Fan Exit Guide Vane Deicing Structure With Integrated Cooling
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Solution Overview
Problem
Current gas turbine engine designs face challenges in managing structural loads and cooling systems, particularly in fan exit guide vanes, due to increased operating temperatures and decreased core sizes, which affect airflow and ice formation at the leading edge.
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 and prevents ice formation by utilizing heat transfer and fluid communication to suppress ice accumulation.
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 cooling capability and deicing functionality are insufficient
Solution Approach 1:
The fan exit guide vane is segmented into functional regions: a monolithic load carrying structure for strength, a cooling cavity for thermal management, and a leading edge deicing structure. This segmentation allows each region to perform its specific function optimally without compromising overall structural integrity.
Solution Approach 2:
The cooling cavity is nested within the fan exit guide vane structure, and the leading edge deicing structure is integrated into the vane assembly. This nesting approach allows multiple functions (structural support, cooling, deicing) to coexist within a compact configuration, improving thermal management without sacrificing strength.
2Power
If core size is decreased to improve engine design, then power density increases, but cooling capability deteriorates
Solution Approach 1:
The cooling system extends into the spanwise dimension with the cooling cavity running along the span of the fan exit guide vane. This dimensional extension provides increased cooling surface area and volume, compensating for the reduced core size and maintaining adequate cooling capability despite higher power density requirements.
3Productivity
If fan exit guide vanes are designed for optimal airflow and acoustic characteristics, then engine performance is improved, but ice formation at leading edge becomes problematic
Solution Approach 1:
The leading edge deicing structure is designed to prevent ice formation before it can adversely affect airflow and engine performance. By addressing the ice formation issue proactively through integrated deicing capability, the system maintains optimal aerodynamic characteristics without interruption from icing conditions.
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 formation while allowing for additional space for heat exchangers and improved thermal management, enhancing the performance and reliability 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
a leading edge deicing structure in fluid communication with the cooling cavity and the leading edge
Data Source
AI summary
A fan exit guide vane with a load member and cooling cavity including an inner attachment region opposite an outer attachment region; a load member cavity 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 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 in fluid communication with the cooling cavity and the leading edge.