CN112507489A - Turbine guide blade and guide device throat area calculation method - Google Patents
Turbine guide blade and guide device throat area calculation method Download PDFInfo
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Abstract
The application belongs to the field of turbine guide blades of aero-engines, and particularly relates to a turbine guide blade and a guide device throat area calculation method. The method comprises the following steps: establishing a cylindrical coordinate system; determining a theoretical width sample molded line and a flange plate sample molded line; and (4) calculating the areas of the guide blades and the throat of the guide device of the turbine. According to the turbine guide blade and the guide device throat area calculation method, influence of concave structures such as a gas film hole and a tail cleft seam on throat area measurement is avoided; the problem of measurement difficulty caused by the limitation of the geometric space of the flow passage surface of the edge plate is solved; the problem that the width profile is cut out from the cross section parallel to the axis of the engine under different Z values, so that the width cross section is not distributed in the radial direction of a measuring channel, and larger errors are caused is solved; the influence of the arc surface of the edge plate and the fillet between the edge plate and the blade on the throat area is taken into account, and the calculation accuracy is improved.
Description
Technical Field
The application belongs to the field of turbine guide blades of aero-engines, and particularly relates to a turbine guide blade and a guide device throat area calculation method.
Background
The size of the throat area of the turbine guider directly influences the front and rear temperature and airflow flow field of a turbine stage, the flow, thrust, rotating speed, oil consumption rate and the like of an engine, has great influence on the stable work of the engine and the matching performance of a gas compressor and a turbine, and is an important parameter for determining the overall performance of the engine.
For turbine guide vanes, especially high-pressure turbine guide vanes, hundreds of air film holes are often distributed on the edge plate and the blade body, and the tail edge of the blade body is also often provided with a tail cleft. Due to the machining deviation of the actual blades, the throat areas of all the blades are difficult to be measured at the same measuring height and keep away from concave shapes such as air film holes, tail cleft seams and the like. This concave shape affects the profile of the surface profile. Thus causing large errors in the measurement and calculation of the throat area. Meanwhile, the measurement of the throat area is difficult due to the limitation of the space modeling of the blade and the reason that the flow passage surface of the edge plate is shielded.
At present, in engineering, a method for searching theoretical coordinate points of throat width and height on a blade body and a flange plate is mostly adopted to calculate the throat area of a blade cascade window. This approach does not solve the above-mentioned problems of film hole interference and edge plate shielding. In addition, in the existing method, due to casting differences of blade profiles or runner surfaces, the measurement position is not an actual blade throat coordinate point; for the twisted blade, the window height error calculated by the method is large. Meanwhile, the existing method adopts a rectangular coordinate system to measure and calculate the width of a plurality of throat area sections parallel to the axis of the engine, and the width sections are distributed in the radial direction of a measuring channel unevenly. And the influence of the arc surface of the edge plate and the fillet between the edge plate and the blade on the throat area is not taken into account. Therefore, the throat area error measured by the existing method is large.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a turbine guide blade and a guide device throat area calculation method to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
the application provides a method for calculating the area of a turbine guide blade and a throat of a guider, which comprises the following steps:
establishing a cylindrical coordinate system, wherein M (r, a and h) represents any point coordinate on a turbine guide blade or a guider, and the point M is represented as M (h, rcosa and rsina) in a rectangular coordinate system, wherein the h axis and the X axis are the axial direction of an engine, the Z axis represents the radial direction of the blade, r is the distance between an origin O and the projection M' of the point M on a plane YOZ, r belongs to [0, ∞ ], a is the angle rotated from the Y axis to OM in the counterclockwise direction from the view of a negative X axis, and a belongs to [0, 2 pi);
step two, determining a theoretical width sample profile and an edge plate sample profile, comprising:
s201, representing a window width molded line by using an intersection line of a cylindrical section and an outer molded surface of a blade under different r values, and determining the number k of groups of the width molded lines and the distribution thereof according to the radial blade profile distribution of the blade;
