Theoretical calculation method for throat area of turbine guide vane
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AECC SHENYANG ENGINE RES INST
- Filing Date
- 2025-12-08
- Publication Date
- 2026-07-10
Smart Images
Figure CN121594826B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aero-engine technology, and specifically relates to a theoretical calculation method for the throat area of a turbine guide vane. Background Technology
[0002] The size of the throat area of turbine guide vanes directly affects the flow capacity of turbine components, and thus the performance of the engine. For heat insulation and cooling purposes, current turbine guide vanes are often coated with thermal barrier coatings, and the thickness of these coatings affects the throat area. Due to limitations in heat insulation requirements and coating processes, the thickness of the thermal barrier coating on the surface of the turbine guide vanes is often uneven.
[0003] Currently, the evaluation of the throat area of turbine guide vanes with thermal barrier coatings is mostly based on calculations of the wall without thermal barrier coatings, and then the coating thickness is directly subtracted from the obtained throat area window. However, this method has two drawbacks:
[0004] 1) The throat area position before spraying is still used. For uneven coatings, this position has shifted, which will directly affect the actual area measurement results.
[0005] 2) The theoretically calculated throat area is inaccurate, which will have an adverse effect on engine performance evaluation, engine tuning, and blade manufacturing control.
[0006] Therefore, a theoretical calculation method for the throat area of turbine guide vanes is needed. Summary of the Invention
[0007] The purpose of this application is to provide a theoretical calculation method for the throat area of a turbine guide vane, so as to solve or alleviate at least one of the problems in the background art.
[0008] The technical solution of this application is: a theoretical calculation method for the throat area of a turbine guide vane, comprising:
[0009] Obtain the set of blade data coordinate points on the blade body of the turbine guide vane, both on the blade head and back sides;
[0010] Obtain the set of coordinate points for the flow channel surfaces of the upper and lower edge plates of the turbine guide vanes;
[0011] The thermal barrier coating thickness of turbine guide vanes with different cross sections was designed to obtain coating thickness matrices with different radius heights and different arc lengths.
[0012] The flow channel surface of each region of the coated turbine guide vane is obtained based on the blade data coordinate point set, the flow channel surface data coordinate point set, and the coating thickness matrix.
[0013] Spline curves are used to represent the intersection lines of cylindrical cross-sections with different radii and heights with the flow channel surfaces of coated turbine guide vanes in different regions, on the basin side and back side.
[0014] Find the shortest distance between the basin-side and back-side spline curves at the same radius and height, and determine the location points of the shortest distance on the basin-side and back-side spline curves;
[0015] Determine the solution range of the position points on the basin side and back side spline curves. Select a point from the solution range of the position points on the basin side and back side spline curves respectively, connect the two points to form a line segment, project the line segment of the blade tip onto the upper edge plate flow channel surface to obtain the first distance formed by the minimum distance between the line segment and the projected curve, and project the line segment of the blade heel onto the lower edge plate flow channel surface to obtain the second distance formed by the minimum distance between the line segment and the projected curve. Based on the shortest distance between the basin side and back side spline curves at the same height, solve for the minimum distance between the two skew shortest distances to obtain the third distance.
[0016] The expression for the throat area of a turbine guide vane is constructed based on line segments and their corresponding distances. By adjusting the selected radius and height, the throat area obtained by the expression is minimized, and this minimum area is the throat area of the turbine guide vane.
[0017] Preferably, the process of obtaining the set of blade data coordinate points on the blade side and back side of the turbine guide vane is as follows:
[0018] A three-dimensional model of a single turbine guide vane is constructed. Multiple cylindrical cross-sections with different radii and heights are intersected with the pressure and suction surfaces with different radial heights of the turbine guide vane three-dimensional model to obtain the set of blade data coordinate points on the blade's basin side and back side.
[0019] Preferably, the process of obtaining the set of coordinate points of the flow channel surface of the upper and lower edge plates of the turbine guide vane is as follows:
[0020] A curve is selected on the flow channel surface of the upper and lower edge plates of the turbine guide vane, and the curve is discretized and rotated along the engine axis by a predetermined angle to form a set of flow channel surface data coordinate points for the corresponding edge plates.
