Twin-Spool Turbomachine Outlet Guide Vane Lubricant Cooling
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Solution Overview
Problem
Existing twin-spool turbomachine outlet guide vanes face challenges in enhancing heat dissipation capacity, mechanical strength, and leak tightness, particularly when performing both structural and heat exchange functions under high pressures.
Innovation Solution
A guide vane design featuring a single-piece aerodynamic part with heat transfer fins arranged in staggered rows at acute angles, improving thermal conduction and mechanical strength, and fabricated using additive methods to facilitate production and reduce leakage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If heat transfer fins are added to the guide vane to improve heat dissipation capacity, then the heat exchange function is enhanced, but the mechanical strength and leak tightness are compromised due to the complex high-pressure lubricant circulation
Solution Approach 1:
The patent merges the heat transfer fin structure with the guide vane body into a single integrated component. The fins are not separate attachments but are formed as an integral part of the vane, creating a unified structure that simultaneously performs both heat dissipation and structural functions. This integration eliminates the need for separate fastening mechanisms and creates a more robust design that can withstand high-pressure lubricant circulation while maintaining effective heat transfer surface area.
2Loss of energy
If conventional ACOC exchangers are reduced or eliminated to limit disturbances in bypass flow, then the global efficiency of the turbomachine is improved, but the heat dissipation capacity is reduced
Solution Approach 1:
The guide vane is designed to perform multiple functions simultaneously: it serves as a flow straightening device, a structural support element, and a heat exchanger. By integrating the heat transfer fins directly into the vane, the system eliminates the need for separate ACOC exchangers that would disturb the bypass flow, while still providing adequate heat dissipation capacity through the fins that are in direct contact with the lubricant and exposed to the bypass airflow.
3Ease of manufacture
If the guide vane is designed with integrated exchanger to facilitate fabrication, then the ease of manufacture is improved, but the complexity of ensuring leak tightness under high pressure increases
Solution Approach 1:
The integrated design merges the exchanger fins with the guide vane body into a single monolithic structure. This integration eliminates the need for separate components and assembly operations, simplifying fabrication while inherently ensuring leak tightness. The high-pressure lubricant circulation occurs within the unified structure where there are no separate joints or connections that could potentially leak, thus simultaneously improving ease of manufacture and ensuring reliability.
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 design enhances heat exchange efficiency, mechanical strength, and leak tightness, allowing for effective heat dissipation and structural functionality while reducing disturbances in the bypass flow, thereby increasing the overall efficiency of the turbomachine.
Implementation Method 1
the aerodynamic part of the vane made in a single piece also comprises heat transfer fins arranged in the first passage connecting the intrados and extrados walls and extending approximately parallel to the first direction
Data Source
AI summary
A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.