Turbine Vane Lubricant Cooling with Interpenetrating Flow Disruptors
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Solution Overview
Problem
Existing designs for outlet guide vanes in dual-flow aircraft turbomachines face challenges in achieving efficient thermal performance while simplifying the manufacturing process, particularly in integrating heat exchanger functions without increasing complexity.
Innovation Solution
The guide vane design incorporates interpenetrating studs on the extrados and intrados bodies, which increase heat exchange efficiency by disrupting the lubricant flow and enhancing convection, while being manufactured using conventional methods like machining or molding, facilitating the production process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the blade length is increased to improve heat exchange efficiency, then the thermal performance is improved, but the manufacturing cost and complexity increase
Solution Approach 1:
The patent applies nesting by placing studs inside the blade structure. The studs are positioned within the blade thickness, creating internal flow disruption elements without extending the external blade length. This nested configuration allows heat exchange enhancement while maintaining compact dimensions and simpler manufacturing compared to longer blades.
Solution Approach 2:
The patent transitions from extending blade length (one dimension) to incorporating internal studs (utilizing the thickness dimension). By disrupting flow in the internal dimension rather than increasing external dimensions, the patent achieves heat exchange improvement without proportionally increasing manufacturing complexity.
2Productivity
If conventional ACOC exchangers are removed to simplify the system, then the overall efficiency is improved, but the lubricant cooling capacity must be integrated into the guide vanes
Solution Approach 1:
The patent merges the heat exchange function with the guide vane structure by integrating studs directly into the vane. This combination eliminates the need for separate ACOC exchangers, reducing system complexity and improving overall efficiency while maintaining lubricant cooling capability within the unified vane structure.
Solution Approach 2:
The guide vane is designed to perform multiple functions: flow guidance and lubricant cooling. By equipping the vane with internal studs that disrupt lubricant flow, the same component serves both aerodynamic and thermal management roles, eliminating dedicated cooling equipment and simplifying the overall system.
3Area of stationary object
If multiple series of studs are added to increase wetted surface area, then heat exchange is improved, but manufacturing complexity increases
Solution Approach 1:
The patent segments the heat exchange function into multiple discrete studs arranged in series within the blade. This segmentation creates extensive wetted surface area through numerous small elements rather than one large complex structure, allowing standardized manufacturing of individual studs that can be systematically arranged to achieve high heat exchange efficiency.
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 enhances thermal performance by increasing the wetted surface area and convection phenomena without requiring complex manufacturing processes, thus addressing the need for efficient thermal function and simplified manufacturing.
Implementation Method 1
increase the wetted surface, with the aim of ensuring better heat exchange. Thus, the higher the desired thermal performance, the longer and/or more costly the manufacture
Implementation Method 2
it has also been proposed to assign an additional function to the outlet guide vanes. This is a heat exchanger function between the outside air passing through the crown of outlet guide vanes, and the lubricant circulating inside these vanes
Data Source
Figure 1~2
Figure 2a~2b
Figure 3~4
AI summary
The invention relates to a guide vane (24) for an aircraft turbomachine, the aerodynamic part (32) of the vane being defined by an upper surface body (32a) and an lower surface body (32b), the part (32) comprising an internal passage (50a) for lubricant cooling equipped with flow-disrupting studs (80a, 80b), among which a first series of studs (80a) made in one piece with the upper surface body (32a), and a second series of studs (80b) made in one piece with the lower surface body (32b), the studs of the second series defining between them a second inter-stud space (84b) penetrated by the studs (80a) of the first series while a first inter-stud space (84a) is penetrated by the studs (80b) of the second series. In addition, the end of the studs (80a) is located at a distance from the intrados body (32b), as is the end of the studs (80b) located at a distance from the extrados body (32a).