[0021] Preferably, the predetermined angle r = 360 / m, where m is the number of blades in the entire ring.
[0022] Preferably, when the amount of data in the coating thickness matrix is less than a predetermined value, the coating thickness matrix is encrypted using the blade data coordinate point set and the flow channel surface data coordinate point set.
[0023] Preferably, the process of obtaining the flow channel surface of each region of the coated turbine guide vane based on the blade data coordinate point set, the flow channel surface data coordinate point set, and the coating thickness matrix is as follows:
[0024] Calculate the normal direction of each coordinate point in the blade data coordinate point set and the flow channel surface data coordinate point set. Move the blade data coordinate point set and the flow channel surface data coordinate point set along the normal direction using the coating thickness matrix to obtain the flow channel surface coordinate point set with coating. Then, refine the flow channel surface coordinate point set with coating using interpolation to obtain the flow channel surface of each region of the coated turbine guide vane.
[0025] Preferably, the spline curve of the intersection line of the basin and the side is:
[0026] ;
[0027] The spline curve of the back-side intersection is:
[0028] .
[0029] Preferably, the solution range for the position points on the spline curve of the back-side intersection is A = (tP - dt1, tP + dt2), and the solution range for the position points on the back-side spline curve is B = (tS - dt3, tS + dt4), where tP and tS are the position points of the shortest distance on the basin-side and back-side spline curves, respectively, and dt1, dt2, dt3, and dt4 are the error ranges.
[0030] Preferably, the expression for the throat area of the turbine guide vane is:
[0031]
[0032] In the formula, PS j To connect two points to form a line segment, PS1 is the line segment at the tip of the blade. n Let d be the line segment representing the high heel of the leaf. j To obtain the third distance by solving for the minimum distance between two skew shortest distances based on the shortest distance between the basin side and the back side spline curves at the same height, d1 is the first distance formed by the minimum distance between the line segment projected onto the upper edge plate flow channel surface at the blade tip and the projected curve. n+1 The second distance is the minimum distance between the line segment projected onto the flow channel surface of the lower edge plate and the projection curve of the line segment at the heel of the blade. n is the number of cylindrical cross-sections with different radii and heights, and j∈[2,n].
[0033] The method of this application can improve the accuracy of numerical and positional assessment of the throat area of turbine guide vanes with non-uniform coatings, which is beneficial for performance evaluation of turbine guide vanes, engine tuning, and blade processing and production control. Attached Figure Description
[0034] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.
[0035] Figure 1 This is a schematic diagram of the theoretical calculation method for the throat area of the turbine guide vane in this application.
[0036] Figure 2 A schematic diagram of the curve selected for the upper edge plate flow channel surface in this application.
[0037] Figure 3 This is a schematic diagram of a curve selected within the upper edge plate in one embodiment of this application.
[0038] Figure 4 This is a schematic diagram of the basin-back side spline curve and the shortest distance in this application. Detailed Implementation
[0039] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.
[0040] To improve the accuracy of the numerical and positional assessment of the throat area of turbine guide vanes, this application proposes a theoretical calculation method for the throat area of turbine guide vanes.
[0041] like Figure 1 As shown, the theoretical calculation method for the throat area of turbine guide vanes provided in this application includes:
[0042] S10: Obtain the set of blade data coordinate points on the blade side and back side of the turbine guide vane.
[0043] like Figure 2 The image shows a 3D model of a single turbine guide vane constructed using UG 3D software in this embodiment of the application. A cylindrical coordinate system is established with the X-axis containing the engine axis as the axis. K cylindrical cross-sections with radius and height R are selected and intersected with the pressure surface (bowl side) and suction surface (back side) of the turbine guide vane on the theoretical model to obtain intersection lines. The blade data coordinate point sets of the pressure surface intersection line and suction surface intersection line are extracted to obtain pressure surface data coordinate point set A and suction surface data coordinate point set B, respectively. Rotating the blade data coordinate point set around the engine axis by a predetermined angle forms an area window.
