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

Abstract

The application discloses a turbine transition section fairing design method and system with large and small support plates, and specifically comprises the following steps: determining the inside pipe diameter of the fairing, the maximum thickness of the fairing outer shape line and the fairing outer shape line parameters; constructing the fairing outer shape line according to the determined fairing parameters; performing full three-dimensional aerodynamic performance analysis on the fairing outer shape to obtain the total pressure loss coefficient of the fairing; constructing the fairing inner cavity line according to the analysis results of the loss coefficient meeting the predetermined loss value requirement; performing fairing cross-section strength evaluation, and further constructing the final fairing entity model for the fairing interface meeting the strength reserve requirement. The fairing design method provided by the application meets the cooling air supply, oil supply and oil return pipeline arrangement requirements of the turbine transition section fairing design condition with large and small support plates, can quickly obtain a fairing with excellent aerodynamic performance and suitable functions, 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 fairing 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 current design methods employ a complex surface structure similar to turbine guide vanes for the fairing. This approach limits fairing thickness, resulting in small areas for individual cooling air supply, lubricating oil supply, and return lines. A large number of fairings are required to meet the flow requirements for these functions. Furthermore, the complex fairing profiles designed using these methods lead to significant manufacturing difficulties, high costs, and unsuitability for axial intake / exhaust.

[0005] Therefore, there is currently a lack of a design method for turbine transition section fairings with large and small support plates, especially a fairing design method that can meet the requirements of cooling air supply, lubricating oil supply and return pipeline layout, and is suitable for axial air 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 fairing with large and small support plates, which meets the working requirements of the turbine transition section fairing of a gas turbine with large and small support plates, and avoids the problem that the fairing cannot meet the aerodynamic performance and cooling air and lubricating oil supply requirements due to inappropriate fairing parameter selection.

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

[0008] Step 1: Determine the internal piping diameter φ of the fairing based on the diameters of the cooling air supply pipe, lubricating oil supply pipe, and lubricating oil return pipe. ZLZ ;

[0009] Step 2: Determine the maximum thickness T of the fairing profile. max ;

[0010] Step 3: Determine the fairing profile parameters, including chord length L and leading edge radius R. LE and trailing edge radius R TE ;

[0011] Step 4: Based on the maximum thickness T of the fairing profile obtained in Step 2. max Using the fairing profile parameters obtained in step 3, construct the fairing profile.

[0012] Step 5: Perform a full three-dimensional aerodynamic performance analysis on the fairing shape to obtain the total pressure loss coefficient of the fairing;

[0013] Step 6: Compare the total pressure loss coefficient of the fairing obtained in Step 5 with the preset loss value requirement. If the requirement is met, proceed to Step 7. If the requirement is not met, repeat Step 3 to Step 5.

[0014] Step 7: Construct the fairing inner cavity profile;

[0015] Step 8: Perform strength assessment calculations on the fairing cross-section. The calculated parameters include the normal stress and axial stress of the fairing caused by airflow pressure.

[0016] Step 9: Compare the fairing strength reserve requirement with the calculation result of Step 8. If the calculation result meets the fairing strength reserve requirement, proceed to Step 10. If the calculation result does not meet the strength reserve requirement, repeat Step 7 to Step 9.

[0017] Step 10: Stretch the fairing outer profile obtained in Step 4 and the fairing inner cavity profile designed in Step 7 to obtain the fairing solid model.

[0018] Preferably, the diameter of the internal pipes of the fairing in step 1 can be obtained by formula (1):

[0019] φ ZLZ =max(φ air φ oil，in φ air，out (1)

[0020] Where, φ air φ oil，in φ air，out These refer to the diameters of the cooling air supply pipe, the lubricating oil supply pipe, and the lubricating oil return pipe, respectively.

[0021] Preferably, in step 2, the maximum thickness of the fairing profile can be expressed as:

[0022] T max =φ ZLZ +Δ+δ (2)

[0023] Where Δ is the fairing wall thickness and δ is the assembly clearance of the internal pipelines of the fairing.

[0024] Preferably, in step 4, airfoil design software is used, combined with the maximum thickness T of the fairing profile obtained in step 2. max Using the fairing profile parameters obtained in step 3, construct the fairing profile.

[0025] Preferably, in step 5, the total pressure loss coefficient ξ of the fairing is as shown in equation (3):

[0026]

[0027] in, For the total pressure of imports, This is the total export pressure.

[0028] Preferably, in step 6, the total pressure loss coefficient of the fairing is less than or equal to the preset loss coefficient.

