Aircraft Turbomachine Exit Guide Vane Lubricant Passage Design
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Solution Overview
Problem
The existing design of outlet guide vanes in turbomachines suffers from lubricant recirculation and reduced heat exchange capacity due to a bent area without heat transfer means, leading to pressure losses and mechanical weakness under high lubricant pressures.
Innovation Solution
Incorporating lubricant guides within the bent area, extending parallel to the curved generatrix, which connects the interior passages and enhances heat transfer and mechanical strength by increasing the wet surface area and promoting lubricant flow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If the bent area is left free without heat transfer means, then pressure drops are limited, but lubricant recirculation occurs and heat exchange capacity is reduced
Solution Approach 1:
A flow director element is introduced as an intermediary component in the bent area to guide lubricant flow from the first interior passage to the second interior passage. This mediator prevents recirculation by directing the flow along the intended path, resolving the contradiction between limiting pressure drops and ensuring flow stability.
Solution Approach 2:
The geometry of the bent area is modified by introducing a flow director element that changes the flow parameters (direction, velocity distribution) of the lubricant. This parameter change prevents recirculation while maintaining acceptable pressure drops, addressing both aspects of the contradiction.
2Loss of energy
If the bent area is left free without heat transfer means, then pressure drops are limited, but heat exchange capacity is reduced
Solution Approach 1:
Heat transfer means are selectively placed in the straight interior passages where they can effectively cool the lubricant, while the bent area is designed with a flow director to maintain flow stability. This local differentiation allows heat exchange enhancement in appropriate locations without compromising flow stability in the bent area.
3Temperature
If heat transfer means are implanted in interior passages, then heat exchange capacity is improved, but mechanical resistance is reduced in the bent area
Solution Approach 1:
The flow director element serves as a structural intermediary that reinforces the bent area, providing the necessary mechanical resistance to withstand high lubricant pressures while allowing the heat transfer means to be effectively installed in the interior passages for enhanced heat exchange capacity.
4Device complexity
If outlet guide vanes are used for heat exchange, then ACOC exchangers can be reduced or eliminated, but lubricant recirculation and pressure losses occur
Solution Approach 1:
The flow director element acts as a necessary intermediary component that enables the outlet guide vane to function effectively as a heat exchanger by preventing lubricant recirculation in the bent area, thereby maintaining low pressure losses while achieving the simplified exchanger configuration.
Solution Approach 2:
The outlet guide vane is designed to perform multiple functions: flow straightening, heat exchange, and flow direction control in the bent area. This multi-functionality allows the elimination of separate ACOC exchangers while maintaining system efficiency through the integrated flow director solution.
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 lubricant guides effectively prevent recirculation, improve heat transfer efficiency, and reinforce the mechanical strength of the bent area, addressing the issues of pressure losses and reduced heat exchange capacity.
Implementation Method 1
heat transfer means are arranged in the first interior passage extending along a first main flowing direction of the lubricant
Implementation Method 2
heat exchanger function is obtained on the vane by providing one or more interior passage(s) within this vane, and by implanting heat transfer means within these passages
Data Source
AI summary
The invention relates to a guide vane for a bypass aircraft turbomachine, its aerodynamic part comprising a first lubricant cooling interior passage in which heat transfer structures are arranged and a second lubricant cooling interior passage in which heat transfer structures are arranged, the aerodynamic part comprising a bent area connecting a lubricant output end of the first interior passage to a lubricant input end of the second passage, the bent area extending along a curved generatrix and being partly delimited by the intrados wall and the extrados wall of the vane. According to the invention, the bent area comprises one or more lubricant guide(s) arranged between the intrados and extrados walls of the vane, and each extending substantially parallel to the curved generatrix of the bent area.