A method and system for designing a turbine transition strut with size struts

Abstract

The application discloses a turbine transition section strut design method and system with large and small support plates, and the method comprises the following steps: determining strut design input and strut profile parameters; constructing a strut shape; calculating a strut cross-sectional area; performing strength evaluation on the constructed strut cross section until design requirements are met; performing full three-dimensional aerodynamic performance analysis on the strut shape until a total pressure loss coefficient of the strut shape meets design requirements; and mixing the strut shape meeting the strength and total pressure loss coefficient design requirements in three-dimensional modeling software to obtain a strut solid model. The application can quickly obtain a strut with excellent aerodynamic performance and suitable functions under the design conditions of the turbine transition section strut with large and small support plates, accelerates the design process of the turbine transition section with large and small support plates, and improves the design speed and efficiency of the turbine transition section.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine design, specifically relating to a design method and system for a turbine transition section support with large and small support plates. Background Technology

[0002] In dual-rotor and triple-rotor gas turbines, the turbines of different rotors are often connected by a meridional expansion turbine transition section, which transports high-temperature gas from the turbine of the preceding rotor to the turbine of the following rotor. To simplify the structure, reduce the number of parts, and shrink the engine size, dual-rotor and triple-rotor gas turbines often arrange cooling air supply channels or pipelines, lubricating oil supply and return channels or pipelines in the support plates / supports or fairings of the turbine transition section. Some engines arrange both large and small support plates in the turbine transition section, with the small support plate used for load-bearing support and the large support plate used as a passage for lubricating oil and cooling air.

[0003] The aerodynamic performance of the turbine transition section directly affects the overall performance of the gas turbine. Therefore, it is of great significance to quickly obtain a turbine transition section with excellent aerodynamic performance and design a high-performance turbine to improve the efficiency of gas turbines.

[0004] Currently, much research focuses on turbine aerodynamic performance design and optimization, with insufficient attention paid to the aerodynamic performance design and flow field assessment of turbine transition sections with two different types of support plates of varying sizes. Most design methods employ complex support profiles similar to turbine guide vanes. This approach results in relatively complex support profiles, increased manufacturing difficulty, and higher costs. Furthermore, supports often utilize double or multi-unit structures and are typically manufactured using casting processes, leading to lower load-bearing capacity compared to forging processes. Additionally, supports are not currently suitable for axial intake / exhaust.

[0005] Therefore, there is currently a lack of a design method for turbine transition section struts with large and small support plates, and in particular, a strut design method that can meet the load-bearing support requirements of gas turbine components, minimize flow losses, and is suitable for axial intake and exhaust. Summary of the Invention

[0006] To solve the above-mentioned technical problems, the present invention provides a design method for a turbine transition section support with large and small support plates, which meets the working requirements of the turbine transition section support with large and small support plates, and avoids problems such as failure to meet aerodynamic performance and support structure strength requirements due to inappropriate selection of support parameters.

[0007] The objective of this invention is achieved through the following technical solution: a design method for a turbine transition section support with large and small support plates, comprising the following steps:

[0008] Step 1: Determine the input parameters for the support column design;

[0009] Step 2: Determine the parameters used to construct the column profile, including the parameters for constructing the column root section outline and the column top section outline;

[0010] Step 3: Construct the external profile of the support root section and the external profile of the support top section based on the support profile construction parameters determined in Step 2;

[0011] Step 4: Based on the support root section outline and support top section outline obtained in Step 3, calculate the cross-sectional area A of the support root section. h and the cross-sectional area A of the top section of the support column t ;

[0012] Step 5: Evaluate the strength of the column section and calculate the strength reserve coefficient of the column root section and the strength reserve coefficient of the column top section;

[0013] Step 6: Compare the strength reserve coefficients of the support root section and the support top section obtained in Step 5 with the preset strength reserve coefficients. If they meet the requirements, proceed to Step 7. If they do not meet the requirements, repeat Step 2 to Step 6.

