Non-Axisymmetric Surface Modeling for Aero Engine Rotors
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current methods for modeling non-axisymmetric surfaces in aeronautical equipment, such as turbojet rotors, face challenges in maintaining aeromechanical soundness and continuity, particularly in the characterization of sections between blades, leading to discontinuities and singularities, which are difficult to manage and manufacture effectively.
Innovation Solution
A method that intentionally allows discontinuities between elementary surfaces and corrects them a posteriori using connection curves and surfaces, ensuring continuity and aerodynamic quality while optimizing computing power, utilizing Bézier curves and splines to define and optimize the surface geometry.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If section characterization methods are used to model non-axisymmetric surfaces, then aerodynamic optimization is improved, but geometric continuity and manufacturing feasibility deteriorate due to discontinuities between elementary surfaces
Solution Approach 1:
The patent divides the non-axisymmetric surface into multiple elementary surfaces, each characterized by independent section parameters. This segmentation allows aerodynamic optimization of each section while maintaining overall surface continuity through controlled transitions between segments.
Solution Approach 2:
The patent introduces intermediate control points and transition zones between elementary surfaces to mediate the connection. These intermediaries ensure geometric continuity and smooth transitions while preserving the aerodynamic benefits of section-wise characterization.
2Adaptability or versatility
If discontinuities are introduced between elementary surfaces for aerodynamic optimization, then flow path control is improved, but geometric soundness deteriorates due to singularities
Solution Approach 1:
The patent applies local quality by allowing controlled discontinuities only in specific regions where aerodynamic optimization requires it, while maintaining geometric soundness in other critical areas. This selective approach enables flow path control without compromising overall geometric reliability.
Solution Approach 2:
The patent performs preliminary geometric validation and continuity checks before finalizing the surface model. This preliminary action ensures that discontinuities introduced for aerodynamic optimization do not create geometric singularities that would compromise manufacturing or structural integrity.
3Adaptability or versatility
If complex section characterization is used to define non-axisymmetric surfaces, then aerodynamic performance is improved, but computational complexity increases
Solution Approach 1:
The patent segments the complex surface definition into multiple simpler elementary surfaces with independent parameters. This segmentation reduces computational complexity by allowing localized optimization without requiring global recalculations, while still achieving improved aerodynamic performance.
Solution Approach 2:
The patent applies partial action by optimizing only the critical sections that most impact aerodynamic performance, rather than uniformly optimizing the entire surface. This approach achieves significant aerodynamic improvement with reduced computational effort compared to full-surface optimization.
Data Source
Figure 1a
Figure 1b
Figure 1c
AI summary
The present invention relates to a method for modeling at least part of a non-axisymmetric surface (S) of one portion (2) of a part (1), the portion (2) being bounded by a first and a second extremal planes (PS, PR). The method is characterized in that it includes the implementation, by a means (11) for processing data from a device (10), of the following steps: (a) modeling at least two basic non-axisymmetric surfaces (Sk, SI, SE) making up said surface (S), each of the basic surfaces (Sk, SI, SE) extending between both extremal planes (PS, PR) of the portion (S) that are juxtaposed so as to have a junction of at least C1 at the extremal planes (PS, PR) and at least one discontinuity; (b) constructing at least one C1 connection curve (CR) tangential to the first and second surfaces; (c) locally modifying the first and second basic surfaces (Sk, SI, SE) such as to keep to said connection curve (CR) near said discontinuity; and (d) restoring, on one interface (13) of said device (10), said at least part of the obtained surface (S).