s202, measuring the minimum distance between two adjacent blade width molded lines under the same r value of a window, creating a width line segment where the minimum distance is located and corresponding width characteristic points, numbering the width line segments from the blade tip to the blade root as line segments 1 to k respectively, and setting the corresponding length as W1To Wk(ii) a The intersection points of the connecting lines of the end points of the two ends of the line segments 1 and 2 and the flow passage surface of the upper edge plate are respectively marked as a point S1 and a point S2, the connecting line of S1 and S2 is called a line segment 0, and the length of the line segment is W0; the intersection points of the connecting lines of the end points of the two ends of the line segments k-1 and k and the flow passage surface of the lower edge plate are respectively marked as points G1 and G2, the connecting lines of the points G1 and G2 are called line segments k +1, and the length of the line segments k +1 is Wk+1(ii) a The intersection point of the connecting line of the midpoints of the line segments 1 and 2 and the flow channel surface of the upper edge plate is marked as an S point; the intersection point of the connecting line of the midpoints of the line segments k-1 and k and the flow channel surface of the lower edge plate is marked as a point G; the distances between the middle points of the adjacent width line segments are respectively H2～Hk(ii) a The distance between the point S and the midpoint of the line segment 1 is H1The distance between the point G and the midpoint of the line segment k is Hk+1Is prepared from H1～Hk+1Referred to as window segment height;
s203, selecting a molded line with a proper length on the theoretical blade as a width sample molded line and an edge plate sample molded line, and enabling a theoretical width characteristic point to be located in the middle of the sample molded line, wherein the edge plate sample molded line comprises H coordinate values of a point S1, a point S2, a point G1 and a point G2;
step three, calculating the areas of the guide vanes of the turbine and the throat of the guider, and comprising the following steps of:
s301, scanning the width sample molded line and the edge plate sample molded line of each window of an actual turbine guide vane or guider coordinate system through three coordinates;
s302, deleting molded line coordinate points of the sample at the inward concave positions such as the air film hole, the tail cleft and the like;
s303, extending the edge plate sample molded line;
s304, interpolating a width sample profile and an edge plate sample profile;
s305, converting the molded line coordinate point of the edge plate sample into a cylindrical coordinate system and rotating around an h axis to form an edge plate runner surface;
s306, calculating the throat areas of the actual window, the turbine guide vane and the guider according to the following formulas:
therein, WWj＝(Wj-1+Wj)/2,(j＝1～k+1)，FiThroat area of a single window in the guide vane, FgIs the throat area of a group of guide vanes, F is the throat area of the guider, i is the window and channel serial number, j is the width line segment number, Wj *The length of a theoretical width line segment is defined, n means that each group of blades consists of n blades, and m guide devices consist of m blades;
c1on a theoretical model, a width line segment 1 is intersected with a plane where an S point is positioned, an upper edge plate and blade body molded surfaces on two sides of a channel, and the area enclosed by the intersection line and the width line segment 1 is identical to WW1H1The ratio of (A) to (B);
ck+1on the theoretical model, the width line section k intersects with the plane where the G point is located, the lower edge plate and the blade body molded surfaces at two sides of the channel, and the area enclosed by the intersection line and the width line section k is the same as WWk+1Hk+1The ratio of (a) to (b).
Optionally, in step S201, when determining the width profile of the turbine guide vane, selecting a middle height of two adjacent film holes as a height of the theoretical width profile.
Optionally, in step S302, the line coordinate points of the concave position samples such as the air film hole and the tail cleft are deleted by:
and S3021, calculating the slope of two adjacent points in the sample profile, wherein the slope k of the width sample profile is dy/dx, and the slope k of the edge plate sample profile is dz/dx.
And S3022, if the slope value suddenly increases, suddenly decreases after a preset distance, or suddenly decreases and suddenly increases after the preset distance, the curve is considered to pass through the air film hole, and relevant data points at the position are deleted.
Optionally, in step S303, the edge plate sample profile is extended by:
s3031, taking one point at one end of the edge plate sample molded line every 2-3 data points, and taking six points in total;
s3032, calculating the slope of each two adjacent points in the six points;
s3033, calculating the average value of the five slopes;
s3034, extending the molded line of the edge plate sample by a required length according to a straight line by using the average value of the slope and the point coordinate of the extreme end part of the molded line of the edge plate sample;
and S3035, repeating the steps S3031-S3034 at the other end of the edge plate sample molded line, and extending the edge plate sample molded line by a required length.
