Air-Heated Guide Vane Tip Heating for Ice Prevention
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Solution Overview
Problem
Gas turbine engines face ice buildup in flow paths, particularly in guide vanes, during icing conditions, which can lead to engine damage and performance degradation, and existing anti-ice methods may not effectively prevent ice formation in all regions.
Innovation Solution
The design incorporates an inlet guide vane with an internal anti-ice flow passage that discharges anti-ice air radially inward toward the inner flow surface, ensuring effective heat transfer and preventing ice formation by maintaining energized flow along the leading edge and warming critical areas.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If hot air is used to raise component temperature to prevent ice formation, then ice build-up is prevented, but energy consumption increases
Solution Approach 1:
The patent applies local quality by directing hot air specifically to the tip region of the inlet guide vane where ice formation is most critical, rather than heating the entire component. The flow passage is configured to deliver hot air radially inward toward the inner flow surface at the tip, providing targeted thermal protection to the most vulnerable area while minimizing overall energy consumption.
2Reliability
If existing anti-ice methods are used, then some ice formation is prevented, but ice formation in tip region cannot be effectively prevented
Solution Approach 1:
The patent implements another dimension by changing the directional approach of hot air delivery. Instead of axial or circumferential flow patterns used in conventional systems, the flow passage is configured to deliver hot air in a radial direction inward toward the inner flow surface. This radial dimension allows direct thermal contact with the tip region's inner surface, effectively protecting areas that previous methods could not reach.
3Reliability
If guide vane structure is modified to include tip heating, then ice formation at tip is prevented, but device complexity increases
Solution Approach 1:
The patent applies merging by integrating the anti-ice flow passage directly into the inlet guide vane structure itself. The flow passage is formed as part of the vane's internal architecture, combining the structural function of the guide vane with the thermal protection function in a single integrated component, thereby minimizing additional complexity.
Solution Approach 2:
The inlet guide vane is designed with multi-functionality by incorporating both its primary aerodynamic guidance function and its secondary anti-ice protection function within the same component. The tip region of the guide vane serves dual purposes: maintaining airflow direction and receiving/distributing hot air to prevent ice formation, eliminating the need for separate anti-ice devices.
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 solution effectively discourages ice formation on the inner flow surface of the guide vane, ensuring continued engine operation and performance by maintaining the flow path's integrity and efficiency.
Implementation Method 1
an anti-ice flow passage located at the tip region between an internal cavity and an outer surface of each respective guide vane, the anti-ice flow passage having a flow port structured to eject a flow of the anti-ice air
Data Source
AI summary
An inlet guide vane for use in a gas turbine engine may include an internal cavity for receipt of an anti-ice air to discourage build-up of ice in a flow path of the gas turbine engine. The inlet guide vane can include an anti-ice flow passage formed in a tip of the inlet guide vane which receives the anti-ice air from the internal cavity prior to being discharged from the inlet guide vane. Anti-ice air can be discharged through a tip of the inlet guide vane, through a leading edge of the inlet guide vane, or into a shaft side passage provided in a component defining the inner flow surface. In another form, anti-ice air can be provided from a sump of the gas turbine engine, through a shaft side passage, and into the inlet guide vane before being discharged.