CN-122020910-A - Parameterization method and system for turbine blade

CN122020910ACN 122020910 ACN122020910 ACN 122020910ACN-122020910-A

Abstract

The embodiment of the disclosure provides a parameterization method and a parameterization system for a turbine blade, which are characterized in that a parameterization target is established by determining core components of the blade, each core component (a blade crown, a blade body, a blade root and an internal cooling cavity) is subjected to block geometric parameterization based on experimental parameters of blade design engineering, a parameterization depth is thinned in a layering (core layer, an expanding layer and a thinning layer) mode to control a parameter scale and supplement detail characteristics to form a complete parameterization result and output, so that the optimization of the whole blade and a sub-module is unified, the intuitiveness of the parameter and the optimization efficiency are improved, and the problems of excessive control parameters, low optimization efficiency and asynchronous modification among components in the parameterization of the complex turbine blade are solved.

Inventors

ZHANG HAO
XIAO JUNFENG
GAO SONG
LI YUANYUAN
YU FEILONG
DUAN JINGYAO
HE WEI
WU YAOZU
WU HE

Assignees

西安热工研究院有限公司

Dates

Publication Date: 20260512
Application Date: 20260227

Claims (10)

1. A method of parameterizing a turbine blade, the method comprising: Aiming at the existing three-dimensional model of the turbine blade, determining the core component part of the turbine blade, and establishing a geometric parameterized overall target; Determining reference geometric parameters of each connection position according to the core component, restricting the connection position relation, and parameterizing the geometric characteristics of the connection position; geometrically parameterizing the core component based on turbine blade geometry design features; Hierarchically refining the parameterized depth of the core component, and gradually increasing the scale of the control parameter; establishing association constraints between the reference geometric parameters of the connection locations and the core components; And supplementing the detail characteristic geometric parameters of the turbine blade to form a turbine blade complete parameterization result, and determining the total number of control parameters and the parameter constraint relation.
2. A method of parameterizing a turbine blade according to claim 1, wherein said core components comprise a shroud, a blade body, a blade root and an internal cooling gallery, and/or, The geometric parameterized overall objective is determined from turbine blade geometric optimization ranges including structural strength optimization, aerodynamic thermal optimization, and fluid-solid coupling optimization.
3. The method of parameterizing a turbine blade according to claim 2, wherein said determining the reference geometry of each connection location comprises: defining a reference coordinate system of the three-dimensional model of the turbine blade, determining the associated datum points of each connecting position, and restricting the positions among the associated datum points to establish an associated datum point mapping relation.
4. The method of parameterizing a turbine blade according to claim 3, wherein said geometrically parameterizing said core component comprises: Establishing a reference coordinate system of each core component by taking the connection position associated datum point of each core component as a reference, performing geometric parameterization in blocks, The geometric parameterization adopts experimental parameters of blade design engineering.
5. A method for parameterizing a turbine blade according to claim 4, wherein the control parameters comprise the number of profile sections in the radial height direction of the turbine blade, the height coordinates of the sections, the profile geometry of the sections when geometrically parameterizing the blade body, The blade profile geometrical parameters comprise at least one of blade profile chord length, installation angle, geometrical air inlet angle, geometrical air outlet angle, leading edge shape parameters, trailing edge shape parameters, blade profile pressure surface Bezier curve control points, blade profile suction surface Bezier curve control points, maximum thickness, blade profile lag angle and throat size.
6. The method of parameterizing a turbine blade according to claim 4, wherein the control parameters include at least one of internal cooling cavity cross-sectional profile, centerline trajectory, wall thickness between the internal cooling cavity and the turbine blade outer surface, diaphragm wall thickness, cooling hole design parameters for different height cross-sections when geometrically parameterizing the internal cooling cavity.
7. The method of parameterizing a turbine blade according to claim 2, wherein said establishing an associated constraint between a reference geometry of said connection location and said core component comprises: converting blade profile control parameters of sections of turbine blades with different heights into control parameters under a cylindrical coordinate system; calculating the height difference between the section of the blade profile control parameter and the characteristic rotating surface of the connecting position, and calculating the blade profile control parameter on the height of the rotating surface by an interpolation method; and converting the leaf profile control parameters under the cylindrical coordinate system into the leaf profile control parameters under the Cartesian coordinate system to obtain the association constraint between the leaf profile control parameters and the characteristic rotating surface of the connecting position.
8. The method of parameterizing a turbine blade according to claim 2, wherein said hierarchically refining said core component parameterized depth comprises: Dividing the control parameters into a core layer, an expansion layer and a refinement layer, wherein, For the blade body, the control parameters of the core layer comprise the chord length, the mounting angle, the geometric air inlet angle, the geometric air outlet angle, the maximum thickness and the throat size of the blade body; for the internal cooling gallery, the control parameters of the core layer include the wall thickness between the internal cooling gallery and the outer surface of the turbine blade.
9. The method of parameterizing a turbine blade according to any one of claims 1 to 8, wherein the turbine blade detail features comprise connection location fillets; after the turbine blade complete parameterization result is formed, a turbine blade control parameter list and a parameterized geometry file are output, wherein, The parameters in the control parameter list include constraint relationships of associated parameters.
10. A parameterized system of turbine blades, the system comprising: the parameterized target setting module is used for determining a turbine blade core component part aiming at the existing turbine blade three-dimensional model and establishing a geometric parameterized overall target; The connection position parameterization module is used for determining the reference geometric parameters of each connection position according to the core component, restricting the connection position relation and parameterizing the geometric characteristics of the connection position; the core component parameterization module is used for geometrically parameterizing the core component based on turbine blade geometric design characteristics; the parameter depth control module is used for hierarchically refining the parameterized depth of the core component part and gradually increasing the control parameter scale; the association constraint establishing module is used for establishing association constraints between the reference geometric parameters of the connection positions and the core component parts; the detail supplementing and outputting module is used for supplementing the detail characteristic geometric parameters of the turbine blade, forming a turbine blade complete parameterization result and determining the total number of control parameters and the parameter constraint relation.