[0014] Step 7: Perform a full three-dimensional aerodynamic performance analysis on the support structure to obtain the total pressure loss coefficient of the support structure;

[0015] Step 8: Compare the total pressure loss coefficient of the support obtained in Step 7 with the preset loss value requirement. If the requirement is met, proceed to Step 9. If the requirement is not met, adjust the support profile parameters given in Step 2 and repeat Step 3 to Step 8.

[0016] Step 9: Construct the solid model of the support column. In the 3D modeling software, use the blending function to blend the support column root section outline and top section outline obtained in Step 3 to obtain the solid model of the support column.

[0017] Preferably, in step 1, the input parameters for the support column design include: determining the number of supports n and the maximum axial width L based on the support column size and space requirements. z Based on the load-bearing requirements of the gas turbine turbine components, determine the supporting force N that the turbine transition section support needs to bear.

[0018] Preferably, in step 2, the parameters for constructing the external shape of the support root section include: the chord length L of the support root section. h Leading edge radius R LE,h Trailing edge radius R TE,h Maximum thickness T max,h The parameters for constructing the external shape of the top section of the column include: the chord length L of the top section of the column. t Leading edge radius RLE,t Trailing edge radius R TE,t Maximum thickness T max,t .

[0019] Preferably, in step 3, the airfoil design program is used to construct the outer profile lines of the support root section and the outer profile lines of the support top section, respectively.

[0020] Preferably, in step 5, the strength reserve coefficients of the support root section and the support top section are as shown in equations (1) to (2):

[0021]

[0022]

[0023] Where, σ b σ is the tensile strength of the support material. h The stress at the root section of the support column is σ. t Stress at the top section of the support column:

[0024]

[0025]

[0026] In the formula, A h Let A be the cross-sectional area of ​​the support root section. t Let N be the cross-sectional area of ​​the top section of the support column, N be the supporting force that the support column needs to bear, and n be the number of support columns.

[0027] Preferably, in step 6, the support strength reserve requirement includes: 1.35 ≤ k h ≤1.4, 1.35≤k t ≤1.4.

[0028] Preferably, in step 7, the total pressure loss coefficient v of the support is as shown in equation (5):

[0029]

[0030] in, For the total pressure of imports, This is the total export pressure.

[0031] Preferably, in step 8, the total pressure loss coefficient of the support column is less than or equal to the preset loss coefficient.

[0032] In addition to providing a design method for a turbine transition section support with large and small support plates, the present invention further provides a design system for a turbine transition section support with large and small support plates to implement the above method. The system includes: a parameter calculation module, a profile construction module, a performance analysis module, and a main control module.

[0033] The parameter calculation module is used to calculate the cross-sectional area of ​​the support root section, the cross-sectional area of ​​the support top section, the stress of the support root section, the stress of the support top section, the strength reserve coefficient of the support root section, and the strength reserve coefficient of the support top section, and sends the calculation results to the performance analysis module. The input of the parameter calculation module is the parameters related to the calculation of the cross-sectional area of ​​the support root section, the cross-sectional area of ​​the support top section, the stress of the support root section, the stress of the support top section, the strength reserve coefficient of the support root section, and the strength reserve coefficient of the support top section.

[0034] The profile construction module is used to construct the profile of the support column based on the profile parameters, and then send the constructed profile of the support column to the performance analysis module.

[0035] The performance analysis module is pre-set with the total pressure loss value and strength reserve requirements for the support strut. It is used to perform three-dimensional aerodynamic performance analysis on the constructed strut profile and compare the analysis results with the pre-set total pressure loss value. The performance analysis module is also used to assess the strength of the constructed strut profile to determine whether it meets the fairing strength reserve requirements. The performance analysis module sends the analysis results to the main control module.

[0036] Based on the analysis results, the main control module selects to output the support model or sends parameter adjustment commands to the parameter calculation module and the profile construction module.

[0037] Compared with the prior art, the present invention has the following advantages:

[0038] This invention provides a design method and system for a turbine transition section support column with large and small support plates. Based on the structural characteristics of the turbine transition section with large and small support plates, this method reorganizes and standardizes the design process for the support column (equivalent to the small support plate) and the working conditions of axial intake and exhaust, and advances the strength assessment process. This not only helps to speed up the design process of the turbine transition section support column, but also helps to obtain a support column structure with less loss and better structural strength.

