A method for modeling and designing a combustor swirler vane
By generating swirl blades using parametric spline curves and thickness overlay technology, the problems of flow separation and pressure fluctuation in swirl combustion chambers were solved, and the flow acceleration and total pressure recovery coefficient were improved.
CN122389208APending Publication Date: 2026-07-14DANIU POWER TECHNOLOGY (MIANYANG) CO LTD
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Patent Information
- Authority / Receiving Office
- CN ยท China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- DANIU POWER TECHNOLOGY (MIANYANG) CO LTD
- Filing Date
- 2026-05-12
- Publication Date
- 2026-07-14
AI Technical Summary
Technical Problem
The existing swirl blade design of swirl combustors is prone to large total pressure loss and flow separation at high swirl numbers, and it is difficult to prevent pressure fluctuations in the combustor.
Method used
Parametric spline curves are used to describe the centerline of the swirl blades. Combined with thickness stacking and spanwise extension techniques, swirl blades with arbitrary smooth shapes are generated to ensure that the overall flow accelerates without decelerating, reduce losses, and improve the total pressure recovery coefficient.
Benefits of technology
It effectively reduces the total pressure loss of the swirl vane design, prevents flow separation and pressure fluctuations, and improves the stability and efficiency of the combustion chamber.
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Figure CN122389208A_ABST
Abstract
The application discloses a combustion chamber swirler blade modeling method, comprising the following steps: S1: determining the inner flow channel boundary, the outer flow channel boundary and the average flow surface generatrix of the swirler blade; S2: establishing a cylindrical coordinate system based on the average flow surface generatrix, adopting a cubic spline curve to describe the distribution relationship between the blade geometric angle and the average flow surface generatrix arc length, and solving to obtain the blade center line; S3: giving the thickness distribution of the blade surface, superimposing the thickness on the blade center line, and forming the blade cross section on the average flow surface; S4: extending the blade cross section on the average flow surface along the spanwise direction and intersecting with the inner flow channel boundary and the outer flow channel boundary to form a single swirler blade configuration; S5: arranging in the circumferential direction according to the number of blades to complete the blade modeling; and S6: controlling the blade passage flow area on the average flow surface to monotonously increase along the streamline direction in the modeling, so that the total pressure loss and the swirled number deviation are controlled. Compared with the prior art, the application has the advantages that a combustion chamber swirler blade modeling method and design method are provided, which can reduce the deviation between the designed swirled number and the actual swirled number, prevent non-uniform flow separation, and resist combustion chamber pressure fluctuation.
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