CN115788598B - Turbine blade air film hole parameterization control and design method - Google Patents
Turbine blade air film hole parameterization control and design method Download PDFInfo
- Publication number
- CN115788598B CN115788598B CN202310092469.1A CN202310092469A CN115788598B CN 115788598 B CN115788598 B CN 115788598B CN 202310092469 A CN202310092469 A CN 202310092469A CN 115788598 B CN115788598 B CN 115788598B
- Authority
- CN
- China
- Prior art keywords
- air film
- hole
- parameters
- film hole
- curve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a turbine blade air film hole parameterization control and design method, which comprises the following steps: s1, obtaining a turbine blade body reference section modeling curve and generating a blade body profile curved surface; s2, designing control parameters of each exhaust film hole according to the cooling design requirement of the film hole; s3, generating specific parameters of all air film holes on the outer surface by using the control parameters; and S4, modeling the air film hole by using the generated air film hole parameters. According to the invention, specific chord direction and radial control parameters and an in-row distribution rule control function can be adopted according to design requirements, so that the control and efficient design of the whole parameters of the air-cooled turbine blade air film hole are realized, related monitoring data are generated for links such as simulation analysis, structural modeling and manufacturing processing, the manufacturing and design compliance is ensured to the greatest extent, and the cooling design efficiency of the turbine blade air film hole and the design target compliance are improved.
Description
Technical Field
The invention relates to the technical field of design of turbine blades of aeroengines, in particular to a parameterized control and design method for air film holes of turbine blades.
Background
With the tremendous pursuit of performance by modern gas turbine engines, turbine inlet gas temperatures have been far above the melting temperature of turbine components, particularly turbine blades, and advanced cooling designs are important technological means for ensuring safe operation of turbine blades, in addition to relying on the promotion of blade material performance.
As an efficient cooling measure, the cooling air flowing out of the air film holes can reduce the temperature of the gas on the outer wall surface of the blade, avoid direct erosion of the gas on the turbine blade, play an important role in protecting the blade, and have wide application in modern high-performance turbine blades.
The design of the advanced air film hole cooling turbine blade needs to be highly cooperated with the professions such as air-driven, cooling, structure, strength and process, and can be completed through repeated design optimization iteration. The cooling design of the air film hole in engineering is generally that a cooling designer gives a rough air film scheme, then a structural designer completes modeling of the air film hole, after the modeling of the blade is completed, the air film hole is returned and transmitted to the cooling designer and an intensity designer for heat transfer and intensity assessment. The repeated iteration links have the problems that the design efficiency of the cooling parameters of the air film holes is low, key control parameters of the air film holes are lost, the consistency of parameter transmission, conversion and use among different professions is poor, the consistency of the cooling manufacture and the design of the air film holes is difficult to ensure, and the like.
In order to ensure the consistency of manufacturing and design to the greatest extent and improve the cooling design efficiency of the turbine blade air film hole and the consistency of design targets, an air film hole parameter control and design method is required to be provided.
Disclosure of Invention
In view of this, the embodiment of the application provides a turbine blade air film hole parameterization control and design method, can adopt specific chord direction, radial control parameters and row distribution rule control functions according to the design requirement, realize the control and the high-efficient design of the air-cooled turbine blade air film hole full parameters, including giving the coordinate, angle, aperture, distribution rule etc. parameters of all air film holes, and generate relevant monitoring data, be used for links such as simulation analysis, structural modeling and manufacturing processing, furthest guarantee the manufacturing and the compliance of design, promote turbine blade air film hole cooling design efficiency and the compliance of design target.
The embodiment of the application provides the following technical scheme: a turbine blade air film hole parameterization control and design method comprises the following steps:
s1, obtaining a turbine blade body reference section modeling curve and generating a blade body profile curved surface;
s2, designing control parameters of each exhaust film hole according to the cooling design requirement of the film hole;
s3, generating specific parameters of all air film holes on the outer surface by using the control parameters;
and S4, modeling the air film hole by using the generated air film hole parameters.
According to one embodiment of the present application, in step S1, a blade body profile curved surface grid is generated by interpolating a blade body reference section modeling curve, and is used for generating hole center coordinates of a gas film hole subsequently.
