Reverse Flow Combustor Sleeve Cooling
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Solution Overview
Problem
Gas turbine engines face challenges in cooling their combustor components due to increased operating temperatures, particularly in configurations with limited axial space, where traditional combustors may not fit and require additional cooling features.
Innovation Solution
A reverse flow combustor assembly with a combustor liner featuring an axial combustion portion and a curved transition portion, along with a sleeve that circumscribes the liner to create an annular cavity with cooling channels, providing impingement cooling and differential pressure zones to optimize cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of stationary object
If a reverse flow combustor is used to reduce surface area, then cooling requirements are reduced, but the combustor may not fit in limited axial space between compressor and HPT
Solution Approach 1:
The patent applies nesting by placing the combustor liner inside the impingement sleeve, creating a compact dual-component structure. The liner is positioned within the sleeve's internal cavity, allowing both components to occupy overlapping spatial volumes and reducing the overall axial footprint of the combustor assembly while maintaining both combustion and cooling functions.
Solution Approach 2:
The patent transitions from traditional axial flow configuration to reverse flow configuration, changing the flow direction dimension. The combustor liner features a curved transition portion that redirects flow from axial to radial direction, enabling the combustor to fit within limited axial space while maintaining effective cooling surface area through the reverse flow path.
2Reliability
If cooling channels are added to the combustor liner, then thermal distress is reduced, but the structural integrity and manufacturing complexity increase
Solution Approach 1:
The patent segments the cooling function into two distinct systems: cooling channels within the combustor liner and separate impingement cooling channels in the sleeve. This segmentation allows each component to be optimized independently for its specific cooling function, simplifying manufacturing while providing comprehensive thermal protection through multiple cooling mechanisms working in parallel.
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 solution effectively reduces thermal distress such as burnthrough, cracking, and damage to the combustor liner by providing comprehensive cooling, enabling efficient operation in space-constrained environments.
Implementation Method 1
a first plurality of cooling channels defined between the inner and outer surfaces
Implementation Method 2
The sleeve includes a second plurality of cooling channels defined therethrough that are configured to channel a fluid against the combustor liner outer surface
Data Source
AI summary
A combustor assembly for use in a gas turbine engine includes a combustor liner that defines a combustion chamber and includes an axial combustion portion and a curved transition portion. The combustion liner also includes an inner surface and an outer surface and a first plurality of cooling channels defined between the inner and outer surfaces. The combustor assembly also includes a sleeve substantially circumscribing the combustor liner such that an annular cavity is defined between the combustor liner and the sleeve. The sleeve includes a second plurality of cooling channels defined therethrough that are configured to channel a fluid against the combustor liner outer surface.