[0039] The turbine transition section support design system with large and small support plates provided by this invention can automate the entire support design process without human intervention. Combined with the parametric design of the turbine transition section fairing, it can realize the parametric design and calculation analysis of the turbine transition section, laying a solid foundation for the rapid optimization design of the turbine transition section.

[0040] The turbine transition section support column design method proposed in this invention is a single-unit structure with a simple column shape, low manufacturing difficulty and low cost. It can be produced by forging, and its load-bearing capacity is significantly improved compared with the cast support column designed by traditional design methods. Attached Figure Description

[0041] Figure 1 This is a flowchart of a turbine transition section support design method with large and small support plates in this invention;

[0042] Figure 2 This is a schematic diagram of the support column arrangement in an embodiment of the present invention;

[0043] Figure 3 This is a schematic diagram illustrating the calculation of cross-sectional area in an embodiment of the present invention;

[0044] Figure 4 The three-dimensional calculation results of the support column outline in the embodiment of the present invention;

[0045] Figure 5 This is a diagram of the pillar model constructed in an embodiment of the present invention.

[0046] In the diagram, 1 represents the fairing; 2 represents the support column. Detailed Implementation

[0047] The present invention will now be described in further detail 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 not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0048] like Figure 1 As shown, the technical solution of the present invention provides a design method for a turbine transition section support with large and small support plates, including the following steps:

[0049] Step 1: Determine the number of supports n and the maximum axial width L based on the space requirements of the supports. z Based on the load-bearing requirements of the gas turbine turbine components, determine the required support force N of the turbine transition section struts; the strut arrangement is as follows. Figure 2 As shown, there are 6 evenly distributed around the circumference, of which 1 is the fairing and 2 is the support.

[0050] Step 2: Based on the existing unit, determine the parameters used to construct the support column profile, including the parameters for constructing the support column root section outline and the support column top section outline. The parameters for constructing the support column root section outline include: the chord length L of the support column root section. h Leading edge radius R LE,h Trailing edge radius R TE,h Maximum thickness T max,h The parameters for constructing the external shape of the column top section include: the chord length L of the column top section. t Leading edge radius R LE,t Trailing edge radius R TE,t Maximum thickness T max,t .

[0051] Step 3: Using the Autoblade airfoil design program, construct the support root section outer profile and the support top section outer profile based on the support profile construction parameters determined in Step 2;

[0052] Step 4: As Figure 3 As shown, based on the support root section outline and support top section outline obtained in step 3, the cross-sectional area A of the support root section is calculated in UG software. h and the cross-sectional area A of the top section of the support column t In this embodiment, the cross-sectional areas of the root section and the top section are obtained by the following method:

[0053] First, the root section and top section outlines of the support column are constructed using the airfoil software AutoBlade, allowing direct reading of their area values. Then, these outlines are imported into the 2D modeling software AutoCAD, where they are created as regions, allowing direct reading of their area values. Finally, the root and top section outlines are imported into the 3D modeling software UG NX, where they are created as surfaces, allowing direct reading of their cross-sectional areas.

[0054] Step 5: Evaluate the strength of the column section, and calculate the strength reserve factor of the column root section and the strength reserve factor of the column top section:

[0055] The strength reserve coefficients of the support root section and the support top section are shown in equations (1) and (2):

[0056]

[0057]

[0058] Where, σ b σ is the tensile strength of the support material. h The stress at the root section of the support column is σ. t Stress at the top section of the support column:

[0059]

[0060]

[0061] In the formula, A h Let A be the cross-sectional area of ​​the support root section. t Let N be the cross-sectional area of ​​the top section of the support column, N be the supporting force that the support column needs to bear, and n be the number of support columns.

[0062] Step 6: Compare the strength reserve coefficients of the support root section and the support top section calculated in Step 5 with the preset strength reserve coefficients. If they meet the design requirements, for example, 1.35≤k h ≤1.4, 1.35≤k t If the value is ≤1.4, proceed to step 7. If the requirement is not met, repeat steps 2 to 6.

