A self-priming reverse turbine moving blade design method

Abstract

The object of the present invention is to provide a design method for a self-priming reverse turbine moving blade, which includes the following steps: constructing a three-dimensional model of the reverse turbine moving blade; obtaining the aerodynamic performance parameters of the reverse turbine, the reverse turbine reverse blowing loss, and the internal cavity profile of the reverse turbine moving blade; constructing a three-dimensional model of the internal cavity of the reverse turbine moving blade and a three-dimensional model of the reverse turbine moving blade with an internal cavity structure; obtaining the mechanical performance parameters of the reverse turbine moving blade with an internal cavity structure; constructing the air inlet and exhaust holes of the reverse turbine moving blade; obtaining the aerodynamic performance parameters of the reverse turbine; obtaining the reverse turbine reverse blowing loss. The present invention can not only meet the requirements of the core indicators such as power and efficiency for the normal operation of the reverse turbine, but also reduce the blowing loss during the reverse operation of the reverse turbine moving blade through the fluid self-priming function, reduce the blade weight and improve the stress state of the blade, and at the same time can also cool the blade tip and the closed cavity of the moving blade.

Description

Technical Field

[0001] The present invention relates to a gas turbine design method, specifically a reverse turbine design method. Background Art

[0002] Since its birth, gas turbines have been favored by various countries due to their high power density and rapid response. Gas turbines have become the main power source for medium and large-sized surface ships.

[0003] Currently, the reverse function of marine gas turbines is mainly achieved through controllable pitch propellers. The emergence of reverse turbines provides a new way for gas turbine reverse, that is, the gas turbine has the ability to rotate forward and backward, and the forward and reverse powers are directly provided by the gas turbine.

[0004] The reverse function of the gas turbine is realized by a reverse turbine with the ability to rotate forward and backward. The moving blades of this turbine are composed of double-layer blades. Usually, the inner-layer blades are forward turbine blades, and the outer-layer blades are reverse turbine blades. The two layers of blades are integrated and connected to the shaft through the turbine disk to output power. When all the gas flow passes through the inner-layer blades, the forward turbine blades work, and at this time, the reverse turbine blades rotate in reverse; when all the gas flow passes through the outer-layer blades, the reverse turbine blades work, and at this time, the forward turbine blades rotate in reverse. The reverse turbine is in the forward operation state for a long time. Therefore, during most of the running time, the reverse turbine is in the reverse operation state. At this time, the reverse turbine is in the compressor working mode and consumes power, which will cause additional reverse drum wind loss.

[0005] The traditional turbine blade profile focuses on blade modeling design from the perspective of how to reduce profile loss and improve turbine performance to meet the performance index requirements such as turbine efficiency, while insufficient attention is paid to the research on the blade modeling design method of the reverse turbine moving blades and reducing the reverse drum wind loss. Researchers urgently hope to have an advanced moving blade design method that can meet the special working requirements of marine reverse turbines and effectively reduce the reverse drum wind loss, so as to avoid the problem of excessive drum wind loss caused by ignoring the long-term reverse state while pursuing normal working state performance. Summary of the Invention

[0006] The purpose of the present invention is to provide a self-aspirating reverse turbine moving blade design method that can solve the problems such as excessive drum wind loss caused by ignoring the long-term reverse state during the design of the reverse turbine blades of marine reversible gas turbines.

[0007] The purpose of the present invention is achieved as follows:

[0008] A self-aspirating reverse turbine moving blade design method of the present invention is characterized in that:

[0009] (1) Based on the aerodynamic parameters of the reverse turbine, the shaping parameters of the reverse turbine rotor blades are given. The blade profile of the reverse turbine rotor is designed by using the traditional turbine rotor blade profile design method. The three-dimensional model of the reverse turbine rotor blade is constructed through the stretching function of the three-dimensional modeling software, and the preliminary design of the reverse turbine rotor is completed;

[0010] (2) Using the full three-dimensional aerodynamic performance numerical simulation software, the full three-dimensional aerodynamic performance calculation and analysis of the reverse turbine stage are carried out for the reverse turbine rotor blade obtained by the traditional turbine blade design method and the reverse turbine guide vane blade, and the aerodynamic performance parameters of the reverse turbine are obtained;