Optionally, in step S304, the coordinates of the exterior line of the compact blade at the deleted position are restored through three-dimensional spline interpolation calculation, and further, the coordinates of the width sample line and the edge plate sample line are encrypted.
The invention has at least the following beneficial technical effects:
according to the turbine guide blade and the guide device throat area calculation method, the influence of concave structures such as a gas film hole and a tail cleft on throat area measurement is avoided, and the precision is obviously improved; the problem of large throat area calculation error caused by over-short actually measured molded line of the edge plate sample due to geometrical space limitation is solved; the problem that the width profile is cut out from the cross section parallel to the axis of the engine under different Z values, so that the width cross section is not distributed in the radial direction of a measuring channel, and larger errors are caused is solved; the influence of the arc surface of the edge plate and the fillet between the edge plate and the blade on the throat area is taken into account, and the calculation result is more accurate.
Drawings
FIG. 1 is a flow chart of a method for calculating turbine guide vane and guide vane throat area according to an embodiment of the present application;
FIG. 2 is a schematic representation of a coordinate system for a turbine guide vane and guide vane throat area calculation method according to an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1-2.
The application provides a method for calculating the area of a turbine guide blade and a throat of a guider, which comprises the following steps:
s100, establishing a cylindrical coordinate system, as shown in FIG. 2:
representing the coordinate of any point on the turbine guide blade or the guider by M (r, a and h), wherein the point M is represented as M (h, rcosa and rsina) in a rectangular coordinate system, wherein an h axis and an X axis are the axial direction of the engine, a Z axis represents the radial direction of the blade, r is the distance between an origin O and the projection M' of the point M on a plane YOZ, and r belongs to [0 and infinity ], a is the angle rotated from the Y axis to OM in the counterclockwise direction from the negative X axis, and belongs to [0 and 2 pi ];
s200, determining a width molded line, and creating a width line segment and a width characteristic point according to the width molded line:
s201, representing a window width molded line by using an intersection line of a cylindrical section and an outer molded surface of a blade under different r values, and determining the number k of groups of the width molded lines and the distribution thereof according to the radial blade profile distribution of the blade;
s202, measuring the minimum distance between two adjacent blade width molded lines under the same r value of a window, creating a width line segment where the minimum distance is located and corresponding width characteristic points, numbering the width line segments from the blade tip to the blade root as line segments 1 to k respectively, and setting the corresponding length as W1To Wk(ii) a The intersection points of the connecting lines of the end points of the two ends of the line segments 1 and 2 and the flow passage surface of the upper edge plate are respectively marked as a point S1 and a point S2, the connecting line of S1 and S2 is called a line segment 0, and the length of the line segment is W0; the intersection points of the connecting lines of the end points of the two ends of the line segments k-1 and k and the flow passage surface of the lower edge plate are respectively marked as points G1 and G2, the connecting lines of the points G1 and G2 are called line segments k +1, and the length of the line segments k +1 is Wk+1(ii) a The intersection point of the connecting line of the midpoints of the line segments 1 and 2 and the flow channel surface of the upper edge plate is marked as an S point; of line segments k-1, kThe intersection point of the connecting line of the middle point and the flow channel surface of the lower edge plate is marked as a G point; the distances between the middle points of the adjacent width line segments are respectively H2～Hk(ii) a The distance between the point S and the midpoint of the line segment 1 is H1The distance between the point G and the midpoint of the line segment k is Hk+1Is prepared from H1～Hk+1Referred to as window segment height;
s203, selecting a molded line with a proper length on the theoretical blade as a width sample molded line and an edge plate sample molded line, and enabling a theoretical width characteristic point to be located in the middle of the sample molded line, wherein the edge plate sample molded line comprises H coordinate values of a point S1, a point S2, a point G1 and a point G2;
s300, calculating the area of the guide blade and the throat of the guide device of the turbine, comprising the following steps:
s301, scanning the width sample molded line and the edge plate sample molded line of each window of an actual turbine guide vane or guider coordinate system through three coordinates;
s302, deleting molded line coordinate points of the sample at the inward concave positions such as the air film hole, the tail cleft and the like;
s303, extending the edge plate sample molded line;
s304, interpolating a width sample profile and an edge plate sample profile;
s305, converting the molded line coordinate point of the edge plate sample into a cylindrical coordinate system and rotating around an h axis to form an edge plate runner surface;
s306, calculating the throat areas of the actual window, the turbine guide vane and the guider according to the following formulas:
therein, WWj＝(Wj-1+Wj)/2,(j＝1～k+1)，FiThroat area of a single window in the guide vane, FgIs the throat area of a group of guide vanes, F is the throat area of the guider, i is the window and channel serial number, j is the width line segment number, Wj *The length of a theoretical width line segment is defined, n means that each group of blades consists of n blades, and m guide devices consist of m blades;
c1on a theoretical model, a width line segment 1 is intersected with a plane where an S point is positioned, an upper edge plate and blade body molded surfaces on two sides of a channel, and the area enclosed by the intersection line and the width line segment 1 is identical to WW1H1The ratio of (A) to (B);
ck+1on the theoretical model, the width line section k intersects with the plane where the G point is located, the lower edge plate and the blade body molded surfaces at two sides of the channel, and the area enclosed by the intersection line and the width line section k is the same as WWk+1Hk+1The ratio of (a) to (b).
