CN115788598A - Turbine blade air film hole parametric control and design method - Google Patents
Turbine blade air film hole parametric control and design method Download PDFInfo
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- CN115788598A CN115788598A CN202310092469.1A CN202310092469A CN115788598A CN 115788598 A CN115788598 A CN 115788598A CN 202310092469 A CN202310092469 A CN 202310092469A CN 115788598 A CN115788598 A CN 115788598A
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Abstract
The invention provides a turbine blade air film hole parameterization control and design method, which comprises the following steps: s1, obtaining a reference section modeling curve of a turbine blade body and generating an appearance curved surface of the turbine blade body; s2, designing control parameters of each exhaust film hole according to the cooling design requirements of the film hole; s3, generating specific parameters of all the air film holes in the outer molded surface by using the control parameters; and S4, completing gas film hole modeling by using the generated gas film hole parameters. According to the design requirement, the method can adopt specific chord direction and radial direction control parameters and the in-row distribution rule control function to realize the control and efficient design of the air-cooled turbine blade air film hole full parameters and generate related monitoring data for links such as simulation analysis, structural modeling, manufacturing and processing and the like, so that the manufacturing and design conformity is ensured to the maximum extent, and the cooling design efficiency of the turbine blade air film hole and the design target conformity are improved.
Description
Technical Field
The invention relates to the technical field of design of turbine blades of aero-engines, in particular to a parameterization control and design method of an air film hole of a turbine blade.
Background
With the extreme performance pursuit of modern gas turbine engines, the turbine inlet gas temperature is far higher than the melting temperature of turbine components, particularly turbine blades, and besides relying on the improvement of the performance of blade materials, advanced cooling design is an important technical means for ensuring the safe operation of the turbine blades.
The film hole cooling is taken as an efficient cooling measure, the gas temperature of the outer wall surface of the blade can be reduced by the aid of outflow cold air of the film hole, direct erosion of gas to turbine blades is avoided, the blade is protected importantly, and the film hole cooling device is widely used on modern high-performance turbine blades.
The design of the advanced film hole cooling turbine blade needs professional high cooperation of pneumatics, cooling, structure, strength, process and the like, and can be finished through continuous and repeated design optimization iteration. In the air film hole cooling design in engineering, a cooling designer generally gives a rough air film scheme, a structural designer completes modeling with the air film hole, and after modeling of the blade is completed, the air film hole cooling design returns and transmits to the cooling designer and the strength designer to conduct heat transfer and strength evaluation. The series of repeated iteration links have the problems of low efficiency of designing the cooling parameters of the gas film holes, missing key control parameters of the gas film holes, poor consistency of parameter transmission, conversion and use among different specialties, difficulty in ensuring the conformity of the cooling manufacture and design of the gas film holes and the like.
In order to ensure the conformity between the manufacturing and the design to the maximum extent and improve the cooling design efficiency of the film hole of the turbine blade and the conformity between the design target, a film hole parameter control and design method needs to be provided.
Disclosure of Invention
In view of this, the embodiment of the present application provides a turbine blade air film hole parameterization control and design method, which may adopt specific chord direction and radial direction control parameters and an in-row distribution rule control function according to design requirements to implement control and efficient design of all parameters of an air film hole of an air-cooled turbine blade, including providing parameters such as coordinates, angles, apertures, distribution rules and the like of all air film holes, and generating related monitoring data for links such as simulation analysis, structural modeling, manufacturing and processing, so as to ensure the conformity between manufacturing and design to the maximum extent, and improve the cooling design efficiency of the turbine blade air film hole and the conformity with design targets.
The embodiment of the application provides the following technical scheme: a turbine blade film hole parameterization control and design method comprises the following steps:
s1, obtaining a reference section modeling curve of a turbine blade body and generating an appearance curved surface of the turbine blade body;
s2, designing control parameters of each exhaust film hole according to the cooling design requirements of the film hole;
s3, generating specific parameters of all the air film holes on the outer molded surface by using the control parameters;
and S4, completing gas film hole modeling by using the generated gas film hole parameters.