[0044] For example, in this embodiment of the application, five cylindrical cross-sections with different radii and heights are selected to intersect with the pressure surface and suction surface of the turbine guide vane. The radii and heights of these five cylindrical cross-sections are 365.24 mm, 360.24 mm, 355.24 mm, 350.24 mm, and 345.24 mm, respectively.
[0045] In this application, the predetermined angle r = 360 / m, where m is the number of blades in the entire ring. For example, in this embodiment of the application, the pressure surface data coordinate point set A can be rotated around the X-axis towards the suction surface by r = 360 / 42 = 8.5714 degrees to form an area window, where 42 is the number of blades in the entire ring. It can be understood that the above process can also be used to rotate the suction surface data coordinate point set by an angle r to form an area window in the same way.
[0046] S20: Obtain the set of coordinate points of the flow channel surface of the upper and lower edge plates of the turbine guide vane.
[0047] like Figure 3 As shown, in this embodiment of the application, a curve 2 is selected from the front end wall to the rear end wall on the flow channel surface of the upper edge plate 1 of the turbine guide vane. The curve 2 is discretized into a set of data coordinate points and rotated 0 to ±8.5714 degrees along the X-axis to finally form the data coordinate point set C of the upper edge plate flow channel surface. The data coordinate point set D of the lower edge plate flow channel surface is similar and will not be described again.
[0048] S30, the thermal barrier coating thickness of the turbine guide vanes with different cross sections was designed to obtain coating thickness matrices with different radius heights and different arc length positions.
[0049] For example, in this embodiment of the application, the thickness of the thermal barrier coating for plasma spraying with different radial cross sections is designed for the turbine guide vanes, resulting in coating thickness matrices A', B', C', and D' with different radii and arc lengths.
[0050] It should be noted that in this application, when the amount of coating thickness matrix A′~D′ data is small, the coating thickness matrix A′, B′, C′, D′ can be encrypted using an interpolation method based on the coordinate position data of the data coordinate point set A, B, C, D.
[0051] S40, based on the blade data coordinate point set, the flow channel surface data coordinate point set and the coating thickness matrix, the flow channel surface of each region of the coated turbine guide vane is obtained.
[0052] For example, in this application, the normal directions of the locations of each point in the blade data coordinate point sets A and B and the flow channel surface data coordinate point sets C and D are respectively denoted as... , , , By moving each coordinate point in the data coordinate point sets A, B, C, and D along the normal direction by distances from the coating thickness matrices A′, B′, C′, and D′, the data coordinate point sets A″, B″, C″, and D″ of the coated flow channel surface are obtained. Finally, spline interpolation can be used to refine the coordinate point sets A″, B″, C″, and D″ of the coated flow channel surface to obtain the flow channel surface of each region of the entire coated turbine guide vane, including the pressure surface, suction surface, and upper and lower edge plates.
[0053] S50 uses spline curves to represent the intersection of cylindrical cross-sections with different radii and heights with the coated flow channel surface.
[0054] In this application, n (n≥k) cylindrical cross-sections with radius and height R are selected, such that... , i∈[2,n], the intersection lines of cylindrical cross-sections with different radii and heights with the pressure and suction surfaces of the turbine guide vanes are selected. For example, in this embodiment of the application, n can be 10, that is, 10 cylindrical cross-sections with radii and heights R are selected to intersect with the pressure and suction surfaces of the turbine guide vanes.
[0055] In this application, spline curves are used to define the intersection lines of the coordinate point sets A″ and B″ of the coated flow channel surface at various radii and heights, where:
[0056] Spline curve of the pelvic side intersection line:
[0057]
[0058] spline curve of the back-side intersection line:
[0059] .
[0060] S60, calculate the shortest distance between the basin-side and back-side spline curves at the same radius and height, and then determine the location of the shortest distance on the basin-side and back-side spline curves.
[0061] In this application, the shortest distance d between the pelvic and dorsal spline curves at the same radius and height R is calculated, and the position points of the shortest distance d on the pelvic and dorsal spline curves are obtained, denoted as tP and tS respectively. Figure 4 In the diagram, mark 3 represents point tP, mark 4 represents point tS, and mark 9 represents the shortest distance d.
