sequence—extended shock wave, reflected shock wave, and induced shock wave—as they rotate through a guide vane channel, thereby achieving a broad distribution of the aerodynamic excitation energy spectrum.

[0027] An optimized output module is used to output the optimal rotor-stationary axis spacing for turbine stage axial layout design.

[0028] In this invention, by optimizing the axial distance between the rotor blades and the stator guide vanes, the axial dimension between the rotor and stator is reduced, directly decreasing the axial dimension of the turbine stage. This provides crucial support for the compact and lightweight design of the overall engine structure. Simultaneously, it effectively suppresses the most prominent shock wave disturbance in high-load, high-pressure turbines of aero-engines, thereby significantly reducing the aerodynamic excitation experienced by the turbine rotor blades. By precisely controlling the axial spacing, the rotor blades are subjected to three shock wave sweeps—extended shock wave, reflected shock wave, and induced shock wave—as they pass through the guide vane passage. This achieves a broadened distribution of the aerodynamic excitation energy spectrum, significantly reducing the amplitude of the first-order aerodynamic excitation experienced by the turbine rotor blades. This effect effectively extends the service life of the turbine blades, improves the reliability and safety of the turbine, and plays a vital role in ensuring the long-term stable operation of aero-engines. Attached Figure Description

[0029] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments of the present invention will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is a schematic diagram of the process of an extended shock wave sweeping rotor blade in one embodiment of the present invention;

[0031] Figure 2 This is a schematic diagram of the process of a reflected shock wave sweeping a rotor blade in one embodiment of the present invention;

[0032] Figure 3 This is a schematic diagram of induced shock waves acting on rotor blades in one embodiment of the present invention.

[0033] The reference numerals in the accompanying drawings are as follows:

[0034] 1-Guide blade, 2-Extended shock wave, 3-Inner extended shock wave, 4-Reflected shock wave, 5-Reflection point, 6-Induced shock wave, 7-Wake, 8-Rotor blade. Detailed Implementation

[0035] To make the technical problems solved, the technical solutions, and the beneficial effects of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0036] In the description of this invention, it should be understood that the terms "longitudinal," "radial," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0037] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0038] like Figures 1 to 3 As shown, one embodiment of the present invention provides a turbine rotor-to-stationary distance design method for suppressing wave system interference, including:

[0039] S1. Obtain the overall design input parameters of the turbine, including the mass flow rate of the airflow passing through a single guide vane channel, the total pressure of the airflow at the guide vane outlet, the total temperature of the airflow at the guide vane outlet, the radius of the guide vane outlet casing, the radius of the guide vane outlet hub, and the gas physical property parameters.

[0040] In one embodiment, step S1 further includes the following sub-steps:

[0041] S101. Define a standardized format for input parameters, converting the parameters provided by the overall design into a format that can be directly read by the one-dimensional model, wherein the parameter naming and units are consistent with the turbine overall design platform.

[0042] S102. Determine the turbine's operating status and confirm that the airflow at the guide vane outlet is at Mach number and in a supersonic flow state.

[0043] In one embodiment, the maximum Mach number of the guide vane outlet airflow in step S102 is higher than 1.4.

[0044] S2. Based on the input parameters, a quantitative calculation model for the distance between the rotating and stationary axes is established. The quantitative calculation model satisfies the local blockage condition of supersonic airflow and is used to generate induced shock waves to suppress wave system interference.

[0045] In one embodiment, the mathematical expression of the quantitative calculation model in step S2 is:

[0046]

[0047] in, This indicates the axial spacing between the high-load, high-pressure turbine rotor blade 8 and the guide vane 1. This represents the mass flow rate of the airflow passing through a single guide vane channel. This indicates the total pressure of the airflow at the guide vane outlet. Indicates the radius of the guide vane exit casing. Indicates the radius of the guide vane outlet hub. This indicates the total temperature of the airflow at the guide vane outlet. Represents the gas constant. This indicates the specific heat ratio of the airflow.

[0048] S3. The optimal rotor-stationary axis spacing is calculated using the quantitative calculation model, so that the rotor blades are subjected to three shock wave sweeps in sequence—extended shock wave, reflected shock wave, and induced shock wave—as they rotate through a guide vane channel, thus achieving a broad distribution of the aerodynamic excitation energy spectrum.