[0011] (3) Based on the reverse turbine rotor blade obtained in step (1), using the full three-dimensional aerodynamic performance numerical simulation software, the calculation of the blowing loss in the reverse state of the reverse turbine rotor is carried out, and the reverse turbine reverse blowing loss is obtained. Record this value as the subsequent comparison basis;

[0012] (4) Based on the reverse turbine rotor blade obtained in step (1), without changing the flow passage size and blade profile, the wall thickness △ of the rotor blade is preset. Through the offset function of the three-dimensional modeling software, the reverse turbine rotor blade profile is offset inward, and the offset distance is △, so as to obtain the internal cavity profile of the reverse turbine rotor;

[0013] (5) Based on the internal cavity profile of the reverse turbine rotor obtained in step (4), the three-dimensional model of the internal cavity of the reverse turbine rotor is constructed through the stretching function of the three-dimensional modeling software;

[0014] (6) Using the three-dimensional model of the reverse turbine rotor blade obtained in step (1) and the three-dimensional model of the internal cavity of the reverse turbine rotor obtained in step (4), through the Boolean subtraction function of the three-dimensional modeling software, the three-dimensional model of the reverse turbine rotor with an internal cavity structure is constructed;

[0015] (7) Using the three-dimensional strength analysis software, the strength calculation and analysis of the three-dimensional model of the reverse turbine rotor with an internal cavity structure obtained in step (6) are carried out, and the mechanical performance parameters of the reverse turbine rotor with an internal cavity structure are obtained;

[0016] (8) Given the intake hole parameters and positions, intake holes are preset on the pressure side and trailing edge surface of the rotor blade. The number of hole rows is N, the number of holes in each row is n i , the hole diameter is φ, and the position of each row of holes is at a distance L from the trailing edge starting from the trailing edge i ;

[0017] (9) Based on the three-dimensional model of the reverse turbine rotor with an internal cavity structure obtained in step (6), using the intake hole parameters and positions given in step (8), the intake holes of the reverse turbine rotor are constructed through the hole punching function of the three-dimensional modeling software, and the internal cavity of the rotor is connected to the cascade flow passage;

[0018] (10) Given the exhaust hole parameters and positions, preset exhaust holes at the top of the moving blade, with the number of holes being N T and the hole diameter being φ T , and the position of the hole is at a distance L from the leading edge measured from the leading edge T,i ;

[0019] (11) Based on the three-dimensional model of the reverse turbine moving blade with an internal cavity structure and the intake hole arrangement obtained in step (9), using the exhaust hole parameters and positions given in step (10), construct the exhaust holes of the reverse turbine moving blade through the hole punching function of the three-dimensional modeling software, and connect the internal cavity of the moving blade with the closed cavity of the top cap of the moving blade;

[0020] (12) Use the full three-dimensional aerodynamic performance numerical simulation software to perform a full three-dimensional aerodynamic performance calculation and analysis on the reverse turbine moving blade obtained in step (11) and the reverse turbine guide vane blade to obtain the aerodynamic performance parameters of the reverse turbine;

[0021] (13) Based on the reverse turbine moving blade obtained in step (11), use the full three-dimensional aerodynamic performance numerical simulation software to carry out the calculation of the blowing loss in the reverse state of the reverse turbine moving blade to obtain the reverse turbine reverse blowing loss.

[0022] The present invention may further include:

[0023] 1. If the aerodynamic performance parameters such as the power and efficiency of the reverse turbine stage obtained in step (2) meet the predetermined standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat steps (1) to (2) until the aerodynamic performance parameters of the reverse turbine stage reach the predetermined standards.

[0024] 2. If the mechanical performance parameters of the reverse turbine moving blade with an internal cavity structure obtained in step (7) meet the predetermined strength standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat steps (4) to (7) until the mechanical performance parameters of the reverse turbine moving blade with an internal cavity structure reach the predetermined strength standards.

[0025] 3. If the aerodynamic performance parameters such as the power and efficiency of the reverse turbine stage obtained in step (12) meet the predetermined standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat steps (8) to (12) until the aerodynamic performance parameters of the reverse turbine stage reach the predetermined standards.