According to an embodiment of the application, in step S1, a blade body reference section modeling curve is interpolated to generate a blade body exterior curved surface mesh for subsequently generating coordinates of a hole center of an air film hole.
According to an embodiment of the present application, in step S2, the exhaust membrane pore control parameters include: the relative position of each exhaust film hole on each reference section modeling curve, the starting height and the ending height of each exhaust film hole on the blade body, the hole number and the hole diameter of each exhaust film hole, and the angle and the hole interval distribution rule of the exhaust film holes.
According to an embodiment of the present application, in step S2, the relative position on each reference cross-sectional modeling curve is used to control a trend curve of each exhaust membrane hole along the height direction of the blade body; the distribution rule of the angles and the hole intervals of the gas film holes is that the distribution rule of the angles and the intervals of the gas film holes is controlled by adopting a Bessel curve according to the cooling design requirement of the gas film holes.
According to an embodiment of the present application, in step S3, the process of generating specific parameters of all the film holes on the outer mold surface by using the control parameters includes:
step S31, generating a more refined trend node curve of each exhaust film hole along the trend curve on the blade body exterior curved surface grid node according to the relative position of each exhaust film hole on each reference section modeling curve;
step S32, generating hole center coordinates of each row of each air film hole on the blade body exterior curved surface grid along the trend node curve in the step S31 by using a hole pitch distribution rule controlled by a Bezier curve, and determining the specific distribution of the air film hole centers on the blade body exterior;
s33, according to the angle control parameter of each row of air film holes, calculating a bias point of the air film hole center coordinate on the outer profile surface of the blade along the hole vector direction by using the air film hole center coordinate, and generating an air film hole cylinder data file for drawing and modeling by using the air film hole diameter, wherein the air film hole cylinder data file is used for structural modeling and inspection of air film hole design results;
and S34, calculating other parameters according to the air film hole parameters generated in the step S33, wherein the other parameters comprise the minimum included angle between each air film hole vector and the outer profile and the distance between adjacent air film holes.
According to an embodiment of the present application, in step S31, the generated trend node curve is smoothed by using a bezier curve.
According to an embodiment of the present application, in step S32, a specific method for controlling the distance between the gas film holes by using the bezier curve includes: according to the cooling design requirement of the film holes, determining the order and the curve form of the Bezier curve, according to the number n of the film holes in each row, uniformly distributing and extracting n-1 Bezier values on the curve along the abscissa, summing the n-1 Bezier values, solving the relative quantity of each Bezier value in the sum, taking the relative quantity as the relative distance distribution of the film holes on the trend node curve obtained in the step S31, and interpolating and generating the absolute coordinates of the hole centers of the film holes on the blade body shape according to the relative distance distribution.
According to an embodiment of the application, in step S4, according to the generated parameters of the film holes with the specific format, the UG software cylinder modeling tool is used for secondary development, so as to complete the rapid modeling of all the film holes on the blade model.
The invention discloses a turbine blade air film hole parameterization control and design method, which comprises the following steps: according to design requirements, specific chord direction and radial direction control parameters and an in-row distribution rule control function are adopted to realize control and efficient design of the air film holes of the air-cooled turbine blade, parameters such as coordinates, angles, apertures and distribution rules of all the air film holes are given, relevant monitoring data are generated and used in links such as simulation analysis, structural modeling and manufacturing and processing, the conformity of manufacturing and design is guaranteed to the maximum extent, and the cooling design efficiency of the air film holes of the turbine blade and the conformity of design targets are improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 shows the profile of the blade body and the chordwise control distribution of the film holes of an embodiment of the invention;
FIG. 2 is a diagram illustrating an outline surface mesh generated based on a blade body modeling section according to an embodiment of the present invention;
FIG. 3 is an initial baseline routing design for the air film holes on the leaf area grid in an embodiment of the present invention;
FIG. 4 is a Bezier distribution control curve of the inter-row gas film hole spacing in an embodiment of the present invention;
FIG. 5 is a diagram illustrating the coordinates of the centers of the pores of the film pores generated on the blade body outer profile mesh according to the pore spacing distribution control curve in an embodiment of the present invention;
FIG. 6 is a diagram illustrating a distribution of film hole cylinder vectors generated from film hole center coordinates and hole angles and hole diameters on an outer profile of a blade in an embodiment of the present invention;
FIG. 7 is a diagram illustrating the effect of three-dimensional distribution of film hole cylinders on the outer profile of the blade body according to an embodiment of the present invention;
FIG. 8 is a diagram illustrating a statistical distribution of the inter-hole distances of the film holes based on the full parameters of the film holes according to an embodiment of the present invention;
FIG. 9 is a flow chart of a specific design of the method of the present invention;
wherein, 1-leaf basin curve; 2-leaf back curve; 3-leading edge; 4-trailing edge; 5-initial trend curve; 51-end height; 52-starting height; 6-trend node curve; 7-gas film hole cylinder vector distribution.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail with reference to the accompanying drawings, wherein the embodiments are described in detail, and it is to be understood that the embodiments are only a part of the embodiments of the present invention, and not all of the embodiments are described. All other embodiments, which can be obtained by a person skilled in the art without inventive step based on the embodiments of the present invention, are within the scope of protection of the present invention.