[0049] In one embodiment, step S3 further includes the following sub-steps:

[0050] S301. Establish an evaluation function for the aerodynamic excitation suppression effect, with a 60% reduction in the amplitude of the first-order aerodynamic excitation of rotor blade 8 as the main objective, and the axial spacing between the rotor and stationary axes as the reference. Minimization is the secondary objective;

[0051] S302. Set engineering constraints, including the distance between the rotating and stationary axes. The value range is 0.25 to 0.50 times the axial chord length of the guide vane, and the rotor blade 8 and the guide vane 1 do not interfere with each other mechanically;

[0052] S303, Solve the equations satisfying steps S301 and S302 using the quantitative calculation model. The value ensures that the induced shock wave forms a local airflow blockage precisely when the rotor blade 8 rotates to a specific circumferential position.

[0053] S4. Output the optimal axial spacing between the rotor and stationary axes for turbine stage axial layout design.

[0054] Understandably, in the high-load, high-pressure turbines of modern aero engines, the maximum Mach number at the exit of guide vane 1 can reach 1.4. Such a high Mach number will induce strong shock wave disturbances, which have become the most significant source of unsteadiness in the turbine flow field. Specifically, the reflected shock wave 4 from the outward-extending shock wave 2 and the inward-extending shock wave 3 at the exit of guide vane 1 ( Figure 2The reflection point 5 of the extended shock wave can be clearly seen. The airflow is reflected here to form a complex wave system consisting of the reflected shock wave 4, which has a very significant impact on the pressure distribution on the surface of the downstream rotor blade 8. Figure 1 and Figure 2 The process of the reflected shock wave 4 from the extended shock wave 2 and the internal shock wave 3 sweeping across the rotor blade 8 is visually demonstrated. The two shock wave sweeps result in the first two orders of aerodynamic excitation amplitudes of the rotor blade 8 being at a high level. Furthermore, because the intensity of the extended shock wave 2 is higher than that of the reflected shock wave 4, the first-order aerodynamic excitation amplitude is more dominant. Generally, high-frequency excitation poses relatively less risk; therefore, suppressing the first-order excitation amplitude becomes crucial in this technical field.

[0055] During continuous rotation of rotor blade 8, the relative positions of rotor blade 8 and guide vane 1 in the circumferential direction constantly change. The turbine rotor-stator spacing design method for suppressing wave interference proposed in this application relies on using induced shock wave 6 to suppress aerodynamic excitation. However, to achieve this goal, controlling the axial spacing between the rotor and stator is crucial; spacing that is too close or too far will not achieve the desired effect. If the axial spacing between the rotor and stator is too close, the flow area enclosed by rotor blade 8 and guide vane 1 will never be sufficient for all airflow to pass through smoothly, and in this case, induced shock wave 6 will not be generated. Conversely, if the spacing is too far, the airflow will not be blocked during the rotation of rotor blade 8, and induced shock wave 6 will also not be generated.

[0056] Given that the airflow at the exit of the guide vane 1 of a high-load, high-pressure turbine in a modern aero-engine is always at supersonic speeds, by optimizing the axial position of the rotor blades 8, the turbine flow channel can be partially blocked at a specific phase, thereby successfully inducing the generation of shock wave 6 (e.g., Figure 3 (As shown). In Figure 3 In addition to observing the formation process of induced shock wave 6, the wake 7 generated by the trailing edge of guide vane 1 can also be seen. The mechanism of induced shock wave 6 is as follows: during the rotation of rotor blade 8, wake 7 acts as an aerodynamic boundary, causing dynamic changes in the effective flow area of ​​airflow between rotor blade 8 and adjacent guide vane 1. When this area is insufficient to allow all the airflow in a single guide vane channel to pass through, induced shock wave 6 will form due to airflow blockage. Thus, rotor blade 8 will be subjected to three shock wave disturbances (extended shock wave 2, reflected shock wave 4, and induced shock wave 6) in sequence as it rotates through a guide vane channel. This effect can broaden the energy distribution of aerodynamic excitation in the spectrum, thereby achieving a significant reduction in the amplitude of the first-order excitation.