The turbine guide blade and the guide device throat area calculation method provided by the application are used for the turbine guide blade and the half window F1、FnWhen calculating, WjShould subtract Wj *And/2, (j is 1 to k +1), and the unknown width characteristic line is replaced by a theoretical line, and when the theoretical line is assembled to simulate the guide, the lines of the positions corresponding to the adjacent blades on the two sides of the theoretical blade are assembled.
For turbine guide vanes, especially high-pressure turbine guide vanes, hundreds of air film holes are often distributed on the edge plate and the blade body, and the tail edge of the blade body is also often provided with a tail cleft. Due to the machining deviation of the actual blades, the throat areas of all the blades are difficult to be measured at the same measuring height and keep away from concave shapes such as air film holes, tail cleft seams and the like. The concave shape affects the distribution of the surface molded lines, so that the measurement and calculation of the throat area have large errors. In one embodiment of the present application, in step S201, when determining the width profile of the turbine guide vane, the intermediate height of two adjacent film holes is selected as the height of the theoretical width profile. In step S302, concave position sample line coordinate points such as a gas film hole and a tail cleft are deleted by:
s3021, calculating slopes of two adjacent points in the sample molded line, wherein the slope k of the width sample molded line is dy/dx, and the slope k of the edge plate sample molded line is dz/dx;
and S3022, if the slope value suddenly increases, the slope value suddenly decreases after a preset distance (the distance is related to the size of the concave shape), or the slope value suddenly decreases, and the slope value suddenly increases after the preset distance, the curve is considered to pass through the air film hole, and the related data point is deleted.
According to the method, the influence of concave structures such as air film holes and tail cleft seams on throat area measurement is avoided by improving the blade sample profile selection method and the data point processing method, and the precision is obviously improved.
In an embodiment of the present application, in step S303, due to the limitation of the blade space shape, when the profile of the flange plate sample is measured, the actually measured profile is often too short, so that the calculation of the throat area has a large error.
Advantageously, in this embodiment, the rim plate sample profile may be extended by:
s3031, taking one point at one end of the edge plate sample molded line every 2-3 data points, and taking six points in total;
s3032, calculating the slope of each two adjacent points in the six points;
s3033, calculating the average value of the five slopes;
s3034, extending the molded line of the edge plate sample by a required length according to a straight line by using the average value of the slope and the point coordinate of the extreme end part of the molded line of the edge plate sample;
and S3035, repeating the steps S3031-S3034 at the other end of the edge plate sample molded line, and extending the edge plate sample molded line by a required length.
In step S304, the outline coordinates of the blade with a compact position (i.e., without the air film hole, the tail slit, etc.) are restored and deleted by three-dimensional spline interpolation calculation, and the sample type line coordinate points are further encrypted.
The method and the device solve the problem that due to the limitation of geometric space, the actually measured molded line of the flange plate sample is too short, so that the calculation error of the throat area is large.
