Aerodynamic Probe Groove Structure for Impurity and Icing Control
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Solution Overview
Problem
Existing aerodynamic measurement probes face issues with sealing moving assemblies to prevent infiltration of impurities, which can cause blockages and reduce measurement accuracy, and are vulnerable to icing due to large functional clearances that promote heat exchange.
Innovation Solution
The design incorporates an annular gap between the shaft and support with internal and external grooves that create vortices to guide impurities away from the rotating mechanism, using a rounded internal groove and rectangular external groove to manage ice, water, and solid particles, ensuring free rotation and thermal protection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a large functional clearance is used between the shaft and support, then the probe is protected from blockage by particles, but the probe becomes vulnerable to icing due to intense heat exchange with air
Solution Approach 1:
The functional clearance is segmented into multiple regions by introducing annular grooves (first groove, second groove, third groove) at different positions. These grooves create distinct zones that serve different functions: some regions allow air flow for particle management, while other regions provide thermal protection, thus resolving the contradiction between particle protection and icing vulnerability
Solution Approach 2:
Different regions of the functional clearance are given different qualities through the groove configuration. Certain areas have enhanced thermal insulation properties while others maintain open flow paths for particle evacuation. This local differentiation allows the same clearance structure to simultaneously protect against particles and prevent icing in critical areas
2Reliability
If sealing measures are implemented to prevent impurity infiltration, then particle blockage is prevented, but measurement accuracy and sensitivity are reduced
Solution Approach 1:
The annular grooves act as intermediary structures between the shaft and support. They provide a controlled interface that allows necessary air flow for particle management while maintaining measurement accuracy. The grooves serve as a mediator that reconciles the need for openness (for particle evacuation) with the need for precision (for accurate measurements)
Solution Approach 2:
The sealing approach is moved from a radial dimension (direct contact sealing) to an axial dimension (groove-based flow control). By using grooves that extend axially, the patent creates a three-dimensional flow path that manages particles without compromising the radial measurement accuracy, thus resolving the contradiction through dimensional transformation
3Measurement precision
If frictionless rotating guide bearings are used to allow free rotation, then response time and accuracy are improved, but impurities can infiltrate the interface between shaft and support
Solution Approach 1:
The harmful function of the functional clearance (allowing impurity infiltration) is extracted and separated from the useful function (enabling frictionless rotation). The grooves are designed to extract and channel impurities away from the rotation interface, allowing the clearance to simultaneously provide frictionless rotation and impurity management without compromising either function
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 solution effectively prevents impurity ingress, maintains measurement accuracy, and reduces icing risks by directing impurities to purge holes, enhancing probe robustness and operational reliability.
Implementation Method 1
an annular gap between the shaft and support with internal and external grooves that create vortices to guide impurities away from the rotating mechanism
Data Source
Figure 1~3
Figure 4
Figure 5a~5b
AI summary
Disclosed is an aerodynamic measurement probe intended to measure a local incidence of air flow circulating along the fuselage of an aircraft, said probe comprising a support (1) and a shaft (2) capable of rotating about a longitudinal axis (3) relative to the support (1), the support (1) and the shaft (2) being configured to form between them a gap (4) passing around an annular tab (2a) at the end of the shaft (2) in the support (1) for maintaining a functional clearance to allow one end of the shaft (2) to pivot freely in the support (1), and communicating with a circuit for discharging impurities (5), the gap (4) comprising an internal annular groove (6) that is formed in the support (1) around the axis of rotation and opens away from the axis directly onto the end part of the annular tab (2a), the profile of the internal groove (6) being rounded.