[0026] 4. If the adjusted reverse turbine reverse blowing loss obtained in step (13) meets the predetermined standards, the design of the self-priming reverse turbine moving blade is completed; if it does not meet the predetermined standards, then repeat steps (8) to (13) until the reverse turbine reverse blowing loss reaches the predetermined standards.

[0027] 5. The reverse turbine moving blades are straight blades, that is, the blade profile of the root section and the top section of the reverse turbine moving blades is the same, and the blade is obtained by stretching the profile line of a section.

[0028] 6. The inside of the reverse turbine moving blade is a hollow structure.

[0029] 7. The surface of the reverse turbine moving blade is provided with inclined air inlet holes, which connect the internal cavity of the moving blade with the cascade flow passage, and lead the air reversely compressed in the cascade of the reverse turbine moving blade to the internal cavity of the moving blade.

[0030] 8. The top of the reverse turbine moving blade is provided with exhaust holes, which connect the internal cavity of the moving blade with the closed cavity of the top cap of the moving blade, discharge the air in the internal cavity of the reverse turbine moving blade to the closed cavity of the top cap of the moving blade, and cool the blade top and the closed cavity at the same time.

[0031] The advantages of the present invention are as follows:

[0032] 1. On the basis of making full use of the shaping design and aerodynamic analysis methods of traditional gas turbine turbine blades and meeting the performance index requirements of the reverse turbine, the present invention reduces the reverse blowing loss of the reverse turbine. Compared with the existing reverse turbine reverse blowing loss control methods, the reverse turbine moving blade of the present invention can further reduce the blowing loss by more than 5% when the reverse turbine is in the reverse state for a long time without changing the original aerodynamic performance and blade profile of the reverse turbine, improve the efficiency when the reversible turbine operates normally (the forward turbine operates in the forward state and the reverse turbine operates in the reverse state), is beneficial to reducing the energy consumption of the reversible turbine, and improving the endurance of the ship.

[0033] 2. The self-priming reverse turbine moving blade design method proposed by the present invention, aiming at the blowing loss in the reverse state of the reverse turbine, combines the existing engineering experience and the internal flow structure characteristics in the reverse state of the reverse turbine, and makes targeted improvement and adjustment to the moving blade, which can effectively control the blowing loss of the reverse turbine of the marine reversible gas turbine, and is beneficial to improving the performance of the marine reversible gas turbine when it operates in the forward state.

[0034] 3. The self-priming reverse turbine moving blade with low reverse blowing loss designed by the present invention has a hollow structure inside the moving blade, which is beneficial to reducing the weight of the moving blade, improving the stress state of the moving blade, and increasing the service life of the reverse turbine moving blade.

[0035] 4. The self-priming reverse turbine moving blade with low reverse blowing loss designed by the present invention can discharge the air in the cascade flow passage of the reverse turbine moving blade to the closed cavity of the top cap of the moving blade to cool the blade top and the closed cavity of the moving blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 is the flow chart of the present invention;

[0037] Figure 2 Schematic diagram of the external shape structure of the reversible turbine moving blade

[0038] Figure 3 Schematic cross-sectional view of the self-priming low-reverse blower-loss reversible turbine moving blade designed by the present invention

[0039] Figure 4 Schematic diagram of the external shape of the self-priming low-reverse blower-loss reversible turbine moving blade designed by the present invention

[0040] Figure 5 Schematic diagram of the cavity structure of the blade tip and cap of the reversible turbine moving blade

[0041] Figure 6 Schematic diagram of the internal streamline when the reversible turbine moving blade rotates in reverse Detailed implementation manners

[0042] The present invention will be described in more detail with reference to the accompanying drawings as follows:

[0043] Combined with Figures 1-6 , detailed implementation manner one: The implementation steps of a self-priming reversible turbine moving blade design method in this implementation manner are as Figure 1 shown, and the specific process is as follows:

[0044] Step 1: According to the aerodynamic parameters of the reversible turbine, give the shaping parameters of the reversible turbine moving blade, complete the design of the reversible turbine moving blade profile by using the traditional turbine moving blade profile design method, and construct a three-dimensional model of the reversible turbine moving blade through the stretching function of the three-dimensional modeling software to complete the preliminary design of the reversible turbine moving blade;