According to an embodiment of the present application, in step S2, the exhaust film hole control parameters include: the relative positions of the exhaust film holes on the modeling curves of the reference sections, the starting height and the ending height of the exhaust film holes on the blade body, the hole number and the hole diameter of the exhaust film holes, and the angle and the hole spacing distribution rule of the air film holes.
According to an embodiment of the present application, in step S2, the relative positions on the reference section modeling curves are used to control the trend curve of each exhaust film hole along the height direction of the blade body; the angle and hole spacing distribution rule of the air film holes is that the Bezier curve is adopted to control the angle and the distance distribution rule of each air film hole according to the cooling design requirement of the air film holes.
According to one embodiment of the present application, in step S3, the process of generating the specific parameters of all the air film holes on the outer surface by using the control parameters includes:
s31, generating a finer trend node curve of each exhaust film hole along the trend curve on the blade body profile curved surface grid node according to the relative positions 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 profile curved surface grid along the trend node curve in the step S31 by utilizing a hole pitch distribution rule controlled by Bezier curves, and determining the specific distribution of the air film hole centers on the blade body profile;
s33, calculating offset points of the outer surface hole center coordinates along the hole vector direction by using the hole center coordinates of the air film holes on the outer surface of the blade according to the angle control parameters of each row of air film holes, and generating air film hole cylinder data files for drawing and modeling by using the air film hole diameters for structural modeling and checking of air film hole design results;
and step 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 Kong Shiliang and the outer surface and the distance between adjacent air film holes.
According to one 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 air film hole pitch by using the bezier curve includes: determining the order and curve shape of the Bezier curve according to the cooling design requirement of the air film holes, uniformly distributing and extracting n-1 Bezier values along the horizontal coordinate on the curve according to the number n of each row of air film holes, 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 air film holes on the trend node curve obtained in the step S31, and generating the absolute coordinates of the air film hole cores on the blade body shape according to the relative distance distribution interpolation.
According to one embodiment of the present application, in step S4, secondary development is performed by using the UG software cylinder modeling tool according to the generated gas film hole parameters in the specific format, so as to complete rapid modeling of all the gas film holes on the blade model.
The invention relates to 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 control parameters and row distribution law control functions are adopted, so that control and efficient design of all parameters of the air film holes of the air-cooled turbine blade are realized, parameters such as coordinates, angles, aperture, distribution laws and the like of all the air film holes are given, relevant monitoring data are generated, the air film holes are used for links such as simulation analysis, structural modeling and manufacturing processing, manufacturing and design compliance is guaranteed to the greatest extent, and the air film hole cooling design efficiency of the turbine blade and design target compliance are improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed 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 that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a blade airfoil profiled cross section and air film hole chord direction control distribution in an embodiment of the invention;
FIG. 2 is an exterior surface mesh generated based on a blade profile section in an embodiment of the present invention;
FIG. 3 is an initial baseline routing design of air film holes on a blade surface grid in an embodiment of the invention;
FIG. 4 is a Bessel distribution control curve of the interval between gas film holes in a row in an embodiment of the invention;
FIG. 5 is a graph showing hole center coordinates of air film holes generated on a blade body outer surface grid according to a hole pitch distribution control curve in an embodiment of the invention;
FIG. 6 is a cylinder vector distribution of air film holes generated according to the coordinates of the hole centers of the air film holes on the outer profile of the blade body and the hole angles and the hole diameters in the embodiment of the invention;
FIG. 7 is a three-dimensional distribution effect diagram of cylinder bodies of air film holes on the outer profile of a blade body in the embodiment of the invention;
FIG. 8 is a graph showing a distribution of hole spacing of air film holes based on statistics of all parameters of the air film holes in an embodiment of the invention;
FIG. 9 is a flow chart of a specific design of the method of the present invention;
wherein, 1-leaf basin curve; 2-dorsum curve; 3-leading edge; 4-trailing edge; 5-initial trend curve; 51-termination height; 52-initial height; 6-going node curves; 7-cylinder vector distribution of the air film holes.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The technical solution of the present invention will be clearly and completely described below in detail with reference to the accompanying drawings in combination with the embodiments, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The following is a further detailed description of a method for controlling and designing parameters of gas film holes of turbine blades according to an embodiment of the present invention with reference to fig. 1 to 9, and the specific implementation steps are as follows:
s1, obtaining a turbine blade body reference section modeling curve and generating a blade body profile curved surface;
according to the bending and twisting characteristics of the turbine blade, a proper number of blade body appearance reference section curves are selected to be used for generating blade body appearance curved surfaces, the blade body reference section curves are usually from pneumatically designed modeling curves, the number of reference section curves is more than 2, and is usually 3-10 sections uniformly distributed along the blade body, the reference section curves are divided into a blade basin curve 1 and a blade back curve 2, the relative positions of a node of the blade basin curve 1 and a node of the blade back curve 2 of the section 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 the appearance reference section curves are used for generating blade body appearance curved surface grids by an interpolation method and are used for generating air film hole core specific coordinates.