[0029] Preferably, in step 7, based on the fairing shape obtained in step 4, a thickness Δ is offset into the interior of the fairing to obtain the fairing inner cavity profile.

[0030] Preferably, in step 8, the normal stress and axial stress of the fairing caused by the airflow pressure are as shown in equations (4) and (5):

[0031]

[0032]

[0033] Where, σ N σ is the normal stress on the fairing caused by airflow pressure. Z This refers to the axial stress generated by the airflow pressure on the fairing.

[0034] Preferably, in step 9, the fairing strength reserve requirement is: σ N ≤[σ N And σ z ≤[σ Z ].

[0035] In addition to providing a design method for a turbine transition section fairing with large and small support plates, the present invention further provides a design system for a turbine transition section fairing 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.

[0036] The parameter calculation module is used to calculate the diameter of the internal pipes of the fairing, the maximum thickness of the fairing profile, and the external parameters of the fairing, and sends the calculation results to the profile construction module. The input of the parameter calculation module is the parameters related to the calculation of the internal pipe diameter, the maximum thickness of the fairing profile, and the external parameters of the fairing.

[0037] The profile construction module receives the calculation results from the parameter calculation module, constructs the outer profile and inner cavity profile of the fairing, and sends the constructed outer profile and inner cavity profile to the performance analysis module.

[0038] The performance analysis module is pre-set with a total pressure loss value and a strength reserve requirement for the fairing. It performs three-dimensional aerodynamic performance analysis on the constructed fairing profile and compares the results with the pre-set total pressure loss value. The module also assesses the strength of the constructed fairing's internal cavity profile to determine if it meets the strength reserve requirement. The performance analysis module then sends the analysis results to the main control module.

[0039] Based on the analysis results, the main control module selects to output the fairing model or sends parameter adjustment instructions to the parameter calculation module.

[0040] Compared with the prior art, the present invention has the following advantages:

[0041] This invention provides a design method and system for a turbine transition section fairing with large and small support plates. Based on the structural characteristics of the turbine transition section with large and small support plates, and considering the requirements for the arrangement of cooling air supply, lubricating oil supply and return pipelines inside the fairing (corresponding to the large support plate), as well as the working conditions of axial air intake and exhaust, the design process is reorganized and standardized. This is beneficial to accelerate the design process of the turbine transition section fairing and can result in a fairing structure with less loss and excellent structural strength.

[0042] This invention can quickly produce a fairing 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.

[0043] The turbine transition section fairing design system with large and small support plates proposed in this invention can automate the entire fairing design process without human intervention. Combined with the parametric design of the turbine transition section support, 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.

[0044] The fairing designed using the turbine transition section fairing design method with large and small support plates proposed in this invention has a simple shape, is less difficult to manufacture and process, and has a lower cost. Attached Figure Description

[0045] Figure 1 This is a flowchart of a turbine transition section fairing design method with large and small support plates in this invention;

[0046] Figure 2 This is a schematic diagram illustrating the method for determining the inner diameter of the fairing in an embodiment of the present invention;

[0047] Figure 3 This is a schematic diagram of fairing design parameters in an embodiment of the present invention;

[0048] Figure 4 This is a schematic diagram of the fairing profile constructed in an embodiment of the present invention;

[0049] Figure 5 The above are the three-dimensional calculation results of the fairing outline in the embodiments of the present invention;

[0050] Figure 6 This is a schematic diagram of the inner cavity profile of the fairing constructed in an embodiment of the present invention;

[0051] Figure 7 This is a schematic diagram of the fairing entity model constructed in an embodiment of the present invention.

[0052] In the diagram, 1 represents the cooling pipe; 2 represents the lubricating oil supply pipe; 3 represents the lubricating oil return pipe; 4 represents the outer profile of the fairing; and 5 represents the inner profile of the fairing. Detailed Implementation

[0053] 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.

[0054] 1. For example Figure 1 As shown, the technical solution of the present invention provides a design method for a turbine transition section fairing with large and small support plates.

[0055] Includes the following steps:

[0056] Step 1: Determine the internal piping diameter φ of the fairing based on the diameters of the cooling air supply pipe, lubricating oil supply pipe, and lubricating oil return pipe. ZLZ :

[0057] φ ZLZ =max(φ air ,φ oil,in ,φ air,out (1)

[0058] Where, φ air ,φ oil,in ,φ air,out These are the diameters of the cooling air supply pipe, lubricating oil supply pipe, and lubricating oil return pipe, respectively. The diameters of these pipes are determined based on the cooling air flow rate and lubricating oil flow rate. The internal diameter of the fairing is greater than or equal to the sum of the diameters and clearances of the cooling air supply pipe, lubricating oil supply pipe, and lubricating oil return pipe. A schematic diagram is shown below. Figure 2 As shown, 1 is the cooling pipe, 2 is the lubricating oil supply pipe, and 3 is the lubricating oil return pipe. Under normal circumstances, the lubricating oil return pipe has the largest diameter.