[0045] Step 2: Use the full three-dimensional aerodynamic performance numerical simulation software to perform a full three-dimensional aerodynamic performance calculation and analysis on the reversible turbine moving blade obtained by the traditional turbine blade design method and the reversible turbine guide vane blade to obtain the aerodynamic performance parameters of the reversible turbine;

[0046] If the aerodynamic performance parameters such as the power and efficiency of the reversible turbine stage obtained in Step 2 meet the predetermined standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat Steps 1 to 2 until the aerodynamic performance parameters of the reversible turbine stage reach the predetermined standards;

[0047] Step 3: Based on the reversible turbine moving blade obtained in Step 1, use the full three-dimensional aerodynamic performance numerical simulation software to carry out the calculation of the blower loss in the reverse rotation state of the reversible turbine moving blade, obtain the reverse rotation blower loss of the reversible turbine, record this value as the subsequent comparison basis;

[0048] Step 4: Based on the reverse turbine moving blade obtained in Step 1, without changing the flow passage size and blade profile, preset the wall thickness △ of the moving blade. Using the offset function of 3D modeling software, offset the reverse turbine moving blade profile inward by a distance of △ to obtain the internal cavity profile of the reverse turbine moving blade;

[0049] Step 5: Based on the internal cavity profile of the reverse turbine moving blade obtained in Step 4, use the extrusion function of 3D modeling software to construct a 3D model of the internal cavity of the reverse turbine moving blade;

[0050] Step 6: Using the 3D model of the reverse turbine moving blade obtained in Step 1 and the 3D model of the internal cavity of the reverse turbine moving blade obtained in Step 4, use the subtraction function of Boolean operation in 3D modeling software to construct a 3D model of the reverse turbine moving blade with an internal cavity structure;

[0051] Step 7: Use 3D strength analysis software to perform strength calculation and analysis on the 3D model of the reverse turbine moving blade with an internal cavity structure obtained in Step 6 to obtain the mechanical property parameters of the reverse turbine moving blade with an internal cavity structure;

[0052] If the mechanical property parameters of the reverse turbine moving blade with an internal cavity structure obtained in Step 7 meet the predetermined strength standard, proceed to the next step; if they do not meet the predetermined standard, repeat Steps 4 to 7 until the mechanical property parameters of the reverse turbine moving blade with an internal cavity structure reach the predetermined strength standard;

[0053] Step 8: Given the intake hole parameters and positions, preset intake holes on the pressure side and trailing edge surface of the moving blade. The number of hole rows is N, the number of holes in each row is n i 、the hole diameter is φ, and the position of each row of holes is at a distance of L from the trailing edge starting from the trailing edge i ;

[0054] Step 9: Based on the 3D model of the reverse turbine moving blade with an internal cavity structure obtained in Step 6, using the intake hole parameters and positions given in Step 8, use the hole punching function of 3D modeling software to construct the intake holes of the reverse turbine moving blade, connecting the internal cavity of the moving blade with the cascade flow passage;

[0055] Step 10: Given the exhaust hole parameters and positions, preset exhaust holes at the top of the moving blade. The number of holes is N T 、the hole diameter is φ T , and the position of the holes is at a distance of L from the leading edge starting from the leading edge T,i ;

[0056] Step Eleven: On the basis of the three-dimensional model of the reverse turbine moving blade with an internal cavity structure and the intake holes arranged in Step Nine, use the exhaust hole parameters and positions given in Step Ten to construct the exhaust holes of the reverse turbine moving blade through the hole punching function of the three-dimensional modeling software, and connect the internal cavity of the moving blade with the closed cavity of the top cap of the moving blade;

[0057] Step Twelve: Use the full three-dimensional aerodynamic performance numerical simulation software to perform a full three-dimensional aerodynamic performance calculation and analysis on the reverse turbine moving blade obtained in Step Eleven and the reverse turbine guide vane blade to obtain the reverse turbine aerodynamic performance parameters;

