Single Cavity Trapped Vortex Combustor with CMC Liners
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Solution Overview
Problem
Conventional combustion sections in propulsion systems face challenges in burning fuels of varying caloric values while reducing emissions and maintaining combustion stability across different fuel/air ratios, airflow rates, and inlet pressures, while also requiring reduced dimensions and improved durability.
Innovation Solution
A single cavity trapped vortex combustor assembly is designed with an annular inner and outer liner, a combustor dome, and a chute member to generate a vortex within the combustion chamber, allowing for efficient fuel/air mixing and reduced dimensions, while being more versatile in placement and easier to manufacture.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional combustion sections are used, then combustion stability can be maintained, but the ability to burn fuels of varying caloric values and reduce emissions is limited
Solution Approach 1:
The combustion chamber is divided into multiple cavities (primary cavity and secondary cavity) with distinct functions. The primary cavity handles fuel injection and initial combustion, while the secondary cavity provides a mixing zone and flame stabilization area. This segmentation allows the system to accommodate varying fuel types and caloric values while maintaining combustion stability through specialized zones.
Solution Approach 2:
Different regions of the combustion chamber are designed with specific properties: the primary cavity has features optimized for fuel injection and ignition, while the secondary cavity has characteristics suited for mixing and flame stabilization. The trap vortex geometry creates localized high-energy regions that promote stable combustion across different fuel types.
2Productivity
If conventional combustion sections are used, then combustion function is provided, but axial and radial dimensions are larger than necessary
Solution Approach 1:
The combustion cavities are nested within a compact trap vortex geometry, where the primary cavity is positioned within the secondary cavity structure. This nested arrangement maximizes the use of available space, achieving high heat release efficiency within a reduced axial and radial envelope, thereby resolving the contradiction between productivity and compact dimensions.
Solution Approach 2:
The trap vortex design utilizes three-dimensional flow patterns and vertical stacking of cavities to achieve efficient combustion in a compact footprint. By transitioning from conventional two-dimensional combustion layouts to a three-dimensional vortex-based architecture, the system achieves high heat release in a smaller overall dimension.
3Ease of manufacture
If conventional combustion sections are used, then combustion is achieved, but manufacturing complexity and part quantities are higher
Solution Approach 1:
Multiple combustion chamber components are merged into an integrated trap vortex assembly with fewer discrete parts. The primary and secondary cavities are formed as unified structures with the vortex geometry, reducing the number of separate components that need to be manufactured and assembled while maintaining the complex combustion performance required for reliable operation.
4Adaptability or versatility
If conventional combustion sections are used, then combustion function is provided, but system packaging flexibility is reduced
Solution Approach 1:
The trap vortex combustor design provides a universal configuration that can be adapted to various system architectures and placement locations. The compact, self-contained geometry with integrated cavities serves multiple functions (fuel mixing, combustion, flame stabilization) within a single unit, enabling flexible packaging and installation in different system configurations without requiring complex external support structures.
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 improves the performance and durability of propulsion systems by enabling high heat release in a compact form, allowing for a wide range of fuel/air ratios, reducing emissions, and providing better packaging and maintainability, leading to a lighter and more versatile combustor assembly.
Implementation Method 1
a chute member positioned within the airflow opening to define an air chute for providing a flow of air to the annular cavity... generate a vortex within the combustion chamber
Data Source
AI summary
Combustor assemblies and methods for assembling combustor assemblies are provided. For example, a combustor assembly comprises an annular inner liner and an annular outer linear, each extending generally along an axial direction. The outer liner includes an outer flange extending forward from its upstream end. The combustor assembly also comprises a combustor dome extending between an inner liner upstream end and the outer liner upstream end and including an inner flange extending forward from a radially outermost end of the combustor dome. The inner liner, outer liner, and combustor dome define a combustion chamber therebetween, and the combustor dome and a portion of the outer liner together define an annular cavity of the combustion chamber. The inner and outer flanges define an airflow opening therebetween, and a chute member is positioned within the airflow opening to define an air chute for providing a flow of air to the annular cavity.