Guide Vane Root Relief Duct for Aircraft Gas Turbine
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Solution Overview
Problem
Existing aircraft gas turbine designs with relief ducts in bypass ducts face inefficiencies due to struts impairing airflow and complex structural requirements, leading to reduced overall efficiency and increased costs.
Innovation Solution
Designing the blade root of the guide vane as a structural element with the relief duct integrated into it, allowing the relief duct to open into the bypass duct downstream of the guide vanes, thus optimizing structural support without disrupting the load path and maintaining low-loss airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If additional struts are arranged downstream of the guide vanes to support the core engine, then the core engine can be mounted, but the struts impair the course of flow in the bypass duct and reduce overall efficiency
Solution Approach 1:
The invention merges the structural support function with the flow guidance function by designing the guide vanes themselves as load-bearing elements that form the struts for mounting the core engine. This integration eliminates separate flow-impairing strut structures while maintaining both structural support and optimal airflow through the bypass duct.
Solution Approach 2:
The guide vanes are designed to perform multiple functions simultaneously: they guide the airflow through the bypass duct and also serve as structural ribs or struts for supporting the core engine. This multi-functionality eliminates the need for additional dedicated support structures that would interfere with flow.
2Stability of the object's composition
If the relief channel is arranged downstream of the guide vanes but upstream of the struts for structural reasons, then structural stability is maintained, but sufficient axial overall length is required and complex constructions result
Solution Approach 1:
The relief channel is integrated directly into the guide vane structure, combining the flow relief function with the structural guide vane elements. This integration eliminates the need for separate complex arrangements of struts and relief channels, reducing construction complexity while maintaining structural stability.
3Strength
If guide vanes are designed as load-bearing elements for mounting the core engine, then structural support is provided, but the bypass duct crosses the load path in the front frame requiring high design effort
Solution Approach 1:
The guide vanes are designed as integral load-bearing elements that form the structural ribs for mounting the core engine. The relief channel is incorporated into the guide vane platform, allowing the load path to run undisturbed through the guide vanes while the relief duct penetrates without disturbing the force-transmitting structure.
Data Source
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AI summary
The invention relates to an aircraft gas turbine with a core engine 10 and a bypass channel 29 surrounding it, wherein the core engine 10 comprises a pre-compressor 30 in its inlet region, in the region of which at least one relief channel 31 is provided for directing an airflow from the pre-compressor 30 into the bypass channel 29, and with a guide vane row 32 arranged downstream of a fan 12 in the bypass channel 29, characterized in that a blade root 33 of the guide vane 32 is designed as a structural element supporting the core engine and that the relief channel 31 is formed in the blade root 33 and opens downstream of the guide vane 32 into the bypass channel 29.