According to the turbine guide blade and the guide device throat area calculation method, the problem that cross sections parallel to the axis of an engine under different Z values are cut to form the width molded lines is solved, the width cross sections are not distributed in the radial direction of a measuring channel, so that large errors are caused, the influence of circular arc surfaces of the edge plates and fillets between the edge plates and the blades on the throat area is taken into account, and the calculation accuracy of the throat areas of the turbine guide blade and the guide device is improved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A method for calculating the area of a turbine guide blade and a guide device throat is characterized by comprising the following steps:
establishing a cylindrical coordinate system, wherein M (r, a and h) represents any point coordinate on a turbine guide blade or a guider, and the point M is represented as M (h, rcosa and rsina) in a rectangular coordinate system, wherein the h axis and the X axis are the axial direction of an engine, the Z axis represents the radial direction of the blade, r is the distance between an origin O and the projection M' of the point M on a plane YOZ, r belongs to [0, ∞ ], a is the angle rotated from the Y axis to OM in the counterclockwise direction from the view of a negative X axis, and a belongs to [0, 2 pi);
step two, determining a theoretical width sample profile and an edge plate sample profile, comprising:
s201, representing a window width molded line by using an intersection line of a cylindrical section and an outer molded surface of a blade under different r values, and determining the number k of groups of the width molded lines and the distribution thereof according to the radial blade profile distribution of the blade;
s202, measuring the minimum distance between two adjacent blade width molded lines under the same r value of a window, creating a width line segment where the minimum distance is located and corresponding width characteristic points, numbering the width line segments from the blade tip to the blade root as line segments 1 to k respectively, and setting the corresponding length as W1To Wk(ii) a The connecting line of the end points of the two ends of the line segments 1 and 2 is intersected with the flow passage surface of the upper edge plate,respectively marked as an S1 point and an S2 point, wherein the connecting line of the S1 and the S2 is called a line segment 0, and the length of the line segment is W0; the intersection points of the connecting lines of the end points of the two ends of the line segments k-1 and k and the flow passage surface of the lower edge plate are respectively marked as points G1 and G2, the connecting lines of the points G1 and G2 are called line segments k +1, and the length of the line segments k +1 is Wk+1(ii) a The intersection point of the connecting line of the midpoints of the line segments 1 and 2 and the flow channel surface of the upper edge plate is marked as an S point; the intersection point of the connecting line of the midpoints of the line segments k-1 and k and the flow channel surface of the lower edge plate is marked as a point G; the distances between the middle points of the adjacent width line segments are respectively H2～Hk(ii) a The distance between the point S and the midpoint of the line segment 1 is H1The distance between the point G and the midpoint of the line segment k is Hk+1Is prepared from H1～Hk+1Referred to as window segment height;
s203, selecting a molded line with a proper length on the theoretical blade as a width sample molded line and an edge plate sample molded line, and enabling a theoretical width characteristic point to be located in the middle of the sample molded line, wherein the edge plate sample molded line comprises H coordinate values of a point S1, a point S2, a point G1 and a point G2;
step three, calculating the areas of the guide vanes of the turbine and the throat of the guider, and comprising the following steps of:
s301, scanning the width sample molded line and the edge plate sample molded line of each window of an actual turbine guide vane or guider coordinate system through three coordinates;
s302, deleting molded line coordinate points of the sample at the inward concave positions such as the air film hole, the tail cleft and the like;
s303, extending the edge plate sample molded line;
s304, interpolating a width sample profile and an edge plate sample profile;
s305, converting the molded line coordinate point of the edge plate sample into a cylindrical coordinate system and rotating around an h axis to form an edge plate runner surface;
s306, calculating the throat areas of the actual window, the turbine guide vane and the guider according to the following formulas:
therein, WWj＝(Wj-1+Wj)/2,(j＝1～k+1)，FiThroat area of a single window in the guide vane, FgIs the throat area of a group of guide vanes, F is the throat area of the guider, i is the window and channel serial number, j is the width line segment number, Wj *The length of a theoretical width line segment is defined, n means that each group of blades consists of n blades, and m guide devices consist of m blades;
c1on a theoretical model, a width line segment 1 is intersected with a plane where an S point is positioned, an upper edge plate and blade body molded surfaces on two sides of a channel, and the area enclosed by the intersection line and the width line segment 1 is identical to WW1H1The ratio of (A) to (B);
ck+1on the theoretical model, the width line section k intersects with the plane where the G point is located, the lower edge plate and the blade body molded surfaces at two sides of the channel, and the area enclosed by the intersection line and the width line section k is the same as WWk+1Hk+1The ratio of (a) to (b).
