Prismatic Vortex Generators for Supersonic Flow Control
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Solution Overview
Problem
Existing vortex generators for supersonic aircraft are not robust enough to withstand harsh pressure and aerodynamic loads, heat erosion, and debris impact, leading to reliability and maintainability issues in engine inlets and other supersonic airflow applications.
Innovation Solution
The use of prismatic-shaped vortex generators with inclined triangular faces and trapezoidal sidewalls, which are more resistant to pressure and heat erosion, and can deflect debris, improving their survivability and ease of manufacturing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If thin rectangular vortex generators are used, then flow separation can be attenuated, but the vortex generators lack robustness to withstand pressure and aerodynamic loads
Solution Approach 1:
The patent applies curvature by transitioning from flat rectangular surfaces to curved prismatic surfaces. The prismatic vortex generator features inclined triangular faces and trapezoidal sidewalls that curve smoothly, allowing airflow to follow the surface contour rather than separating abruptly. This curved geometry maintains structural integrity under pressure loads while effectively generating vortices to attenuate flow separation.
2Reliability
If thin rectangular vortex generators are used, then they can be positioned upstream of flow separation, but they are susceptible to heat erosion and debris impact
Solution Approach 1:
The patent converts the harmful effect of debris impact into a beneficial deflection mechanism. The inclined triangular faces are specifically designed to intercept and deflect debris particles away from the vulnerable thin sections of the vortex generator. The angled surfaces redirect the kinetic energy of impacting debris harmlessly, protecting the structural integrity while maintaining the vortex generation function.
3Ease of manufacture
If rectangular vortex generators are used, then they can generate vortices to prevent flow separation, but they are difficult to incorporate into manufacturing processes
Solution Approach 1:
The patent applies segmentation by dividing the complex prismatic geometry into simpler manufacturing stages. The vortex generator is constructed as a prismatic structure that can be fabricated from flat plate stock through sequential forming operations. The inclined triangular faces and trapezoidal sidewalls are created through controlled bending and shaping of the base material, breaking down the complex 3D geometry into manageable manufacturing steps that are easier to produce than monolithic complex shapes.
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 prismatic-shaped vortex generators effectively prevent flow separation, enhance reliability and maintainability, and tolerate debris impact, while being easier to produce and adapt for various supersonic airflow applications, including engine inlets and wing structures.
Implementation Method 1
The vortex generators proposed previously for supersonic engine inlets primarily consist of a plurality of short (smaller than the boundary layer height), thin rectangular blades (or microvanes) located downstream of the leading edge of the engine inlet
Implementation Method 2
Vortices that form off the tips of the blades can draw air down from the upper region of the boundary layer down toward the near-wall region to attenuate flow separation
Implementation Method 3
The thin, rectangular vortex generators also do not tolerate damage due to debris that may impact the vortex generator
Data Source
AI summary
A prismatic vortex generator for attenuating flow separation which occurs during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet engine inlet, or similar surfaces subjected to supersonic airflow. A series of prismatic vortex generators are provided, each of which is configured to generate a vortex which attenuates flow separation and weight drag resulting from the supersonic airflow. Each prismatic vortex generator has a prismatic shape with a base, leading and trailing ends, and sidewalls that incline toward and join each other to form an apex. The leading end of each prismatic vortex generators is inclined away from the direction of flow.