[0059] Specifically, the diameters of the cooling air supply pipe, lubricating oil supply pipe, and lubricating oil return pipe can be calculated using the following formula:

[0060]

[0061]

[0062]

[0063] Among them, G air For cooling air supply flow rate, V air For cooling air supply velocity, ρ air To cool the air density, G oil For lubricating oil supply flow rate, V oil,in For lubricating oil supply flow rate, ρ oil V is the density of lubricating oil. oil,in This refers to the return flow rate of the lubricating oil.

[0064] Step 2: Based on the existing units, determine the maximum thickness T of the fairing profile. max :like Figure 3 As shown, based on the given internal pipe diameter φ of the fairing... ZLZ The maximum thickness of the fairing profile can be obtained by summing the three factors: fairing wall thickness Δ, internal piping assembly clearance δ, and the fairing wall thickness Δ.

[0065] T max =φ ZLZ +Δ+δ (2)

[0066] Step 3: Determine the fairing profile parameters, including chord length L and leading edge radius R. LE and trailing edge radius R TE ;

[0067] Step 4: Using Autoblade airfoil design software, combined with the maximum thickness T of the fairing profile obtained in Step 2. max Using the fairing profile parameters obtained in step 3, construct the fairing profile to obtain the following: Figure 4 The fairing shape shown is shown in the figure, where 4 is the outer profile of the fairing and 5 represents the inner profile of the fairing cavity.

[0068] Step 5: Using a full three-dimensional aerodynamic performance analysis program, perform a full three-dimensional aerodynamic performance analysis on the fairing shape to obtain the total pressure loss coefficient ξ of the fairing as shown in equation (3):

[0069]

[0070] in, For the total pressure of imports, The three-dimensional calculation results of the fairing shape are as follows, representing the total outlet pressure. Figure 5 As shown.

[0071] Step 6: Compare the total pressure loss coefficient of the fairing obtained in Step 5 with the preset loss value requirement. If the requirement is met, proceed to Step 7. If the requirement is not met, repeat Steps 3 to 5. The total pressure loss coefficient of the fairing should be less than or equal to the preset loss coefficient, for example, ξ≤0.005.

[0072] Step 7: Based on the fairing shape obtained in Step 4, use the modeling software UG NX to offset the fairing shape lines with a thickness Δ towards the inside of the fairing, resulting in the following... Figure 6 The fairing inner cavity profile is shown;

[0073] Step 8: Perform strength assessment calculations on the fairing cross-section. The calculated parameters include the normal stress and axial stress of the fairing caused by airflow pressure.

[0074] The normal and axial stresses of the fairing caused by airflow pressure are shown in equations (4) and (5):

[0075]

[0076]

[0077] Where, σ N σ is the normal stress on the fairing caused by airflow pressure. Z This refers to the axial stress generated by the airflow pressure on the fairing.

[0078] Step 9: Compare the fairing strength reserve requirement with the calculation result of Step 8. If the calculation result meets the fairing strength reserve requirement, proceed to Step 10. If the calculation result does not meet the strength reserve requirement, repeat Steps 7 to 9. The fairing strength reserve requirement can be set as σ. N ≤[σ N And σ Z ≤[σ Z ].

[0079] Step 10: Using UG NX modeling software, extrude the fairing outer profile obtained in Step 4 and the fairing inner cavity profile designed in Step 7 to obtain the fairing solid model, such as... Figure 7 As shown.

[0080] 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.

[0081] In addition to providing a design method for a turbine transition section fairing with large and small support plates, the present invention further provides a design system for a turbine transition section fairing 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.

[0082] The parameter calculation module is used to calculate the diameter of the internal pipes of the fairing, the maximum thickness of the fairing profile, and the external parameters of the fairing, and sends the calculation results to the profile construction module. The input of the parameter calculation module is the parameters related to the calculation of the internal pipe diameter, the maximum thickness of the fairing profile, and the external parameters of the fairing.

[0083] The profile construction module receives the calculation results from the parameter calculation module, constructs the outer profile and inner cavity profile of the fairing, and sends the constructed outer profile and inner cavity profile to the performance analysis module.