[0058] If the aerodynamic performance parameters such as the power and efficiency of the reverse turbine stage obtained in Step Twelve meet the predetermined standards, proceed to the next step; if they do not meet the predetermined standards, repeat Steps Eight to Twelve until the aerodynamic performance parameters of the reverse turbine stage reach the predetermined standards;

[0059] Step Thirteen: Based on the reverse turbine moving blade obtained in Step Eleven, use the full three-dimensional aerodynamic performance numerical simulation software to carry out the calculation of the blowing loss in the reverse state of the reverse turbine moving blade to obtain the reverse turbine reverse blowing loss;

[0060] If the adjusted reverse turbine reverse blowing loss obtained in Step Thirteen meets the predetermined standards, the design of the self-priming reverse turbine moving blade ends; if it does not meet the predetermined standards, repeat Steps Eight to Thirteen until the reverse turbine reverse blowing loss reaches the predetermined standards.

[0061] Specific Embodiment Two: The difference between this embodiment and Specific Embodiment One is that the self-priming reverse turbine moving blade designed by the design method is a straight blade (as Figure 2 shown), that is, the blade profile of the root section and the top section of the reverse turbine moving blade is the same, and the blade is obtained by stretching the profile of one section.

[0062] Other steps and parameters are the same as those in Specific Embodiment One.

[0063] Specific Embodiment Three: The difference between this embodiment and one of Specific Embodiments One and Two is that the self-priming reverse turbine moving blade designed by the design method has a hollow structure inside the moving blade (as Figure 3 shown). On the one hand, it is used to lead the reverse compressed air to the outside of the blade. On the other hand, it is also beneficial to reduce the weight of the moving blade by 60%, improve the stress state of the moving blade, and increase the life of the reversible turbine moving blade.

[0064] Other steps and parameters are the same as those in one of Specific Embodiments One and Two.

[0065] Embodiment 4: The difference between this embodiment and any one of Embodiments 1 to 3 is that for the self-priming low-reverse blower-loss reverse turbine moving blade designed by the design method, several rows of inclined air intake holes are provided on the surface of the moving blade (as shown in Figure 3 , Figure 4 ), and these air intake holes connect the internal cavity of the moving blade with the cascade flow passage, and are used to lead the reversely compressed air in the cascade of the reverse turbine moving blade to the internal cavity of the moving blade, reducing the amount of reversely compressed air, thereby reducing the reverse blower loss by more than 5%.

[0066] Other steps and parameters are the same as those in any one of Embodiments 1 to 3.

[0067] Embodiment 5: The difference between this embodiment and any one of Embodiments 1 to 4 is that for the self-priming low-reverse blower-loss reverse turbine moving blade designed by the design method, several exhaust holes are provided at the top of the moving blade (as shown in Figure 4 ), and these exhaust holes connect the internal cavity of the moving blade with the closed cavity of the top cap of the moving blade (as shown in Figure 5 ), and are used to discharge the air in the internal cavity of the reverse turbine moving blade to the closed cavity of the top cap of the moving blade, and at the same time play a role in cooling the blade top and the closed cavity.

[0068] Other steps and parameters are the same as those in any one of Embodiments 1 to 4.

[0069] Embodiment 6: The difference between this embodiment and any one of Embodiments 1 to 5 is that the 3D modeling software is UG software.

[0070] Other steps and parameters are the same as those in any one of Embodiments 1 to 5.

[0071] Embodiment 7: The difference between this embodiment and any one of Embodiments 1 to 6 is that the full 3D aerodynamic performance numerical simulation software is NUMECA and CFX software.

[0072] Other steps and parameters are the same as those in any one of Embodiments 1 to 6.

[0073] Embodiment 8: The difference between this embodiment and any one of Embodiments 1 to 7 is that the 3D strength analysis software is ANSYS software.

[0074] Other steps and parameters are the same as those in any one of Embodiments 1 to 7.

