Gas Turbine Conduit Protrusions for Thermal Gradient Management
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engine conduits experience significant thermal gradients due to the lack of heat transfer features, leading to structural concerns such as low-cycle fatigue and stress from temperature differences between connected sections.
Innovation Solution
Incorporating a protrusion configuration on the interior or exterior surfaces of conduits, which acts as a heat transfer surface to reduce thermal gradients and alleviate stress, potentially with a minor increase in pressure loss.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If smooth conduit surfaces are used, then manufacturing is simple and pressure loss is low, but thermal gradients cause stress and low-cycle fatigue
Solution Approach 1:
The patent applies local quality by adding protrusions only to specific regions of the conduit surface where heat transfer enhancement is needed. The protrusions are distributed in patterns (e.g., helical, axial, or circumferential arrangements) rather than uniformly across the entire surface, allowing localized thermal management while preserving smooth sections for structural integrity and low pressure drop.
Solution Approach 2:
The patent transitions from a two-dimensional smooth surface to a three-dimensional textured surface by adding protrusions with specific heights, diameters, and spatial distributions. This dimensional change creates additional surface area and thermal pathways without significantly increasing pressure loss, as the protrusions are optimized to minimize flow disruption.
2Temperature
If protrusion configuration is added to enhance heat transfer, then thermal response rate improves, but pressure loss increases
Solution Approach 1:
The patent optimizes multiple parameters of the protrusions including height (0.002-0.5 inches), diameter (0.007-2.9 inches), spacing patterns, and distribution densities. By carefully selecting these parameters, the design achieves enhanced heat transfer while minimizing pressure loss. The protrusion geometry is tuned to create beneficial flow patterns that improve thermal response without excessive energy penalty.
Solution Approach 2:
The patent applies partial action by implementing protrusions only in specific sections or patterns rather than covering the entire conduit surface. This selective application provides sufficient thermal enhancement to meet performance requirements while reducing the overall pressure loss that would result from complete surface coverage. The protrusion density and distribution are optimized to achieve the minimum necessary thermal improvement.
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 protrusion configuration enhances the thermal response rate and durability of conduits, reducing stress and improving the performance of the turbine engine by effectively managing thermal gradients.
Implementation Method 1
the protrusion configuration acts as a heat transfer surface to reduce thermal gradients
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
A turbine engine (20) including one or more conduits (204, 206, 208, 210, 212) is disclosed herein. At least one conduit (206) of the turbine engine (20) includes a first end coupled to the turbine engine (20), a second end, and a body (206c) extending from the first end to the second end, the body (206c) including an interior surface and an exterior surface, wherein at least one of the interior surface or the exterior surface includes a protrusion configuration (301).