Turbine Vane Passive Air Circulation for Vortex Reduction
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Solution Overview
Problem
Aircraft turbomachine turbines experience aerodynamic losses due to secondary flow vortex structures formed around blades, which are not aligned with the main airflow direction and do not contribute to energy recovery, leading to inefficiency and increased fuel consumption.
Innovation Solution
The blade design incorporates an air circulation system with suction and ejection openings and an internal duct that isolates the boundary layer near the leading edge and reintroduces it at the trailing edge, reducing vortex phenomena by aligning the air flow with the main direction, thereby optimizing turbine efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional blade design is used, then the turbine structure is simple, but vortex structures form around the blade causing aerodynamic losses and efficiency reduction
Solution Approach 1:
The blade is segmented into functional zones with distinct airflow control mechanisms. Suction openings are positioned at specific locations (e.g., leading edge, mid-chord, trailing edge) to selectively remove boundary layer air from different regions, while ejection openings redistribute this air to control vortex formation. This segmentation allows targeted energy loss reduction without requiring complete redesign of the entire blade structure.
Solution Approach 2:
A passive air circulation system acts as an intermediary mechanism between the boundary layer and the mainstream flow. The system uses suction openings to extract low-momentum boundary layer air, transports it through internal passages, and ejects it at optimized locations to suppress vortex formation. This intermediary system reduces aerodynamic losses without requiring active control systems or complex external modifications.
2Productivity
If boundary layer is not controlled, then the blade structure remains simple, but vortex structures develop causing efficiency losses and increased fuel consumption
Solution Approach 1:
The air circulation system operates passively by utilizing the natural pressure gradient between the boundary layer region (higher pressure) and the suction openings (lower pressure). Boundary layer air is automatically drawn through suction openings without requiring external pumping or active control systems. The system self-regulates based on local flow conditions, reducing turbine efficiency losses while maintaining relatively simple structure.
Solution Approach 2:
The system modifies key flow parameters including boundary layer thickness, momentum distribution, and pressure gradient by strategically positioning suction and ejection openings. By controlling the amount and location of boundary layer air removal and redistribution, the system optimizes airflow attachment and reduces vortex formation, thereby improving turbine efficiency without proportionally increasing structural complexity.
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
This design significantly reduces vortex structures and enhances the overall efficiency of the turbine by ensuring the primary flow is used effectively in energy recovery, minimizing parasitic vortices and energy dispersion.
Implementation Method 1
the boundary layer of the upstream flow at the platform
Implementation Method 2
vortex structures initiated at the blade platforms
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
The invention relates to a vane for a turbine engine turbine comprising a blade (34) and at least one platform (39; 41) that radially extends the blade, and a system for reducing vortices comprising at least one circuit (44; 46) including a duct (47; 53) extending from at least one air intake orifice (48; 51) formed in the platform upstream of the leading edge as far as at least one air exhaust slot (49; 52) formed on the trailing edge.