[0075] Through Figures 1 to 6 the working principle is described as follows:

[0076] When the ahead turbine is working, the rotor blades of the astern turbine rotate in the reverse direction at this time, that is, the astern turbine rotates reversely. In this case, the astern turbine enters the compressor working mode, that is, the air flow reversely flows from the original outlet to the inlet side, and the air is compressed. That is, the exhaust gas of the ahead turbine is sucked into the cascade channel formed by the rotor blades of the astern turbine and the adjacent blades. At this time, the astern turbine is in the state of reverse power consumption, not only does not generate power, but also consumes power. The rotor blades of the astern turbine with self-suction function and low reverse blowing loss designed by the present invention lead the reversely compressed air in the cascade of the rotor blades of the astern turbine to the internal cavity of the rotor blade by arranging air guiding holes on the blade surface, providing an internal cavity in the rotor blade and arranging exhaust holes at the top, reducing the amount of reversely compressed air, and thus reducing the reverse blowing loss. In this way, it can meet the requirements of the core indicators such as power and efficiency for the normal operation of the astern turbine, and at the same time, through the fluid self-suction function, reduce the blowing loss of the rotor blades of the astern turbine during reverse operation. The invention solves the problem that the blowing loss of the rotor blades of the astern turbine of a marine reversible gas turbine is too large due to the neglect of its long-term reverse state during the design of the rotor blades of the astern turbine. At the same time, because the inside of the rotor blade is a hollow structure, it is beneficial to reduce the weight of the rotor blade, improve the stress state of the rotor blade, increase the service life of the reversible turbine rotor blade, and also cool the top and the closed cavity of the rotor blade.

[0077] In summary, the present invention relates to a design method of the rotor blades of an astern turbine that can meet the requirements of core indicators such as power and efficiency for the normal operation of the astern turbine, and at the same time, through the fluid self-suction function, reduce the blowing loss of the rotor blades of the astern turbine during reverse operation. The purpose of the present invention is to solve the problem that the blowing loss of the rotor blades of the astern turbine of a marine reversible gas turbine is too large due to the neglect of its long-term reverse state during the design of the rotor blades of the astern turbine, and further provide a design method of the rotor blades of an astern turbine suitable for a marine reversible gas turbine, with self-suction function and low reverse blowing loss. The present invention is used in the fields of improving the control of the reverse blowing loss of the rotor blades of a marine reversible gas turbine and the weight reduction design of the blades.

Claims

1. A self-priming reverse turbine moving blade design method, characterized in that: (1) According to the aerodynamic parameters of the reverse turbine, give the shaping parameters of the reverse turbine rotor blades. Use the traditional turbine rotor blade design method to complete the design of the reverse turbine rotor blades. Through the stretching function of the 3D modeling software, construct the 3D model of the reverse turbine rotor blades to complete the preliminary design of the reverse turbine rotor blades; (2) Use the full 3D aerodynamic performance numerical simulation software to perform the full 3D aerodynamic performance calculation and analysis of the reverse turbine rotor blades obtained by the traditional turbine blade design method and the reverse turbine guide vane blades to obtain the aerodynamic performance parameters of the reverse turbine; (3) Based on the reverse turbine rotor blades obtained in step (1), use the full 3D aerodynamic performance numerical simulation software to carry out the calculation of the blowing loss under the reverse rotation state of the reverse turbine rotor blades to obtain the reverse turbine reverse blowing loss, record this value as the basis for subsequent comparison; (4) Based on the reverse turbine rotor blades obtained in step (1), without changing the flow passage size and blade profile, preset the wall thickness △ of the rotor blades. Through the offset function of the 3D modeling software, offset the reverse turbine rotor blade profile inward by a distance of △ to obtain the internal cavity profile of the reverse turbine rotor blades; (5) Based on the internal cavity profile of the reverse turbine rotor blades obtained in step (4), construct the 3D model of the internal cavity of the reverse turbine rotor blades through the stretching function of the 3D modeling software; (6) Use the 3D model of the reverse turbine rotor blades obtained in step (1) and the 3D model of the internal cavity of the reverse turbine rotor blades obtained in step (4). Through the subtraction function of the Boolean operation of the 3D modeling software, construct the 3D model of the reverse turbine rotor blades with an internal cavity structure; (7) Use the 3D strength analysis software to perform strength calculation and analysis on the 3D model of the reverse turbine rotor blades with an internal cavity structure obtained in step (6) to obtain the mechanical performance parameters of the reverse turbine rotor blades with an internal cavity structure; (8) Given the intake hole parameters and positions, intake holes are preset on the pressure side and trailing edge surface of the moving blade. The number of hole rows is N, the number of holes in each row is n i , the hole diameter is φ, and the position of each row of holes is at a distance L from the trailing edge starting from the trailing edge i ; (9) Based on the 3D model of the reverse turbine rotor blades with an internal cavity structure obtained in step (6), use the intake hole parameters and positions given in step (8). Through the hole punching function of the 3D modeling software, construct the intake holes of the reverse turbine rotor blades to connect the internal cavity of the rotor blades with the cascade flow passage; (10) Given the exhaust hole parameters and positions, exhaust holes are preset at the top of the moving blade, and the number of holes is N T , the hole diameter is φ T , and the position of the hole is at a distance of L from the leading edge measured from the leading edge T,i ; (11) Based on the 3D model of the reverse turbine rotor blades with an internal cavity structure and completed intake hole arrangement obtained in step (9), use the exhaust hole parameters and positions given in step (10). Through the hole punching function of the 3D modeling software, construct the exhaust holes of the reverse turbine rotor blades to connect the internal cavity of the rotor blades with the closed cavity at the top cap of the rotor blades; (12) Use the full 3D aerodynamic performance numerical simulation software to perform the full 3D aerodynamic performance calculation and analysis of the reverse turbine rotor blades obtained in step (11) and the reverse turbine guide vane blades to obtain the aerodynamic performance parameters of the reverse turbine; (13) Based on the reverse turbine rotor blades obtained in step (11), use the full 3D aerodynamic performance numerical simulation software to carry out the calculation of the blowing loss under the reverse rotation state of the reverse turbine rotor blades to obtain the reverse turbine reverse blowing loss.

