Fan Exit Guide Vane Structure With Integrated Leading Edge Deicing
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Solution Overview
Problem
Current gas turbine engine designs face challenges in managing airflow back pressure, structural load distribution, and ice formation on fan exit guide vanes, particularly with increasing operating temperatures and decreasing core sizes.
Innovation Solution
The implementation of a fan exit guide vane with a load carrying member and leading edge deicing structure, featuring a load member cavity, cooling cavity, and a leading edge deicing structure, which supports structural loads, facilitates heat transfer, and prevents ice formation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a monolithic load carrying structure is used in fan exit guide vanes, then structural strength is maintained, but ice formation prevention capability is insufficient
Solution Approach 1:
The fan exit guide vane is divided into functional segments: a monolithic load carrying structure for strength, and integrated deicing cavities/channels for ice prevention. This segmentation allows each component to specialize in its function while working together as a unified system.
Solution Approach 2:
The deicing functionality is merged into the load carrying structure by integrating deicing cavities and fluid channels directly into the vane body. This combines structural support and ice prevention into a single integrated component, eliminating the need for separate deicing systems.
2Productivity
If core size is decreased to improve engine efficiency, then operating temperature increases, but cooling and deicing capability becomes more challenging
Solution Approach 1:
The deicing system utilizes the spanwise dimension of the fan exit guide vane, extending deicing cavities and fluid channels along the span from root to tip. This dimensional approach provides sufficient surface area for heat transfer and deicing functionality without interfering with the core size reduction.
Solution Approach 2:
The system changes the thermal parameters by introducing heated fluid through the deicing channels to counteract the increased operating temperatures. This allows the engine to operate at higher temperatures for improved efficiency while maintaining ice prevention capability through controlled thermal parameters.
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 design effectively manages structural loads and prevents ice accumulation while allowing for additional design features like heat exchangers, enhancing the performance and efficiency of the gas turbine engine.
Implementation Method 1
the cooling cavity being configured to support heat transfer from a working fluid to a fan bypass flow
Implementation Method 2
the leading edge deicing structure being configured to suppress ice formation proximate the leading edge
Data Source
Figure 1~3
Figure 4~4a
Figure 5~5a
AI summary
A fan exit guide vane (18) with a load member (42) and cooling cavity (74) including an inner attachment region (30) opposite an outer attachment region (30); a load member cavity (44) formed within the fan exit guide vane extending spanwise through the fan exit guide vane from the inner attachment region to the outer attachment region; the load member extending through the load member cavity beyond each of the inner attachment region and the outer attachment region of the fan exit guide vane; a cooling cavity (74) formed within the fan exit guide vane extending spanwise through the fan exit guide vane between the inner attachment region and the outer attachment region; and a leading edge deicing structure (86) in fluid communication with the cooling cavity and the leading edge (26).