Specifically, the reference section curves of the blade body adopted in the embodiment are modeling curves of pneumatic design, the reference section number is 7, each reference section curve is divided into a blade basin curve 1 and a blade back curve 2, the relative positions of the nodes of the blade basin curve 1 and the nodes of the blade back curve 2 of the sections 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 the embodiment utilizes the Lagrangian method to interpolate the reference section curves of the profile to generate a profile curved surface grid of the blade body for subsequently generating specific coordinates of a hole core of the air film.
S2, designing control parameters of each exhaust film hole according to the cooling design requirement of the film hole;
the air film hole control parameters adopted in the embodiment include: the relative positions of the exhaust film holes on the reference section curves, the starting height 52 and the ending height 51 of the exhaust film holes on the blade body, particularly shown in fig. 1 and 3, the hole number and the hole diameter of the exhaust film holes, and the angle and the hole spacing distribution rule of the air film holes. The relative positions of the reference section curves are used for controlling the initial trend curve 5 of each exhaust film hole along the height direction of the blade. The angle and hole spacing distribution rule is controlled by adopting a multipoint Bezier curve according to the cooling design requirement of the air film holes, wherein the distribution rule of the angle and the distance of each hole is shown in figure 4.
S3, generating specific parameters of all air film holes on the outer surface by using the control parameters;
the specific parameters of all the air film holes on the outer surface are generated by utilizing the control parameters, and the specific steps are as follows:
in step S31, according to the relative positions of the exhaust film holes on the reference section curves, as shown in fig. 1, on the blade profile curved surface grid nodes, a trend node curve 6 is generated, along which the initial trend curve 5 of each exhaust film hole is finer, and in this embodiment, the bezier curve is used to smooth the trend node curve 6, and the effect after the processing is shown in fig. 3.
Step S32, using the hole pitch distribution rule controlled by Bezier curve as shown in FIG. 4, generating the hole center coordinates of each row of each air film hole on the curved surface grid of the blade body shape along the finer trend node curve 6 as shown in step S31, and determining the specific distribution of the hole centers of the air film holes on the blade body shape as shown in FIG. 5.
In the step S32, the specific method for controlling the air film hole pitch by using the bezier curve is as follows: as shown in fig. 4, the order and curve shape of the bessel curve are determined according to the cooling design requirement of the air film holes, n-1 bessel values are uniformly distributed and extracted along the horizontal coordinate on the curve according to the number n of each row of air film holes, n-1 bessel values are summed to obtain the relative quantity of each bessel value in the sum, the relative quantity is used as the relative distance distribution of the air film holes on the trend node curve 6 obtained in the step S31, and the absolute coordinates of the air film hole centers on the blade body shape are generated by interpolation according to the relative distance distribution, as shown in fig. 5.
And S33, calculating offset points of the hole center coordinates of the outer surface along the hole vector direction by using the hole center coordinates of the air film holes on the outer surface of the blade according to the angle control parameters of each row of air film holes, generating air film hole cylinder data files for drawing by using the test software and UG modeling by using the hole diameters of the air film holes, and further generating air film hole cylinder vector distribution 7 for structural modeling and checking of air film hole design results, as shown in fig. 5, 6 and 7.