[0084] The performance analysis module is pre-set with a total pressure loss value and a strength reserve requirement for the fairing. It performs three-dimensional aerodynamic performance analysis on the constructed fairing profile and compares the results with the pre-set total pressure loss value. The module also assesses the strength of the constructed fairing's internal cavity profile to determine if it meets the strength reserve requirement. The performance analysis module then sends the analysis results to the main control module.

[0085] Based on the analysis results, the main control module selects to output the fairing model or sends parameter adjustment instructions to the parameter calculation module.

[0086] 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 fairing with large and small support plates, characterized in that: The method includes the following steps: Step 1: Determine the internal piping diameter of the fairing based on the diameters of the cooling air supply pipe, lubricating oil supply pipe, and lubricating oil return pipe. ; Step 2: Determine the maximum thickness of the fairing's outer profile. The maximum thickness of the fairing's outer profile can be expressed as: （2） Where △ represents the fairing wall thickness. For the assembly clearance of the internal piping of the fairing; Step 3: Determine the fairing profile parameters, including chord length. Leading edge radius and trailing edge radius ; Step 4: Based on the maximum thickness of the fairing profile obtained in Step 2. Using the fairing profile parameters obtained in step 3, construct the fairing profile. Step 5: Perform a full three-dimensional aerodynamic performance analysis on the fairing shape to obtain the total pressure loss coefficient of the fairing; Step 6: Compare the total pressure loss coefficient of the fairing obtained in Step 5 with the preset loss value requirement. If the requirement is met, proceed to Step 7. If the requirement is not met, repeat Step 3 to Step 5. Step 7: Construct the fairing inner cavity profile. Based on the fairing outer shape obtained in Step 4, offset the thickness Δ inwards to obtain the fairing inner cavity profile. Step 8: Perform strength assessment calculations on the fairing cross-section. The calculated parameters include the normal stress and axial stress of the fairing caused by airflow pressure. Step 9: Compare the fairing strength reserve requirement with the calculation result of Step 8. If the calculation result meets the fairing strength reserve requirement, proceed to Step 10. If the calculation result does not meet the strength reserve requirement, repeat Step 7 to Step 9. Step 10: Stretch the fairing outer profile obtained in Step 4 and the fairing inner cavity profile designed in Step 7 to obtain the fairing solid model.

2. The turbine transition section fairing design method with large and small support plates as described in claim 1, characterized in that: The diameter of the internal pipes of the fairing in step 1 can be obtained by formula (1): （1） in, These refer to the diameters of the cooling air supply pipe, the lubricating oil supply pipe, and the lubricating oil return pipe, respectively.

3. The turbine transition section fairing design method with large and small support plates as described in claim 2, characterized in that: In step 4, airfoil design software is used, combined with the maximum thickness of the fairing profile obtained in step 2. Using the fairing profile parameters obtained in step 3, construct the fairing profile.

4. A turbine transition section fairing design method with large and small support plates as described in claim 3, characterized in that: In step 5, the total pressure loss coefficient of the fairing As shown in equation (3): （3） in, For the total pressure of imports, This is the total export pressure.

5. The turbine transition section fairing design method with large and small support plates as described in claim 4, characterized in that: In step 6, the total pressure loss coefficient of the fairing is less than or equal to the preset loss coefficient.

6. A turbine transition section fairing design method with large and small support plates as described in claim 5, characterized in that: In step 8, the normal stress and axial stress of the fairing due to the airflow pressure are as shown in equations (4) and (5): （4） （5） in, This refers to the normal stress on the fairing caused by airflow pressure. This refers to the axial stress generated by the airflow pressure on the fairing.

7. The turbine transition section fairing design method with large and small support plates as described in claim 6, characterized in that: In step 9, the fairing strength reserve requirement is as follows: and .

8. A turbine transition section fairing design system with large and small support plates, characterized in that: The system is used to implement the fairing design method according to any one of claims 1-7, 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 diameter of the internal pipes of the fairing, the maximum thickness of the fairing profile, and the external parameters of the fairing, and sends the calculation results to the profile construction module; the input of the parameter calculation module is the parameters related to the calculation of the internal pipe diameter, the maximum thickness of the fairing profile, and the external parameters of the fairing. The profile construction module receives the calculation results from the parameter calculation module, constructs the fairing outer profile and fairing inner cavity profile, and sends the constructed fairing outer profile and fairing inner cavity profile to the performance analysis module. The performance analysis module is preset with a total pressure loss value and a strength reserve requirement for the fairing. It is used to perform three-dimensional aerodynamic performance analysis on the constructed fairing profile 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 fairing inner cavity profile to 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 fairing model or sends parameter adjustment instructions to the parameter calculation module.

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