[0057] In one embodiment, the optimal axis spacing between the rotating and stationary axes calculated in step S303 is: The axial chord length of the guide vane is 0.36 times the dimensionless axial chord length of the guide vane.

[0058] Understandably, at the theoretical level, the 0.36 times axial chord length of the guide vane is calculated using the mathematical quantitative model of this invention, and derived through rigorous and detailed mathematical derivation. The model can be traced back to the formula for calculating the mass flow rate of compressible fluids, and its expression is:

[0059]

[0060] in, This indicates the size of the cross-sectional area through which the airflow passes. Let M be the Mach number of the airflow. When local blockage forms, the Mach number M=1, and the mass flow rate calculation formula simplifies to:

[0061]

[0062] At this point, there is a clear functional relationship between the airflow mass flow rate and the critical flow area. In the turbine passage, the critical flow area is the size of the region enclosed by the guide vane trailing edge, the moving blade leading edge, the hub, and the casing. The airflow area of ​​a single passage is:

[0063]

[0064] This allows us to obtain the functional relationship between airflow mass flow rate and critical flow area:

[0065]

[0066] The thermodynamic parameters of aviation kerosene fuel gas (γ=1.33, R) gas Substituting (e.g., 287 J / kg / K) into the equation and performing calculations, an optimal axial spacing can be obtained. The axial spacing is dimensionless using the axial chord length of guide vane 1. The dimensionless axial spacing converges to 0.36 times the axial chord length of the guide vane.

[0067] At the numerical simulation verification level, the effectiveness of the design method was rigorously verified using the ANSYS CFX2021R1 solver. Specifically, verification examples were constructed in the form of an arithmetic sequence, including five examples: 0.25 (3 / 12) times the axial chord length of the guide vane, 0.33 (4 / 12) times the axial chord length of the guide vane, 0.42 (5 / 12) times the axial chord length of the guide vane, 0.50 (6 / 12) times the axial chord length of the guide vane, and the optimized 0.36 times the axial chord length of the guide vane. Unsteady calculations were performed using the SSTk-ω turbulence model and a dual time-step method. The physical time step was set to one-sixtieth of the time required for the rotor to rotate through a single guide vane channel, and a total of 10 complete cycles were calculated until the time-domain signal difference was less than 1%. The calculation results are shown in Table 1 of the specification. In the optimized design examples, the first-order amplitude of the aerodynamic excitation was the smallest, much smaller than that of other examples where the axial spacing was not refined, verifying the efficiency of the axial spacing optimization design method proposed in this invention.

[0068]

[0069] This invention also provides a turbine rotor-to-station pitch design system for suppressing wave system interference, implemented using the turbine rotor-to-station pitch design method for suppressing wave system interference as described above, including:

[0070] The overall parameter input module is used to obtain the overall design input parameters of the turbine. The input parameters include the mass flow rate of the airflow passing through a single guide vane channel, the total pressure of the airflow at the guide vane outlet, the total temperature of the airflow at the guide vane outlet, the radius of the guide vane outlet casing, the radius of the guide vane outlet hub, and gas physical property parameters.

[0071] The spacing calculation module is used to establish a quantitative calculation model of the spacing between the rotating and stationary axes based on the input parameters. The quantitative calculation model satisfies the local blockage condition of supersonic airflow and is used to generate induced shock waves to suppress wave system interference.

[0072] The shock wave interferometry analysis module is used to calculate the optimal rotor-stationary axis spacing using the quantitative calculation model, so that the rotor blades are subjected to three shock wave sweeps in sequence—extended shock wave, reflected shock wave, and induced shock wave—as they rotate through a guide vane channel, thereby achieving a broad distribution of the aerodynamic excitation energy spectrum.

[0073] An optimized output module is used to output the optimal rotor-stationary axis spacing for turbine stage axial layout design.

[0074] The above-described embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. 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. Such 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, and should all be included within the protection scope of the present invention.