The parametric control and design method for the turbine blade film hole according to the embodiment of the present invention is further described in detail with reference to fig. 1 to 9, and the specific implementation steps are as follows:
s1, obtaining a reference section modeling curve of a turbine blade body and generating an appearance curved surface of the turbine blade body;
according to the bending characteristic of the turbine blade, a proper number of blade body shape datum section curves are selected for generating a blade body shape curved surface, the blade body datum section curves are usually from a pneumatically designed modeling curve, the number of the datum sections is more than 2, and 3 to 10 sections which are uniformly distributed along the blade body are suitable, the datum section curves are divided into a basin curve 1 and a blade back curve 2, the relative positions of a section basin curve 1 node and a blade back curve 2 node are defined from a front edge 3 to a tail edge 4, the relative position of the front edge 3 is 0.0, the relative position of the tail edge 4 is 1.0, and an interpolation method is used for generating a blade body shape curved surface grid from the shape datum section curves for subsequently generating specific coordinates of an air film hole center.
Specifically, the blade body reference section curves adopted in the embodiment are from pneumatically designed modeling curves, the number of the reference sections is 7, each reference section curve is divided into a cone curve 1 and a back curve 2, the relative positions of the cone curve 1 node and the back curve 2 node of the section are defined from the leading edge 3 to the trailing edge 4, the relative position of the leading edge 3 is 0.0, and the relative position of the trailing edge 4 is 1.0, and the embodiment interpolates the shape reference section curves by using a lagrangian method to generate blade body shape curved surface grids for subsequently generating specific coordinates of the pore center of the air film pore.
S2, designing control parameters of each exhaust film hole according to the cooling design requirements of the film hole;
the control parameters of the air film hole adopted by the embodiment comprise: the relative position of each exhaust film hole on each reference section curve, the starting height 52 and the ending height 51 of each exhaust film hole on the blade body, as shown in fig. 1 and 3, the hole number and the hole diameter of each exhaust film hole, and the angle and the hole interval distribution rule of the exhaust film holes. And the relative position on each reference section curve is used for controlling an initial trend curve 5 of each exhaust membrane hole along the height direction of the blade body. The distribution rule of the angles and the hole intervals is that according to the cooling design requirements of the film holes, the distribution rule of the angles and the intervals of all the holes is controlled by adopting a multi-point Bessel curve, wherein the interval distribution rule of a row of film holes is shown in figure 4.
S3, generating specific parameters of all the air film holes on the outer molded surface by using the control parameters;
the control parameters are utilized to generate specific parameters of all the air film holes on the outer molded surface, and the specific steps are as follows:
step S31, according to the relative position of each exhaust film hole on each reference cross-sectional curve, as shown in fig. 1, a more precise trend node curve 6 of each exhaust film hole along the initial trend curve 5 is generated on the leaf body exterior curved surface mesh node, in this embodiment, the trend node curve 6 is smoothed by using a bezier curve, and the effect after the smoothing is shown in fig. 3.