[0063] Step 7: Perform a full three-dimensional aerodynamic performance analysis on the support structure, analyze the internal flow state, and obtain the total pressure loss coefficient ξ of the support structure as shown in equation (5):

[0064]

[0065] in, For the total pressure of imports, Given the total outlet pressure, in this embodiment, the flow state inside the support column is as follows: Figure 4 As shown.

[0066] Step 8: Compare the total pressure loss coefficient of the support obtained in Step 7 with the preset loss value requirement. If the requirement is met, such as ξ≤0.004, proceed to Step 9. If the requirement is not met, adjust the support profile parameters given in Step 2 and repeat Step 3 to Step 8.

[0067] Step 9: Construct the solid model of the support column. In UG NX 3D modeling software, use the blending function to blend the root section outline and the top section outline of the support column obtained in Step 3 to obtain the solid model of the support column, as shown below. Figure 5 As shown.

[0068] In this embodiment, the software used includes: modeling software AutoCAD / UG NX, airfoil software AutoBlade, full three-dimensional aerodynamic performance analysis program CFX / NUMECA, and strength analysis software ANSYS.

[0069] In addition to providing a design method for a turbine transition section support with large and small support plates, the present invention further provides a design system for a turbine transition section support with large and small support plates to implement the above method. The system includes: a parameter calculation module, a profile construction module, a performance analysis module, and a main control module.

[0070] The parameter calculation module is used to calculate the cross-sectional area of ​​the support root section, the cross-sectional area of ​​the support top section, the stress of the support root section, the stress of the support top section, the strength reserve coefficient of the support root section, and the strength reserve coefficient of the support top section, and sends the calculation results to the performance analysis module. The input of the parameter calculation module is the parameters related to the calculation of the cross-sectional area of ​​the support root section, the cross-sectional area of ​​the support top section, the stress of the support root section, the stress of the support top section, the strength reserve coefficient of the support root section, and the strength reserve coefficient of the support top section.

[0071] The profile construction module is used to construct the profile of the support column based on the profile parameters, and then send the constructed profile of the support column to the performance analysis module.

[0072] The performance analysis module is pre-set with the total pressure loss value and strength reserve requirements for the support strut. It is used to perform three-dimensional aerodynamic performance analysis on the constructed strut profile and compare the analysis results with the pre-set total pressure loss value. The performance analysis module is also used to assess the strength of the constructed strut profile to determine whether it meets the fairing strength reserve requirements. The performance analysis module sends the analysis results to the main control module.

[0073] Based on the analysis results, the main control module selects to output the support model or sends parameter adjustment commands to the parameter calculation module and the profile construction module.

[0074] In summary, this invention provides a design method that can meet the working requirements of a gas turbine turbine transition section support with support plates of different sizes. It can quickly obtain a support with excellent aerodynamic performance and suitable function, accelerate the design process of turbine transition sections with support plates of different sizes, and improve the design speed and efficiency of turbine transition sections.

[0075] The above are preferred embodiments of the present invention. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A design method for a turbine transition section support column with large and small support plates, characterized in that: The method includes the following steps: Step 1: Determine the input parameters for the support column design; Step 2: Determine the parameters used to construct the column profile, including the parameters for constructing the column root section outline and the column top section outline; Step 3: Construct the external profile of the support root section and the external profile of the support top section according to the support profile construction parameters determined in Step 2; Step 4: Based on the support root section profile and support top section profile obtained in Step 3, calculate the cross-sectional area A of the support root section. h and the cross-sectional area A of the top section of the support column t ; Step 5: Evaluate the strength of the column section and calculate the strength reserve coefficient of the column root section and the strength reserve coefficient of the column top section; Step 6: Compare the strength reserve coefficients of the support root section and the support top section calculated in Step 5 with the preset strength reserve coefficients. If the requirements are met, proceed to Step 7. If the requirements are not met, repeat Step 2 to Step 6. Step 7: Perform a full three-dimensional aerodynamic performance analysis on the support structure to obtain the total pressure loss coefficient of the support structure; Step 8: Compare the total pressure loss coefficient of the support obtained in Step 7 with the preset loss value requirement. If the requirement is met, proceed to Step 9. If the requirement is not met, adjust the support profile parameters given in Step 2 and repeat Step 3 to Step 8. Step 9: Construct the solid model of the support column. In the 3D modeling software, use the blending function to blend the support column root section outline and top section outline obtained in Step 3 to obtain the solid model of the support column.

