Slot Cooled Combustor Double-Wall Heat Shield Panels
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Solution Overview
Problem
Gas turbine engine combustors face significant heat loads that can lead to oxidation, cracking, and thermal stresses in heat shield panels, necessitating effective cooling solutions to protect these structures.
Innovation Solution
The combustor design incorporates a double-wall system with ceramic matrix composite panels and overlapping air slots to channel cooling air from the compressor, providing impingement and convective cooling to manage heat loads and reduce thermal stresses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the combustor is configured to burn fuel in a minimum volume, then the combustion efficiency is improved, but the heat load on the combustor structure increases substantially
Solution Approach 1:
The combustor structure is segmented into multiple heat shield panels that can be independently cooled. Each panel is a separate component that can be cooled individually through the double-wall system with air slots, allowing distributed heat management across the combustion chamber while maintaining high combustion efficiency in the minimized volume.
Solution Approach 2:
A double-wall cooling system with air slots is introduced as an intermediary between the combustion chamber and the heat shield panels. Cool air from the compressor is channeled through passages in the double-wall structure and discharged through air slots onto the panel surfaces, creating a cooling barrier that protects the structure from direct exposure to high temperatures while maintaining compact combustion volume.
2Reliability
If special consideration is given to the cooling of heat shield panels, then the structural integrity is improved, but the device complexity increases
Solution Approach 1:
The double-wall structure serves multiple functions simultaneously: it provides the structural framework of the combustor, creates cooling passages for air flow, and forms the basis for the heat shield panel mounting system. The air slots serve dual purposes as both structural features and cooling discharge points, reducing the need for separate cooling components and simplifying the overall system while maintaining structural integrity.
Solution Approach 2:
The cooling system utilizes changes in air parameters (temperature, pressure, velocity) as it flows through the double-wall passages and discharges through air slots. The air is cooled and pressurized in the passages, then accelerated through the slots to create effective impingement cooling on the panels. This parameter transformation approach provides effective cooling without requiring complex active control systems.
3Temperature
If air slots are used to channel cooling air, then the cooling effectiveness is improved, but the manufacturing precision requirements increase
Solution Approach 1:
The cooling system is designed with local quality variations where different regions of the heat shield panels receive different cooling intensities. Air slots are positioned and sized to provide appropriate cooling density in different areas based on local heat load requirements. This localized approach allows for effective cooling while accommodating reasonable manufacturing tolerances, as not all regions require the same level of precision.
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 effectively reduces thermal stresses and maintains consistent airflow for cooling, even at high temperatures, by using ceramic matrix composites and strategic air slot configurations, ensuring the structural integrity and efficiency of the combustor.
Implementation Method 1
The inward wall and the inward shell define an inward air passageway therebetween, the inward air passageway being fluidly connected to the inward air slot
Implementation Method 2
providing impingement and convective cooling to manage heat loads and reduce thermal stresses
Data Source
Figure 1
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AI summary
A combustor (300) for use in a gas turbine engine (20) comprising: an outward shell (710); an inward shell (720) located radially inward of the outward shell (710), the inward shell (720) and the outward shell (710) defining a combustion chamber (302) therebetween; an aft outward panel (730) located proximate the outward shell (710), the aft outward panel (730) extending from an aft end (704) of the combustion chamber (302) to an outward panel joint (792); an aft inward panel (740) located proximate the inward shell (720), the aft inward panel (740) extending from the aft end (704) of the combustion chamber (302) to an inward panel joint (794); and a forward panel (750) located proximate a forward end (702) of the combustion chamber (302), the forward panel (750) comprising: an outward wall (760) located proximate the outward shell (710); an inward wall (770) located proximate the inward shell (720); and a forward wall (780) located proximate the forward end (702) of the combustion chamber (302), the forward wall (780) extending from the inward wall (770) to the outward wall (760).