Turbomachinery Vane Dual Deicing Circuits
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Solution Overview
Problem
Turbomachinery components, such as vanes in aircraft engines, face icing issues during certain flight phases, leading to performance degradation and potential damage, and turbulence at assembly clearance zones reduces efficiency.
Innovation Solution
A vane with dual deicing fluid flow circuits and selection means to direct fluid flow based on operating states, utilizing deicing air from the compressor outlet to effectively prevent icing and reduce turbulence by adjusting fluid distribution through distinct zones within the vane.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single deicing fluid flow circuit is used in the vane, then the structure is simple, but it cannot effectively address icing conditions across different operating states and reduce turbulence simultaneously
Solution Approach 1:
The single fluid circuit is segmented into two distinct circuits: a first circuit with outlets at the trailing edge for deicing the blade portion, and a second circuit with outlets at the axial ends for reducing turbulence at clearance zones. This segmentation allows each circuit to perform its specific function independently, improving overall deicing effectiveness while managing complexity through functional division.
Solution Approach 2:
The system incorporates selection means (valves or variable geometry elements) that dynamically direct the majority of deicing fluid toward either the first or second circuit based on the operating state. This dynamic adaptation allows the system to optimize fluid distribution for different flight conditions, maintaining high reliability without requiring two completely independent circuit systems.
2Object-affected harmful factors
If deicing fluid is directed to the trailing edge circuit, then the blade portion is effectively deiced, but turbulence at assembly clearance zones is not reduced
Solution Approach 1:
The fluid circuit system is segmented into two separate circuits with distinct outlet locations: the first circuit directs fluid to the trailing edge to prevent ice accumulation on the blade portion, while the second circuit directs fluid to the axial ends to reduce turbulence at the clearance zones. This segmentation allows simultaneous addressing of both harmful effects through selective fluid distribution.
Solution Approach 2:
Different regions of the vane receive different quality and quantity of deicing fluid based on local requirements. The trailing edge region receives fluid primarily for ice prevention, while the axial end regions receive fluid primarily for turbulence reduction. The selection means enables local adaptation of fluid distribution to match the specific needs of each zone.
3Ease of manufacture
If the vane structure is simplified without dual circuits, then manufacturing is easier, but the ability to adapt to different operating states is reduced
Solution Approach 1:
The vane incorporates dynamic selection means (valves or variable geometry elements) that allow the system to adapt fluid distribution to different operating states. These dynamic elements are integrated into the vane structure in a way that maintains relative manufacturing simplicity while enabling the system to respond appropriately to varying flight conditions by directing fluid to the most needed circuit.
Solution Approach 2:
The dual-circuit vane structure is designed to perform multiple functions within a single integrated component. The same vane structure houses both deicing circuits and can switch between different operational modes (trailing edge deicing, clearance zone turbulence reduction, or combined operation), providing multi-functionality without requiring separate components for each 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 de-ices the vane and reduces turbulence at assembly clearance zones, enhancing turbomachinery efficiency and preventing ice accumulation, even at high engine speeds.
Implementation Method 1
Due to the pressure difference between the concave surfaces 5 and the convex surfaces 6 of the vanes, sheets of vortices 17 passing circumferentially through the above-mentioned clearance zones can flow from the higher-pressure zones to the lower-pressure zones
Data Source
AI summary
A vane for turbomachinery, such as, for example, an aircraft turbojet or turbofan engine, or an aircraft turboprop engine. The vane includes: (i) a first deicing fluid flow circuit inside the vane; (ii) a second deicing fluid flow circuit inside the vane; and (iii) a selector for directing the majority of the fluid towards the first circuit when the turbomachinery is in a first operating state, and for directing the majority of the fluid towards the second circuit when the turbomachinery is in a second operating state.