2. The design method for a turbine transition section support column with large and small support plates as described in claim 1, characterized in that: In step 1, the input parameters for the support column design include: determining the number of supports n and the maximum axial width L based on the space requirements of the support column dimensions. z Based on the load-bearing requirements of the gas turbine turbine components, determine the supporting force N that the turbine transition section support needs to bear.

3. The design method for a turbine transition section support column with large and small support plates as described in claim 2, characterized in that: In step 2, the parameters for constructing the external shape of the support root section include: the chord length L of the support root section. h Leading edge radius R LE,h Trailing edge radius R TE,h Maximum thickness T max,h The parameters for constructing the external shape of the column top section include: the chord length L of the column top section. t Leading edge radius R LE,t Trailing edge radius R TE,t Maximum thickness T max,t .

4. The design method for a turbine transition section support column with large and small support plates as described in claim 3, characterized in that: In step 3, the airfoil design program is used to construct the outer profile of the support root section and the outer profile of the support top section, respectively.

5. The design method for a turbine transition section support column with large and small support plates as described in claim 4, characterized in that: In step 5, the strength reserve coefficients of the support root section and the support top section are shown in equations (1) to (2): Where, σ b σ is the tensile strength of the support material. h The stress at the root section of the support column is σ. t Stress at the top section of the support column: In the formula, A h Let A be the cross-sectional area of ​​the support root section. t Let N be the cross-sectional area of ​​the top section of the support column, N be the supporting force that the support column needs to bear, and n be the number of support columns.

6. The design method for a turbine transition section support column with large and small support plates as described in claim 5, characterized in that: In step 6, the support strength reserve requirement includes: 1.35 ≤ k h ≤1.4, 1.35≤k t ≤1.

4.

7. The design method for a turbine transition section support column with large and small support plates as described in claim 6, characterized in that: In step 7, the total pressure loss coefficient ξ of the support column is as shown in equation (5): in, For the total pressure of imports, This is the total export pressure.

8. The design method for a turbine transition section support column with large and small support plates as described in claim 7, characterized in that: In step 8, the total pressure loss coefficient of the support column is less than or equal to the preset loss coefficient.

9. A turbine transition section support design system with large and small support plates, characterized in that: The system is used to implement the turbine transition section support design method according to any one of claims 1-8, and the system includes: a parameter calculation module, a profile construction module, a performance analysis module, and a main control module; The parameter calculation module is used to calculate the cross-sectional area of ​​the support root section, the cross-sectional area of ​​the support top section, the stress of the support root section, the stress of the support top section, the strength reserve coefficient of the support root section, and the strength reserve coefficient of the support top section, and sends the calculation results to the performance analysis module. The input of the parameter calculation module is the parameters related to the calculation of the cross-sectional area of ​​the support root section, the cross-sectional area of ​​the support top section, the stress of the support root section, the stress of the support top section, the strength reserve coefficient of the support root section, and the strength reserve coefficient of the support top section. The profile construction module is used to construct the profile of the support column according to the profile parameters of the support column, and send the constructed profile of the support column to the performance analysis module. The performance analysis module is preset with a total pressure loss value and a strength reserve requirement for the support column. It is used to perform three-dimensional aerodynamic performance analysis on the constructed support column shape and compare the analysis results with the preset total pressure loss value. The performance analysis module is also used to evaluate the strength of the constructed support column shape and determine whether it meets the fairing strength reserve requirement. The performance analysis module sends the analysis results to the main control module; Based on the analysis results, the main control module selects to output the support model or sends parameter adjustment instructions to the parameter calculation module and the profile construction module.

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