And step S34, calculating parameters such as the minimum included angle between each air film Kong Shiliang and the outer surface, the distance between adjacent air film holes and the like according to the air film hole parameters generated in the step S33, and using the parameters for subsequent related design including structural modeling, heat transfer analysis, strength evaluation, related key parameter monitoring and the like, so as to improve the design quality, wherein the distance distribution of each longitudinal air exhaust film hole from left to right in FIG. 7 is shown in FIG. 8.
And S4, modeling the air film hole by using the generated air film hole parameters.
According to the specific format of the air film hole parameters generated in the step S34, the air film hole parameters generated in the embodiment are text files, and include the cylinder ground center coordinates, the cylinder top surface center coordinates and the cylinder diameter, namely the air film hole diameter, for describing the air film hole cylinder. And (3) carrying out secondary development by utilizing a UG software cylinder modeling tool, and realizing rapid modeling of all 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, and can be used for structural modeling, heat transfer analysis, strength analysis, process hole making and the like, so that the consistency of the use of the air film hole parameters in each link is ensured to the greatest extent, the consistency of manufacturing and design is ensured, and the cooling design efficiency of the turbine blade air film hole and the consistency of design targets are improved.
According to the description, the feasibility of the invention can be seen from fig. 1-9.
Thus, the present invention has the following advantages: according to the design requirement, the control and the efficient design of the whole parameters of the air-cooled turbine blade air film hole are realized by adopting specific chord direction and radial control parameters and row distribution rule control functions, the parameters such as coordinates, angles, aperture, distribution rules and the like of all the air film holes are given, and relevant monitoring data are generated for links such as simulation analysis, structural modeling, manufacturing and processing and the like, so that the manufacturing and design consistency is ensured to the greatest extent, the cooling design efficiency of the turbine blade air film hole and the design target consistency are improved, and the method has excellent engineering practical value.
The test and examination are carried out on a certain type of turbine blade designed by the method, the performance is good, and a key technical support is provided for the efficient and reliable type turbine blade cooling design.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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. The parameterization control and design method for the gas film holes of the turbine blades is characterized by comprising the following steps of:
s1, obtaining a turbine blade body reference section modeling curve and generating a blade body profile curved surface;
s2, designing control parameters of each exhaust film hole according to the cooling design requirement of the film hole;
s3, generating specific parameters of all air film holes on the outer surface by using the control parameters;
s4, modeling the air film hole by using the generated air film hole parameters;
in step S2, the control parameters of each exhaust film hole include: the relative positions of the exhaust film holes on the modeling curves of the reference sections, the starting height and the ending height of the exhaust film holes on the blade body, the hole number and the hole diameter of the exhaust film holes, and the angle and the hole spacing distribution rule of the air film holes;
in step S2, the relative positions on the reference section modeling curves are used for controlling the trend curves of the exhaust film holes along the height direction of the blade body; the angle and hole spacing distribution rule of the air film holes is that a Bezier curve is adopted to control the angle and the spacing distribution rule of each air film hole according to the cooling design requirement of the air film holes;
in step S3, the process of generating specific parameters of all the air film holes on the outer surface by using the control parameters includes:
s31, generating a finer trend node curve of each exhaust film hole along the trend curve on the blade body profile curved surface grid node according to the relative positions 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 profile curved surface grid along the trend node curve in the step S31 by utilizing a hole pitch distribution rule controlled by Bezier curves, and determining the specific distribution of the air film hole centers on the blade body profile;
s33, calculating offset points of the outer surface hole center coordinates along the hole vector direction by using the hole center coordinates of the air film holes on the outer surface of the blade according to the angle control parameters of each row of air film holes, and generating air film hole cylinder data files for drawing and modeling by using the air film hole diameters for structural modeling and checking of air film hole design results;
and step 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 Kong Shiliang and the outer surface and the distance between adjacent air film holes.
2. The method for parameterized control and design of gas film holes of turbine blades according to claim 1, wherein in step S1, a blade body profile curved surface grid is generated by interpolating a blade body reference section modeling curve for subsequent generation of gas film hole center coordinates.
