Compressor Blade Sinusoidal Trailing Edge Stability
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Solution Overview
Problem
Gas turbine engine compressor blades face a trade-off between high efficiency at one operating point and high stability across varying engine speeds, often requiring compromises that increase weight, complexity, and fuel consumption.
Innovation Solution
A novel compressor blade design that simultaneously optimizes the suction and pressure surfaces for efficiency and stability, featuring a thicker trailing edge with a sinusoidal pattern to control vortex shedding and minimize losses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the blade is designed for high efficiency at one operating point, then fuel consumption is reduced, but stability across varying engine speeds deteriorates
Solution Approach 1:
The blade design applies different geometric characteristics to different regions of the blade. The suction surface and pressure surface are designed with different curvature and thickness distributions to simultaneously achieve high efficiency at design point and high stability across operating range. This local differentiation allows each region to contribute optimally to both efficiency and stability requirements.
Solution Approach 2:
The blade geometry is designed with dynamic characteristics that allow it to adapt to varying operating conditions. The trailing edge is made thicker to control vortex shedding at high speeds, while the overall blade shape maintains efficiency at the design point. This dynamic geometric design enables the blade to maintain optimal performance across different engine speeds without requiring variable guide vanes or air bleed systems.
2Stability of the object's composition
If variable guide vanes and air bleed systems are introduced to ensure stability, then stability is improved, but device complexity and weight increase
Solution Approach 1:
The invention extracts and eliminates the need for variable guide vanes and air bleed systems by incorporating stability-enhancing features directly into the blade geometry itself. The thicker trailing edge and optimized surface profiles provide the necessary stability control without requiring separate auxiliary systems, thereby reducing overall device complexity.
Solution Approach 2:
The blade design merges the functions of efficiency optimization and stability control into a single integrated component. By combining the suction surface and pressure surface designs with the thicker trailing edge, the blade simultaneously achieves high efficiency at the design point and high stability across operating range, eliminating the need for separate variable guide vanes and air bleed systems.
3Stability of the object's composition
If the trailing edge is made thicker to control vortex shedding, then stability is improved, but vortex generation losses increase
Solution Approach 1:
The blade design changes the geometric parameters of the trailing edge by increasing its thickness, which fundamentally alters the vortex shedding characteristics. This parameter change suppresses harmful vortex generation while maintaining the stability benefits, achieving a balance between stability improvement and energy loss minimization through optimized trailing edge geometry.
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 achieves simultaneous high efficiency and stability, potentially eliminating the need for variable guide vanes and air bleed systems, reducing maintenance complexity, and improving fuel efficiency.
Implementation Method 1
the trailing edges of the pressure surface and suction surface of the blade are joined by a third trailing edge surface
Data Source
AI summary
The disclosure concerns a compressor blade for gas turbine engine. Specifically the blades of the compressor are modified according to predetermined requirements for both aerodynamic stability and fuel economy in multiple planes.