Step S32, using the hole pitch distribution rule controlled by the bezier curve shown in fig. 4, along the finer trend node curve 6 described in step S31, generating the hole center coordinates of each row of each gas film hole on the blade body outline curved surface mesh, and determining the specific distribution of the gas film hole centers on the blade body outline, as shown in fig. 5.
In step S32, the specific method for controlling the distance between the air film holes by using the bezier curve includes: as shown in fig. 4, according to the film hole cooling design requirement, the order and the curve form of the bezier curve are determined, n-1 bezier values are uniformly distributed and extracted on the curve along the abscissa according to the number n of each row of film holes, the n-1 bezier values are summed to obtain the relative quantity of each bezier value in the sum, the relative quantity is used as the relative distance distribution of the film holes on the trend node curve 6 obtained in step S31, and the absolute coordinates of the center of the film hole on the blade body shape are generated by interpolation according to the relative distance distribution, as shown in fig. 5.
Step S33, according to the angle control parameters of each row of air film holes, calculating a bias point of the hole center coordinate of the outer molded surface along the hole vector direction by using the air film hole center coordinate on the outer molded surface of the blade, generating an air film hole cylinder data file which can be used for tecplot and UG modeling by using the air film hole diameter, and further generating an air film hole cylinder vector distribution 7 for structural modeling and inspection of air film hole design results, as shown in FIGS. 5, 6 and 7.
Step S34, calculating parameters such as a minimum included angle between each gas film hole vector and the outer profile and a distance between adjacent gas film holes according to the gas film hole parameters generated in step S33, and using the parameters for subsequent related design including structure modeling, heat transfer analysis, strength evaluation, related key parameter monitoring, and the like, so as to improve design quality, wherein the distance distribution of each longitudinal gas discharge film hole from left to right in fig. 7 is shown in fig. 8.
And S4, completing gas film hole modeling by using the generated gas film hole parameters.
According to the gas film hole parameters in the specific format generated in step S34, the gas film hole parameters generated in this embodiment are text files, and include coordinates of the center of the ground circle of the cylinder, coordinates of the center of the top circle of the cylinder, and a diameter of the cylinder, which is the diameter of the gas film hole, for describing the cylinder of the gas film hole. And carrying out secondary development by using a UG software cylinder modeling tool, and quickly modeling all the air film holes on the blade model after circulation.
After the steps are completed, all design parameters of the turbine blade air film hole can be obtained, the parameters can be used for structural modeling, heat transfer analysis, strength analysis, process hole making and the like, the consistency of the air film hole parameter use in each link is guaranteed to the maximum extent, the consistency of manufacturing and design is guaranteed, and the cooling design efficiency of the turbine blade air film hole and the consistency of design targets are improved.
According to the above description, the invention provides a turbine blade air film hole parameterization control and design method, and the feasibility of the invention can be seen from fig. 1-9.
Therefore, the invention has the following advantages: according to design requirements, specific chord direction and radial direction control parameters and an in-row distribution rule control function are adopted to realize control and efficient design of the air-cooled turbine blade air film hole full parameters, parameters such as coordinates, angles, apertures, distribution rules and the like of all air film holes are given, and relevant monitoring data are generated to be used in links such as simulation analysis, structural modeling, manufacturing and processing, so that the manufacturing and design conformance is ensured to the maximum extent, and the turbine blade air film hole cooling design efficiency and the design target conformance are improved.
The turbine blade of a certain type designed by the method of the invention is tested and examined, has good performance and provides a key technical support for the cooling design of the turbine blade with high efficiency and reliability.
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 (8)
1. A turbine blade film hole parameterization control and design method is characterized by comprising the following steps:
s1, obtaining a reference section modeling curve of a turbine blade body and generating an appearance curved surface of the turbine blade body;
s2, designing control parameters of each exhaust film hole according to the cooling design requirements of the film hole;
s3, generating specific parameters of all the air film holes on the outer molded surface by using the control parameters;
and S4, completing gas film hole modeling by using the generated gas film hole parameters.
2. The parametric control and design method for the turbine blade air film hole as claimed in claim 1, wherein in step S1, the blade body profile surface mesh is generated by interpolating the blade body reference section modeling curve for subsequent generation of the coordinates of the air film hole center.