3. The method for parameterized control and design of gas film holes of turbine blades according to claim 1, wherein in step S31, the generated trend node curve is smoothed by using a bezier curve.
4. The method for parameterizing and designing gas film holes of turbine blades according to claim 1, wherein in step S32, the specific method for controlling the gas film hole pitch by using bezier curves comprises: determining the order and curve shape of the Bezier curve according to the cooling design requirement of the air film holes, uniformly distributing and extracting n-1 Bezier values along the horizontal coordinate on the curve according to the number n of each row of air film holes, 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 air film holes on the trend node curve obtained in the step S31, and generating the absolute coordinates of the air film hole cores on the blade body shape according to the relative distance distribution interpolation.
5. The method for parameterized control and design of gas film holes of turbine blades according to claim 1, wherein in step S4, secondary development is performed by using a UG software cylinder modeling tool according to generated gas film hole parameters with specific formats, so as to complete rapid modeling of all gas film holes on a blade model.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310092469.1A CN115788598B (en) | 2023-02-10 | 2023-02-10 | Turbine blade air film hole parameterization control and design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310092469.1A CN115788598B (en) | 2023-02-10 | 2023-02-10 | Turbine blade air film hole parameterization control and design method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115788598A CN115788598A (en) | 2023-03-14 |
| CN115788598B true CN115788598B (en) | 2023-06-30 |
Family
ID=85430778
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310092469.1A Active CN115788598B (en) | 2023-02-10 | 2023-02-10 | Turbine blade air film hole parameterization control and design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115788598B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN118378495B (en) * | 2024-06-25 | 2024-08-30 | 北京航空航天大学 | Turbine performance reliability simulation method and system of liquid rocket engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107977523A (en) * | 2017-12-14 | 2018-05-01 | 中国航发沈阳发动机研究所 | A kind of turbine air cooling blade design method towards parameterized model |
| CN108563872A (en) * | 2018-04-16 | 2018-09-21 | 西北工业大学 | Mesh parameterization method and axial flow turbine Aerodynamic optimization design method based on the mesh parameterization method |
| CN114676533A (en) * | 2022-05-26 | 2022-06-28 | 中国航发四川燃气涡轮研究院 | Turbine moving blade cooling sensitivity analysis method coupled with air system |
| CN115585020A (en) * | 2022-08-29 | 2023-01-10 | 中国航发四川燃气涡轮研究院 | End wall cooling structure suitable for high-pressure turbine blade |
| CN115659527A (en) * | 2022-09-20 | 2023-01-31 | 长沙理工大学 | Gas film cooling hole outlet hole pattern design method based on multi-segment spline curve |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090104023A1 (en) * | 2005-07-19 | 2009-04-23 | Frederic Favray | Variable Nozzle Turbocharger |
| WO2014007934A1 (en) * | 2012-07-02 | 2014-01-09 | United Technologies Corporation | Gas turbine engine turbine vane airfoil profile |
| CN104598684B (en) * | 2015-01-19 | 2017-07-18 | 西北工业大学 | A kind of air film hole parametric modeling method |
| US10443396B2 (en) * | 2016-06-13 | 2019-10-15 | General Electric Company | Turbine component cooling holes |
| KR102164137B1 (en) * | 2017-04-27 | 2020-10-13 | 이스탄불 테크니크 위니웨르시테시 | New design method for creation and parametric modification of yacht hull surface |
| CN107288690B (en) * | 2017-07-07 | 2019-02-05 | 厦门大学 | A kind of turbine blade film cooling holes morpheme parameter correction method based on parameter of curve |
| CN108090275B (en) * | 2017-12-14 | 2021-12-28 | 中国航发沈阳发动机研究所 | Turbine air cooling blade configuration method facing parametric model |
| CN110727995B (en) * | 2018-06-29 | 2023-09-22 | 中国航发商用航空发动机有限责任公司 | Blade shape construction method, blade, and computer device |
| CN110096776B (en) * | 2019-04-22 | 2022-07-19 | 西北工业大学 | Parametric modeling and orientation optimization method for special-shaped air film holes on single-crystal turbine blade |
