Combustor Tongue Joint Cooling to Prevent Thermal Hotspots
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Solution Overview
Problem
Existing gas turbine engine joints, particularly in high-heat areas like the combustor, face challenges with thermal insulation and leakage, leading to localized hotspots and reduced durability due to inadequate cooling.
Innovation Solution
Incorporating a cooling channel between mating combustor panels with radial intrusions and leakage paths to facilitate airflow for cooling, using channels and additional cooling holes to minimize thermal stress and enhance joint durability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a tongue joint is used to connect combustor panels, then the joint provides structural strength and stiffness to maintain part to part contact, but the joint experiences thermal insulation and inadequate cooling leading to localized hotspots
Solution Approach 1:
The joint structure is segmented into multiple functional zones: a tongue portion extending from the first panel, a groove portion in the second panel, and integrated cooling channels within both the tongue and groove portions. This segmentation allows the joint to simultaneously provide structural connection and thermal management through dedicated cooling passages that receive coolant flow to reduce localized hotspots.
Solution Approach 2:
Coolant acts as an intermediary substance introduced into the cooling channels formed by the tongue and groove portions. The coolant absorbs heat from the joint interface through thermal conduction and convection, preventing excessive temperature buildup while maintaining the structural integrity of the tongue joint connection.
2Temperature
If cooling channels are added to the tongue joint, then thermal hotspots are reduced, but the device complexity increases
Solution Approach 1:
The cooling channels are merged into the existing tongue and groove joint structure rather than being added as separate components. The cooling channels are formed by shaping the tongue portion and groove portion themselves, integrating thermal management functionality into the structural connection elements and avoiding additional device complexity.
Solution Approach 2:
The tongue and groove portions serve multiple functions: they provide structural connection between panels and simultaneously form cooling channels for thermal management. This multi-functionality eliminates the need for separate cooling components, reducing overall device complexity while achieving effective heat dissipation.
3Temperature
If radial intrusions are created for cooling channels, then cooling effectiveness is improved, but manufacturing precision requirements increase
Solution Approach 1:
The cooling channels are preliminarily formed as integral features of the tongue and groove portions during the manufacturing of these components. By pre-forming the channels within the molded or machined tongue and groove structures, the alignment and connectivity of cooling passages are established during manufacturing, reducing the need for post-assembly alignment operations and minimizing precision requirements for field assembly.
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 cooling design effectively reduces thermal hotspots and enhances the structural integrity and durability of the joint by providing efficient cooling, thereby improving the performance and longevity of the engine components.
Implementation Method 1
a channel defined between a radially outer surface of the tongue and a radially inner surface of the combustor panel
Implementation Method 2
The cooling design effectively reduces thermal hotspots and enhances the structural integrity and durability of the joint by providing efficient cooling
Data Source
Figure 1
Figure 2A~7
AI summary
A gas turbine engine (20) including a core having a compressor section (24) fluidly connected to a combustor (56) via a primary flowpath and a turbine section (28) connected to the combustor (56) via the core flow path (C). An assembly is disposed within the gas turbine engine (20) and includes a first part (110) connected to a second part (120) via a radial stack joint. The first part (110) includes a radially inward facing surface (112) contacting a corresponding radially outward facing surface (126) of the second part (120). A fastener (130) protrudes through the first part (110) and the second part (120) and is configured to maintain the relative positions of the first part (110) and the second part (120). A channel (140) is disposed on at least one of the radially inward facing surfaces (112, 126) and is positioned between the fastener (130) and a circumferential edge of the first part (110). The channel (140) is connected to at least one cooling air source (150).