[0062] S70, determine the solution range of the position points on the basin side and back side spline curves, select a point from the solution range of the position points on the basin side and back side spline curves respectively, connect the two points to form a line segment, project the line segment of the blade tip onto the upper edge plate flow channel surface to obtain the first distance formed by the minimum distance between the line segment and the projected curve, project the line segment of the blade heel onto the lower edge plate flow channel surface to obtain the second distance formed by the minimum distance between the line segment and the projected curve, and solve the minimum distance between the two skew shortest distances based on the shortest distance between the basin side and back side spline curves at the same height to obtain the third distance.
[0063] In this application, for the point whose shortest distance is on the basin side, the solution range is A = (tP - dt1, tP + dt2), and for the point whose shortest distance is on the dorsal side, the solution range is B = (tS - dt3, tS + dt4). Points P and S are taken within the solution ranges A and B respectively, and the line segment formed by points P and S is PS. j , j∈[1,n], where dt1, dt2, dt3, and dt4 are the error ranges. In this embodiment of the application, the error ranges are set as follows: dt1=5mm, dt2=10mm, dt3=5mm, dt4=7mm. Ten cylindrical cross-sections with different radial heights are selected, therefore the line segment PS j j∈[1,10].
[0064] like Figure 4 The diagram shows the spline curve of the back side of the basin. Point 3 is tP, point 4 is tS, point 5 is tP-dt1, point 6 is tP+dt2, point 7 is tS-dt3, point 8 is tS+dt4, point 9 is the shortest distance d, and point 10 is the line segment PS.
[0065] In this application, the line segment PS1 at the uppermost blade tip is projected onto the upper edge plate flow channel surface, and the distance between line segment PS1 and the projected curve is d1. The line segment PS1 at the lowermost blade root is also projected onto the upper edge plate flow channel surface. n Projected onto the flow channel surface of the lower edge plate, this line segment PS n The distance between the projection curve and the projection curve is d n+1 The minimum distance between two skew lines is obtained by finding the shortest distance between spline curves on the basin side and the back side under the same radius and height R, thus yielding the distance d. j , j∈[2,n].
[0066] S80, based on line segments and corresponding distances, constructs an expression for the throat area of the turbine guide vane. By adjusting the selected radius and height, the throat area obtained by the expression is minimized, and this minimum area is the throat area of the turbine guide vane.
[0067] In this application, the expression for the turbine guide vane throat area constructed based on the line segments and corresponding distances in step S70 is as follows:
[0068] .
[0069] For example, in this embodiment of the application, 10 cylindrical cross-sections with different radii and heights are selected, and the expression for the throat area of the turbine guide vane is:
[0070] .
[0071] By varying the radius and height R to minimize the turbine throat area F, the turbine guide vane throat area becomes A = F. min The positions of the corresponding control points are the locations for subsequent geometric measurements of the throat area.
[0072] For example, in this embodiment of the application, the minimum area A = F is obtained by solving the problem. min =432.058mm 2 .
[0073] The method of this application can improve the accuracy of numerical and positional assessment of the throat area of turbine guide vanes with non-uniform coatings, which is beneficial for performance evaluation of turbine guide vanes, engine tuning, and blade processing and production control.
[0074] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A theoretical calculation method for the throat area of a turbine guide vane, characterized in that, include: Obtain the set of blade data coordinate points on the blade body of the turbine guide vane, both on the blade head and back sides; Obtain the set of coordinate points for the flow channel surfaces of the upper and lower edge plates of the turbine guide vanes; The thermal barrier coating thickness of turbine guide vanes with different cross sections was designed to obtain coating thickness matrices with different radius heights and different arc lengths. The flow channel surface of each region of the coated turbine guide vane is obtained based on the blade data coordinate point set, the flow channel surface data coordinate point set, and the coating thickness matrix. Spline curves are used to represent the intersection lines of cylindrical cross-sections with different radii and heights with the flow channel surfaces of coated turbine guide vanes in different regions, on the basin side and back side. Find the shortest distance between the basin-side and back-side spline curves at the same radius and height, and determine the location points of the shortest distance on the basin-side and back-side spline curves; Determine the solution range of the position points on the basin side and back side spline curves. Select a point from the solution range of the position points on the basin side and back side spline curves respectively, connect the two points to form a line segment, project the line segment of the blade tip onto the upper edge plate flow channel surface to obtain the first distance formed by the minimum distance between the line segment and the projected curve, and project the line segment of the blade heel onto the lower edge plate flow channel surface to obtain the second distance formed by the minimum distance between the line segment and the projected curve. Based on the shortest distance between the basin side and back side spline curves at the same height, solve for the minimum distance between the two skew shortest distances to obtain the third distance. An expression for the throat area of a turbine guide vane is constructed based on line segments and their corresponding distances. By adjusting the selected radius and height, the throat area obtained by the expression is minimized, thus obtaining the throat area of the turbine guide vane.
