Turbine Engine Stator Fin Profile for Stall-Resistant Gas Flow
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Solution Overview
Problem
The existing stator blades in turbomachines experience secondary aerodynamic flows and corner separation, leading to pressure losses and aerodynamic stall, particularly at high angles of attack, which affects the efficiency of gas flow guidance.
Innovation Solution
A stator component with a specific geometry featuring blades and fins that reduce corner separation by limiting the angle between the blade profile and tangent to less than 45 degrees, along with a fin height ratio and chord ratios that guide the flow without separation, enhancing aerodynamic performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional stator blade geometry is used, then the structure is simple and easy to manufacture, but corner separation and aerodynamic stall occur leading to pressure losses
Solution Approach 1:
The invention applies curvature to the blade profile by defining a specific geometric constraint where the angle between the foot profile and the tangent to the section is less than or equal to 45 degrees. This curved geometric approach modifies the blade shape to prevent corner separation and reduce pressure losses while maintaining manufacturability through a clear geometric definition.
2Reliability
If conventional blade profile is used, then manufacturing is easy, but aerodynamic stall occurs at high angles of attack
Solution Approach 1:
The invention changes the geometric parameters of the blade profile by imposing a specific angle constraint (≤45 degrees) between the foot profile and the tangent to the section. This parameter modification improves aerodynamic performance and prevents stall at high angles of attack while maintaining ease of manufacture through a well-defined geometric criterion.
3Productivity
If standard stator blade design is used, then the structure is simple, but corner separation generates pressure losses and stall
Solution Approach 1:
By implementing a curved blade profile with the angle constraint (≤45 degrees) between the foot profile and the tangent to the section, the invention eliminates corner separation and prevents aerodynamic stall. This curved geometry significantly improves flow guidance efficiency and productivity while the geometric definition remains clear and manufacturable.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The proposed geometry significantly reduces corner separation and aerodynamic stall, improving fluid flow efficiency and reducing pressure losses, especially at high Mach numbers.
Implementation Method 1
corner separation and corner vortexing can occur. This separation generates pressure losses and aerodynamic stall
Data Source
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AI summary
The invention relates to a stator part (20) of a turbine engine, comprising a platform (22), a blade (24, 26) extending radially relative to a central axis (A), and a fin (28) extending radially from a fin root (44) to a fin tip (46), the fin comprising a lower side (48) and an upper side (50), each point (100) of the lower side or of the upper side defining a radial axis (Ar) passing through the point, each plane (Pr) that includes the radial axis defining a section (S) of the lower side or of the upper side, an angle defined in the plane between the root profile and a tangent to the section at an intersection (104) of the section and of the root profile being less than or equal to 45 degrees, the section being located between the root profile and the tangent.