Translatable Low-Drag Surface for High-Mach Skin Friction
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Solution Overview
Problem
Existing gas turbine engine designs face significant aerodynamic losses due to drag, particularly at high Mach numbers, leading to inefficient operation and potential vibration issues from non-uniform flow, which existing design constraints struggle to mitigate effectively.
Innovation Solution
A low drag surface design featuring a cut-out region with a continuously translatable surface portion that forms a fluidwash surface, reducing skin friction and altering the boundary layer, while being operable at high Mach numbers, and optionally incorporating actuators to control the translation speed and direction of the surface portion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If the surface area of the gas turbine engine is minimized to reduce drag, then aerodynamic losses are reduced, but the engine design becomes more constrained and difficult to manufacture
Solution Approach 1:
The surface is segmented into multiple zones with different properties: a static aerodynamic surface and a translatable surface portion that can move independently. This segmentation allows each zone to be optimized for its specific function while maintaining manufacturability of the overall structure.
Solution Approach 2:
The surface transitions from a completely static design to a dynamic design where the surface portion can translate relative to the aerodynamic surface. This dynamic capability allows the surface to adapt to flow conditions and reduce drag without requiring a complete redesign of the engine structure.
2Productivity
If the surface is designed to be more aerodynamic to minimize losses, then efficiency improves, but non-uniform flow is caused that exerts unsteady forces on downstream parts
Solution Approach 1:
The translatable surface portion dynamically adjusts the boundary layer characteristics to maintain more uniform flow downstream. By moving the surface portion, the system can actively control flow separation and reduce unsteady forces on downstream components while preserving aerodynamic efficiency.
Solution Approach 2:
The system changes the physical parameters of the surface (position, velocity) to optimize flow characteristics. By varying the translation speed and position of the surface portion, the boundary layer properties are modified to achieve both efficiency and flow uniformity.
3Loss of energy
If a translatable surface portion is added to reduce skin friction, then aerodynamic losses are reduced, but device complexity increases
Solution Approach 1:
The complex function of drag reduction is segmented into two parts: the static aerodynamic surface provides the base structure, while the translatable surface portion provides the active drag reduction mechanism. This segmentation makes the overall complex system more manageable and manufacturable.
Solution Approach 2:
The drag reduction function is extracted from the main engine structure and implemented as a separate translatable surface portion. This extraction allows the complex drag reduction mechanism to be designed and manufactured independently, then integrated with the engine.
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 low drag surface design significantly reduces aerodynamic losses and prevents ice accumulation by generating heat through friction, enhancing the efficiency and operational stability of gas turbine engines, especially at high Mach numbers.
Implementation Method 1
Low drag may mean that the translatable surface portion reduces skin friction on the low drag surface
Implementation Method 2
The continuously translatable surface translates such that it generates heat for preventing the accumulation of ice
Data Source
AI summary
A low drag surface is provided for a fluid washed object, the low drag surface comprising an aerodynamic surface comprising a cut-out region, and a continuously translatable surface comprising a surface portion. The surface portion is positioned in the cut-out region such that the aerodynamic surface and the surface portion form a fluidwash surface, and the surface portion is translatable relative to the aerodynamic surface.