3. The parametric control and design method for turbine blade film holes as claimed in claim 1, wherein in step S2, each of the exhaust film hole control parameters comprises: the relative position of each exhaust film hole on each reference section modeling curve, the starting height and the ending height of each exhaust film hole on the blade body, the hole number and the hole diameter of each exhaust film hole, and the angle and the hole interval distribution rule of the exhaust film holes.
4. The parametric control and design method for turbine blade air film holes as claimed in claim 3, wherein in step S2, the relative position on each reference section modeling curve is used for controlling the trend curve of each exhaust film hole along the blade height direction; the distribution rule of the angles and the hole intervals of the gas film holes is that the distribution rule of the angles and the intervals of the gas film holes is controlled by adopting a Bessel curve according to the cooling design requirement of the gas film holes.
5. The parametric control and design method for turbine blade film holes as claimed in claim 4, wherein the step S3 of generating specific parameters of all film holes on the outer surface by using the control parameters comprises:
step S31, generating a more refined trend node curve of each exhaust film hole along the trend curve on the blade body exterior curved surface grid node according to the relative position of each exhaust film hole on each reference section modeling curve;
step S32, generating hole center coordinates of each row of each air film hole on the blade body exterior curved surface grid along the trend node curve in the step S31 by using a hole pitch distribution rule controlled by a Bezier curve, and determining the specific distribution of the air film hole centers on the blade body exterior;
s33, according to the angle control parameter of each row of air film holes, calculating a bias point of the air film hole center coordinate on the outer profile surface of the blade along the hole vector direction by using the air film hole center coordinate, and generating an air film hole cylinder data file for drawing and modeling by using the air film hole diameter, wherein the air film hole cylinder data file is used for structural modeling and inspection of air film hole design results;
and S34, calculating other parameters according to the air film hole parameters generated in the step S33, wherein the other parameters comprise the minimum included angle between each air film hole vector and the outer profile and the distance between adjacent air film holes.
6. The parametric control and design method for turbine blade film holes as in claim 5, wherein in step S31, the generated trend node curve is smoothed by a Bezier curve.
7. The parametric control and design method for turbine blade film holes as claimed in claim 5, wherein the specific method for controlling the film hole pitch by using the Bezier curve in step S32 comprises: according to the cooling design requirement of the film holes, determining the order and the curve form of the Bezier curve, according to the number n of the film holes in each row, uniformly distributing and extracting n-1 Bezier values on the curve along the abscissa, summing the n-1 Bezier values, solving the relative quantity of each Bezier value in the sum, taking the relative quantity as the relative distance distribution of the film holes on the trend node curve obtained in the step S31, and interpolating and generating the absolute coordinates of the hole centers of the film holes on the blade body shape according to the relative distance distribution.
8. The parametric control and design method for the turbine blade air film holes as claimed in claim 5, wherein in step S4, according to the generated air film hole parameters with specific formats, the UG software cylinder modeling tool is used for secondary development, and the rapid modeling of all the air film holes on the blade model is completed.
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| CN116738621A (en) * | 2023-08-09 | 2023-09-12 | 武汉华锋惠众科技有限公司 | Method, system, electronic equipment and storage medium for constructing derivative curved surface |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116186943A (en) * | 2023-04-23 | 2023-05-30 | 中国航发四川燃气涡轮研究院 | Turbine blade frequency modulation method based on root extension structural parameter adjustment |
| CN116186943B (en) * | 2023-04-23 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Turbine blade frequency modulation method based on root extension structural parameter adjustment |
| CN116738621A (en) * | 2023-08-09 | 2023-09-12 | 武汉华锋惠众科技有限公司 | Method, system, electronic equipment and storage medium for constructing derivative curved surface |
| CN116738621B (en) * | 2023-08-09 | 2023-11-17 | 武汉华锋惠众科技有限公司 | Method, system, electronic equipment and storage medium for constructing derivative curved surface |
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| Publication number | Publication date |
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| CN115788598B (en) | 2023-06-30 |
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