Claims

1. A method for designing turbine rotor-to-stationary distance to suppress wave system interference, characterized in that, include: S1. Obtain the overall design input parameters of the turbine, including the mass flow rate of the airflow passing through a single guide vane passage, the total pressure of the airflow at the guide vane outlet, the total temperature of the airflow at the guide vane outlet, the radius of the guide vane outlet casing, the radius of the guide vane outlet hub, and gas physical property parameters. S2. Based on the input parameters, establish a quantitative calculation model for the distance between the rotating and stationary axes. The quantitative calculation model satisfies the local blockage condition of supersonic airflow and is used to generate induced shock waves to suppress wave system interference. S3. The optimal rotor-stationary axis spacing is calculated using the quantitative calculation model, so that the rotor blades are subjected to three shock wave sweeps in sequence by the extended shock wave, the reflected shock wave and the induced shock wave as they rotate through a guide vane channel, thereby achieving a broad distribution of the aerodynamic excitation energy spectrum. S4. Output the optimal axial spacing between the rotor and stationary axes for turbine stage axial layout design.

2. The turbine rotor-to-stationary distance design method for suppressing wave system interference according to claim 1, characterized in that, Step S1 further includes the following sub-steps: S101. Define a standardized format for input parameters, converting the parameters provided by the overall design into a format that can be directly read by the one-dimensional model, wherein the parameter naming and units are consistent with the turbine overall design platform. S102. Determine the turbine's operating status and confirm that the airflow at the guide vane outlet is at Mach number and in a supersonic flow state.

3. The turbine rotor-to-stationary distance design method for suppressing wave system interference according to claim 2, characterized in that, The mathematical expression for the quantitative calculation model in step S2 is: ； in, This indicates the axial spacing between the rotor blades and guide vanes of a high-load, high-pressure turbine. This represents the mass flow rate of the airflow passing through a single guide vane channel. This indicates the total pressure of the airflow at the guide vane outlet. Indicates the radius of the guide vane exit casing. Indicates the radius of the guide vane outlet hub. This indicates the total temperature of the airflow at the guide vane outlet. Represents the gas constant. This indicates the specific heat ratio of the airflow.

4. The turbine rotor-to-stationary distance design method for suppressing wave system interference according to claim 3, characterized in that, Step S3 further includes the following sub-steps: S301. Establish an evaluation function for the aerodynamic excitation suppression effect, with a primary objective of reducing the amplitude of the first-order aerodynamic excitation of the rotor blades by 60%, and the rotation-stationary axial spacing as the primary objective. Minimization is the secondary objective; S302. Set engineering constraints, including the distance between the rotating and stationary axes. The value range is 0.25 to 0.50 times the axial chord length of the guide vane, and the rotor blades and guide vanes do not interfere with each other mechanically; S303, Solve the equations satisfying steps S301 and S302 using the quantitative calculation model. The value ensures that the induced shock wave forms a local airflow blockage precisely when the rotor blades rotate to a specific circumferential position.

5. The turbine rotor-to-stationary distance design method for suppressing wave system interference according to claim 4, characterized in that, The maximum Mach number of the airflow at the guide vane outlet in step S102 is higher than 1.

4.

6. The turbine rotor-to-stationary distance design method for suppressing wave system interference according to claim 5, characterized in that, The optimal rotation-stationary axis spacing calculated in step S303 is: The axial chord length of the guide vane is 0.36 times the dimensionless axial chord length of the guide vane.

7. A turbine rotor-to-stationary distance design system for suppressing wave system interference, characterized in that, The method for designing turbine rotor-to-stationary distance to suppress wave system interference, as described in any one of claims 1-6, includes: The overall parameter input module is used to obtain the overall design input parameters of the turbine. The input parameters include the mass flow rate of the airflow passing through a single guide vane channel, the total pressure of the airflow at the guide vane outlet, the total temperature of the airflow at the guide vane outlet, the radius of the guide vane outlet casing, the radius of the guide vane outlet hub, and gas physical property parameters. The spacing calculation module is used to establish a quantitative calculation model of the spacing between the rotating and stationary axes based on the input parameters. The quantitative calculation model satisfies the local blockage condition of supersonic airflow and is used to generate induced shock waves to suppress wave system interference. The shock wave interferometry analysis module is used to calculate the optimal rotor-stationary axis spacing using the quantitative calculation model, so that the rotor blades are subjected to three shock wave sweeps in sequence—extended shock wave, reflected shock wave, and induced shock wave—as they rotate through a guide vane channel, thereby achieving a broad distribution of the aerodynamic excitation energy spectrum. An optimized output module is used to output the optimal rotor-stationary axis spacing for turbine stage axial layout design.

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