2. The method according to claim 1, wherein in step S201, when determining the width profile of the turbine guide vane, the height between two adjacent film holes is selected as the height of the theoretical width profile.
3. The method for calculating the throat area of the turbine guide vane and the guide vane as claimed in claim 2, wherein in step S302, the line coordinate points of the concave position samples such as the film hole and the tail cleft are deleted by:
and S3021, calculating the slope of two adjacent points in the sample profile, wherein the slope k of the width sample profile is dy/dx, and the slope k of the edge plate sample profile is dz/dx.
And S3022, if the slope value suddenly increases, suddenly decreases after a preset distance, or suddenly decreases and suddenly increases after the preset distance, the curve is considered to pass through the air film hole, and relevant data points at the position are deleted.
4. The method of claim 3, wherein in step S303, the platform sample profile is extended by:
s3031, taking one point at one end of the edge plate sample molded line every 2-3 data points, and taking six points in total;
s3032, calculating the slope of each two adjacent points in the six points;
s3033, calculating the average value of the five slopes;
s3034, extending the molded line of the edge plate sample by a required length according to a straight line by using the average value of the slope and the point coordinate of the extreme end part of the molded line of the edge plate sample;
and S3035, repeating the steps S3031-S3034 at the other end of the edge plate sample molded line, and extending the edge plate sample molded line by a required length.
5. The method of claim 4, wherein in step S304, the compact blade profile coordinates at the deleted position are restored by three-dimensional spline interpolation, and further the width sample profile and platform sample profile coordinate points are encrypted.
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| CN113639700A (en) * | 2021-08-23 | 2021-11-12 | 中国航发贵阳发动机设计研究所 | Turbine guide device throat area three-coordinate measuring method |
| CN114719801A (en) * | 2022-03-30 | 2022-07-08 | 中国航发沈阳发动机研究所 | Turbine guide blade welding positioning method |
| CN114910030A (en) * | 2022-05-17 | 2022-08-16 | 安徽应流航源动力科技有限公司 | Method for measuring throat distance of multi-connected blade |
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| CN113607119A (en) * | 2021-07-26 | 2021-11-05 | 中国船舶重工集团公司第七0三研究所 | Method for measuring throat area of marine gas turbine blade based on characteristic dimension |
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| CN113639700B (en) * | 2021-08-23 | 2023-10-27 | 中国航发贵阳发动机设计研究所 | Three-coordinate measuring method for throat area of turbine guide |
| CN114719801A (en) * | 2022-03-30 | 2022-07-08 | 中国航发沈阳发动机研究所 | Turbine guide blade welding positioning method |
| CN114719801B (en) * | 2022-03-30 | 2024-03-19 | 中国航发沈阳发动机研究所 | Turbine guide vane welding positioning method |
| CN114910030A (en) * | 2022-05-17 | 2022-08-16 | 安徽应流航源动力科技有限公司 | Method for measuring throat distance of multi-connected blade |
| CN115292854A (en) * | 2022-10-09 | 2022-11-04 | 中国航发四川燃气涡轮研究院 | Blade throat solving method based on flow tube segmentation and quadratic curve |
| CN115292854B (en) * | 2022-10-09 | 2023-02-17 | 中国航发四川燃气涡轮研究院 | Blade throat solving method based on flow tube segmentation and quadratic curve |
| CN116341132B (en) * | 2023-02-24 | 2024-01-30 | 中国科学院西安光学精密机械研究所 | Air film hole position and axial correction method based on blade deformation displacement field |
| CN116341132A (en) * | 2023-02-24 | 2023-06-27 | 中国科学院西安光学精密机械研究所 | Air film hole position and axial correction method based on blade deformation displacement field |
| CN116164695A (en) * | 2023-04-23 | 2023-05-26 | 中国航发沈阳发动机研究所 | Turbine guide and exhaust area measurement method thereof |
| CN117272550A (en) * | 2023-11-17 | 2023-12-22 | 陕西空天信息技术有限公司 | Method, device and equipment for designing flow channel and computer storage medium |
| CN117272550B (en) * | 2023-11-17 | 2024-03-22 | 陕西空天信息技术有限公司 | Method, device and equipment for designing flow channel and computer storage medium |
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