2. The self-priming reverse turbine moving blade design method according to claim 1, characterized in that: If the aerodynamic performance parameters of the reverse turbine power and efficiency obtained in step (2) meet the predetermined standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat steps (1) to (2) until the aerodynamic performance parameters of the reverse turbine stage reach the predetermined standards.

3. The self-priming reverse turbine moving blade design method according to claim 1, characterized in that: If the mechanical performance parameters of the reverse turbine moving blade with an internal cavity structure obtained in step (7) meet the predetermined strength standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat steps (4) to (7) until the mechanical performance parameters of the reverse turbine moving blade with an internal cavity structure reach the predetermined strength standards.

4. The self-priming reverse turbine moving blade design method according to claim 1, characterized in that: If the aerodynamic performance parameters of the reverse turbine power and efficiency obtained in step (12) meet the predetermined standards, then proceed to the next step; if they do not meet the predetermined standards, then repeat steps (8) to (12) until the aerodynamic performance parameters of the reverse turbine stage reach the predetermined standards.

5. The self-priming reverse turbine moving blade design method according to claim 1, characterized in that: If the reverse turbine reverse blowing loss obtained in step (13) meets the predetermined standards, the design of the self-priming reverse turbine moving blade is completed; if it does not meet the predetermined standards, then repeat steps (8) to (13) until the reverse turbine reverse blowing loss reaches the predetermined standards.

6. The self-priming reverse turbine moving blade design method according to claim 1, characterized in that: The reverse turbine moving blade is a straight blade, that is, the blade profile of the root section and the top section of the reverse turbine moving blade is the same, and the blade is obtained by stretching the profile line of a section.

7. The self-priming reverse turbine moving blade design method according to claim 1, characterized in that: The inside of the reverse turbine moving blade is a hollow structure.

8. The self-priming reverse turbine moving blade design method according to claim 1, characterized in that: The surface of the reverse turbine moving blade is provided with inclined air intake holes, and the air intake holes communicate the internal cavity of the moving blade with the cascade flow passage, and lead the air reversely compressed in the reverse turbine moving blade cascade to the internal cavity of the moving blade.

9. The self-priming reverse turbine moving blade design method according to claim 1, characterized in that: The top of the reverse turbine moving blade is provided with exhaust holes, and the exhaust holes communicate the internal cavity of the moving blade with the closed cavity of the top cap of the moving blade, and discharge the air in the internal cavity of the reverse turbine moving blade to the closed cavity of the top cap of the moving blade, and at the same time cool the blade top and the closed cavity.

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