Description

Parameterization method and system for turbine blade Technical Field The embodiment of the disclosure belongs to the technical field of turbine blade geometric parametrization, and particularly relates to a parametrization method and system of turbine blades. Background The parameterization work of the turbine blade of the gas turbine is an important link in the blade design and optimization, and the selection of the parameterization method directly influences the period and effect of the blade design and optimization. For complex turbine blades, such as gas turbine blades with crowns and complex internal cooling channels, the parameterized effort will increase significantly, and it is a big problem how to achieve blade geometry control with as few and accurate parameters as possible. Along with the wide application of the parameterized fitting algorithm, the deviation between the parameterized geometry and the target geometry is controlled through the fitting method, so that the fine control of any geometric feature is realized, and the parameterized fitting algorithm has the advantage of extremely high degree of freedom of adjustment. However, in the field of turbine blades with complex structures, the adoption of a parametric fitting method will generate a large number of control parameters, greatly increasing the complexity of geometric optimization, and further resulting in loss of geometric optimization period and efficiency. Disclosure of Invention Embodiments of the present disclosure are directed to at least one of the technical problems identified in the prior art, and provide a method and system for parameterizing turbine blades. One aspect of the present disclosure provides a method of parameterizing a turbine blade, the method comprising: Aiming at the existing three-dimensional model of the turbine blade, determining the core component part of the turbine blade, and establishing a geometric parameterized overall target; Determining reference geometric parameters of each connection position according to the core component, restricting the connection position relation, and parameterizing the geometric characteristics of the connection position; geometrically parameterizing the core component based on turbine blade geometry design features; Hierarchically refining the parameterized depth of the core component, and gradually increasing the scale of the control parameter; establishing association constraints between the reference geometric parameters of the connection locations and the core components; And supplementing the detail characteristic geometric parameters of the turbine blade to form a turbine blade complete parameterization result, and determining the total number of control parameters and the parameter constraint relation. Further, the core components include a tip shroud, a blade body, a blade root, and an internal cooling gallery, and/or, The geometric parameterized overall objective is determined from turbine blade geometric optimization ranges including structural strength optimization, aerodynamic thermal optimization, and fluid-solid coupling optimization. Further, the determining the reference geometric parameter of each connection position includes: defining a reference coordinate system of the three-dimensional model of the turbine blade, determining the associated datum points of each connecting position, and restricting the positions among the associated datum points to establish an associated datum point mapping relation. Further, the geometrically parameterizing the core component includes: Establishing a reference coordinate system of each core component by taking the connection position associated datum point of each core component as a reference, performing geometric parameterization in blocks, The geometric parameterization adopts experimental parameters of blade design engineering. Further, when the blade body is geometrically parameterized, the control parameters include the number of blade profile sections in the radial height direction of the turbine blade, the height coordinates of each section, and the blade profile geometry of each section, wherein, The blade profile geometrical parameters comprise at least one of blade profile chord length, installation angle, geometrical air inlet angle, geometrical air outlet angle, leading edge shape parameters, trailing edge shape parameters, blade profile pressure surface Bezier curve control points, blade profile suction surface Bezier curve control points, maximum thickness, blade profile lag angle and throat size. Further, when the internal cooling gallery is geometrically parameterized, the control parameters include at least one of internal cooling gallery cross-sectional profile, centerline trajectory, wall thickness between the internal cooling gallery and the turbine blade outer surface, diaphragm wall thickness, and cooling hole design parameters for different height cross-sections. Further, the establishing assoc