Heat Shield Insert for Gas Turbine Combustor Hot Spots
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Solution Overview
Problem
Gas turbine combustor heat shield panels face durability issues due to local hot spots, which can cause stress and cracking, and conventional cooling methods may negatively impact emissions and profile.
Innovation Solution
An insert made of ceramic matrix composite or high temperature metal alloy is positioned between heat shield panels and the support shell at hot spots, providing thermal protection and minimizing stress through isothermal operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If more cooling air is used to combat hot spots, then heat shield panel durability is improved, but combustor emissions and profile are negatively affected
Solution Approach 1:
The patent applies local quality by placing inserts specifically at hot spot locations rather than uniformly cooling the entire heat shield panel. The insert is positioned adjacent to the support shell and heat shield panel at the identified hot spot, providing localized thermal protection only where needed. This selective approach protects durability at critical areas while minimizing the overall cooling air requirement, thus avoiding negative impacts on combustor emissions and profile.
Solution Approach 2:
The insert acts as an intermediary component between the support shell and the heat shield panel. It mediates the thermal environment at the hot spot by providing an additional thermal barrier that reduces the temperature exposure of the heat shield panel. This intermediary structure allows the system to maintain panel durability without requiring increased cooling air flow through the entire combustor, thereby preventing emissions deterioration.
2Weight of moving object
If heat shield panels are used instead of full hoop structures, then combustor weight is reduced, but durability at hot spots is compromised
Solution Approach 1:
The patent applies segmentation by dividing the heat shield structure into panels rather than using a continuous full hoop structure. This segmentation reduces overall combustor weight while maintaining structural integrity. The panels are strategically positioned and supported, with additional inserts at critical hot spot locations, allowing the segmented structure to achieve both weight reduction and localized durability enhancement.
Solution Approach 2:
The patent employs composite material strategy by combining the heat shield panel with an insert made of different material properties. The insert, positioned between the support shell and heat shield panel, is made of material suitable for withstanding high temperatures at hot spots. This composite approach allows the lighter heat shield panel to be used overall while compensating for durability concerns at specific locations through the insert.
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 insert reduces high temperature stress and cooling air usage, allowing more cooling air for emissions and profile control, thereby enhancing the durability and performance of the combustor.
Implementation Method 1
An insert made of ceramic matrix composite or high temperature metal alloy is positioned between heat shield panels and the support shell at hot spots, providing thermal protection
Implementation Method 2
providing thermal protection and minimizing stress through isothermal operation
Data Source
AI summary
A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert at least partially between opposed surfaces of the support shell and the heat shield panel, the insert exposed to a combustion chamber, and the insert being flush with a hot side of the heat shield.