Turbomachine Blade Row With Wavy Side Wall Contour
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Solution Overview
Problem
In turbomachines, secondary flows or channel vortices form due to differences in pressure gradients across blade cascades, leading to increased pressure losses and reduced efficiency.
Innovation Solution
The implementation of wavy sidewall contouring in blade channels with multiple elevations and depressions, which influence primary pressure gradients and outflow angles, reducing secondary flow vortices and improving flow distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional smooth side walls are used in blade channels, then the structure is simple and easy to manufacture, but secondary flows and channel vortices form due to pressure gradients, leading to increased pressure losses and reduced efficiency
Solution Approach 1:
The side wall contour is designed with wave-like curvature featuring multiple elevations and depressions instead of a smooth surface. This curvature modification influences the pressure gradient distribution and reduces secondary flows, directly addressing the energy loss problem while accepting increased geometric complexity
Solution Approach 2:
The side wall contour introduces local variations in the form of elevations and depressions at specific positions along the side wall. These local geometric modifications create favorable pressure gradients in critical regions, reducing secondary flows and improving overall flow distribution without requiring complete redesign of the entire blade channel
2Productivity
If wave-like side wall contouring with elevations and depressions is implemented, then secondary flows are reduced and outflow angle alignment is improved, but the side wall contour becomes more complex
Solution Approach 1:
The wave-like contour with elevations and depressions modifies the side wall geometry to influence pressure gradients and improve flow characteristics. This curvature approach enhances productivity by reducing secondary flows and improving outflow angle alignment, while the complexity is managed through systematic contour design
Solution Approach 2:
The side wall contour parameters such as elevation height, depression depth, wavelength, and position are optimized to achieve the desired flow control. By adjusting these geometric parameters, the system improves turbomachine efficiency while maintaining manufacturable complexity levels
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 reduces secondary flows and enhances the alignment of the outflow angle, resulting in improved turbomachine efficiency without inducing additional vortices or mixing losses.
Implementation Method 1
A primary or main flow guided through a flow channel is deflected by a lateral pressure gradient parallel to the boundary wall
Implementation Method 2
Since flow layers near the wall are deflected more strongly than those further away due to their lower velocity, a secondary flow or channel vortex is formed
Implementation Method 3
A primary or main flow guided through a flow channel is deflected by a lateral pressure gradient parallel to the boundary wall
Data Source
Figure 1
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AI summary
A blade grid of a turbomachine is disclosed, the circumferential side wall of which is wave-like and has at least two protrusions and at least one depression or at least two depressions and at least one protrusion, as well as a turbomachine with such a blade grid.