2. The theoretical calculation method for the throat area of a turbine guide vane as described in claim 1, characterized in that, The process of obtaining the set of blade data coordinate points on the blade side and back side of the turbine guide vane is as follows: A three-dimensional model of a single turbine guide vane is constructed. Multiple cylindrical cross-sections with different radii and heights are intersected with the pressure and suction surfaces with different radial heights of the turbine guide vane three-dimensional model to obtain the set of blade data coordinate points on the blade's basin side and back side.
3. The theoretical calculation method for the throat area of a turbine guide vane as described in claim 1, characterized in that, The process of obtaining the set of coordinate points for the flow channel surfaces of the upper and lower edge plates of the turbine guide vane is as follows: A curve is selected on the flow channel surface of the upper and lower edge plates of the turbine guide vane, and the curve is discretized and rotated along the engine axis by a predetermined angle to form a set of flow channel surface data coordinate points for the corresponding edge plates.
4. The theoretical calculation method for the throat area of a turbine guide vane as described in claim 3, characterized in that, The predetermined angle r = 360 / m, where m is the number of blades in the entire ring.
5. The theoretical calculation method for the throat area of a turbine guide vane as described in claim 1, characterized in that, When the amount of data in the coating thickness matrix is less than a predetermined value, the coating thickness matrix is encrypted using the blade data coordinate point set and the flow channel surface data coordinate point set.
6. The theoretical calculation method for the throat area of a turbine guide vane as described in claim 1, characterized in that, The process of obtaining the flow channel surface of each region of the coated turbine guide vane based on the blade data coordinate point set, the flow channel surface data coordinate point set, and the coating thickness matrix is as follows: Calculate the normal direction of each coordinate point in the blade data coordinate point set and the flow channel surface data coordinate point set. Move the blade data coordinate point set and the flow channel surface data coordinate point set along the normal direction using the coating thickness matrix to obtain the flow channel surface coordinate point set with coating. Then, refine the flow channel surface coordinate point set with coating using interpolation to obtain the flow channel surface of each region of the coated turbine guide vane.
7. The theoretical calculation method for the throat area of a turbine guide vane as described in claim 1, characterized in that, The solution range for the position points on the spline curve of the back-side intersection is A = (tP - dt1, tP + dt2), and the solution range for the position points on the back-side spline curve is B = (tS - dt3, tS + dt4), where tP and tS are the position points of the shortest distance on the basin-side and back-side spline curves, respectively, and dt1, dt2, dt3, and dt4 are the error ranges.
8. The theoretical calculation method for the throat area of a turbine guide vane as described in claim 7, characterized in that, The expression for the throat area of the turbine guide vane is: ； In the formula, PS j To connect two points and form a line segment, PS1 is a line segment along the tip of the blade. n Let d be the line segment along the heel of the leaf. j To obtain the third distance by solving for the minimum distance between two skew shortest distances based on the shortest distance between the basin side and the back side spline curves at the same height, d1 is the first distance formed by the minimum distance between the line segment projected onto the upper edge plate flow channel surface at the blade tip and the projected curve. n+1 The second distance is the minimum distance between the line segment projected onto the flow channel surface of the lower edge plate and the projection curve of the line segment at the heel of the blade. n is the number of cylindrical cross-sections with different radii and heights, and j∈[2,n].