| CN112733252B (en) * | 2020-12-24 | 2024-03-29 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Design method of axial flow turbine blade formed by framework |
| CN114429001B (en) * | 2021-11-29 | 2024-10-15 | 哈尔滨工程大学 | Parameterized modeling method for turbine blade air film hole cooling structure |
| CN115329528A (en) * | 2022-05-29 | 2022-11-11 | 中国船舶重工集团公司第七0三研究所 | Power turbine wicker leaf profile forming method based on Bezier curve |
-
2023
- 2023-02-10 CN CN202310092469.1A patent/CN115788598B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107977523A (en) * | 2017-12-14 | 2018-05-01 | 中国航发沈阳发动机研究所 | A kind of turbine air cooling blade design method towards parameterized model |
| CN108563872A (en) * | 2018-04-16 | 2018-09-21 | 西北工业大学 | Mesh parameterization method and axial flow turbine Aerodynamic optimization design method based on the mesh parameterization method |
| CN114676533A (en) * | 2022-05-26 | 2022-06-28 | 中国航发四川燃气涡轮研究院 | Turbine moving blade cooling sensitivity analysis method coupled with air system |
| CN115585020A (en) * | 2022-08-29 | 2023-01-10 | 中国航发四川燃气涡轮研究院 | End wall cooling structure suitable for high-pressure turbine blade |
| CN115659527A (en) * | 2022-09-20 | 2023-01-31 | 长沙理工大学 | Gas film cooling hole outlet hole pattern design method based on multi-segment spline curve |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115788598A (en) | 2023-03-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115788598B (en) | Turbine blade air film hole parameterization control and design method | |
| US7191161B1 (en) | Method for constructing composite response surfaces by combining neural networks with polynominal interpolation or estimation techniques | |
| CN112528575B (en) | Multi-dimensional collaborative design method for multistage axial flow compressor of ship gas turbine | |
| CN101470771B (en) | Selection procedure for the arrangement of sectors of a stator ring for a turbomachine | |
| CN108563872B (en) | Grid parameterization method and axial flow turbine aerodynamic optimization design method based on grid parameterization method | |
| CN104281751B (en) | Turbine cooling blade parametrization constructing system and the method for a kind of feature based | |
| CN108549773B (en) | Grid parameterization method and turbine blade multidisciplinary reliability design optimization method based on grid parameterization method | |
| US6606612B1 (en) | Method for constructing composite response surfaces by combining neural networks with other interpolation or estimation techniques | |
| Chi et al. | Multi-dimensional platform for cooling design of air-cooled turbine blades | |
| CN112765732B (en) | Aviation blade topology optimization design method based on selective laser melting process | |
| CN101767185B (en) | Quantitative reverse deformation arrangement based method for designing cast model | |
| CN112548032B (en) | Casting method based on three-dimensional scanning | |
| CN107016161A (en) | Shaped-beam reflector antenna type face based on Zernike multinomials and trigonometric function describes method | |
| CN115455588A (en) | Turbine blade precision casting mold surface reversible deformation design method | |
| CN113094964B (en) | Method and device for generating blade machining coordinates | |
| US9358645B2 (en) | Adaptive machining method for smelted blades | |
| Coirier et al. | A Cartesian, cell-based approach for adaptively-refined solutions of the Euler and Navier-Stokes equations | |
| Wagner et al. | Multi-objective optimization of the cooling configuration of a high pressure turbine blade | |
| CN114048558B (en) | Modeling method for blade profile of air compressor with non-uniform contour error | |
| CN116127638A (en) | Method for generating three-dimensional solid grids of investment casting shell based on curvature method | |
| Hao et al. | Template-based hexahedral mesh generation for turbine cooling geometries | |
| Li et al. | An engineering rules based parameterization approach for turbine blade reverse engineering | |
| CN113821885A (en) | Aero-engine blade flow field computing platform based on grid automatic generation technology | |
| JP4981313B2 (en) | Three-dimensional shape processing apparatus, curved surface creation program, and curved surface creation method | |
| CN112380651B (en) | Method for extracting topological data of turbine cooling blade pipe network |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |