Tangential Radial Inflow Combustor Eliminates Guide Vanes
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Solution Overview
Problem
Existing gas turbine combustors experience inefficiencies due to the use of guide vanes that redirect air and combustion gas flows, leading to increased operating inefficiencies.
Innovation Solution
A tangential radial inflow combustor design with an inner and outer combustion liner, featuring an inlet assembly with multiple cavity air tubes and a fuel injector, which induces bulk swirl airflow and maintains high angular momentum, enhancing flame stabilization and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If guide vanes are used to redirect air and combustion gas flows, then flow angle requirements are satisfied, but operating inefficiencies increase
Solution Approach 1:
The patent removes the guide vane component from the combustor system entirely. Instead of using guide vanes to redirect flows, the invention uses a tangential radial inflow combustor design where the airflow naturally follows the combustor geometry, eliminating the need for flow redirection components and their associated energy losses.
Solution Approach 2:
Rather than using guide vanes to actively redirect and change the flow direction, the invention inverts the approach by designing the combustor geometry itself to guide the flow naturally along the desired path through tangential radial inflow, allowing the flow to follow the geometry rather than being forced to change direction.
2Ease of operation
If guide vanes redirect flows, then bulk swirl is removed or increased, but device complexity increases
Solution Approach 1:
The patent eliminates the complex guide vane assemblies from the combustor design. The tangential radial inflow combustor achieves bulk swirl control through its geometric design and airflow pattern rather than through additional mechanical components, thereby reducing device complexity.
Solution Approach 2:
The combustor geometry itself performs multiple functions: it guides the airflow, controls the bulk swirl, and defines the combustion chamber, eliminating the need for separate guide vane components that would add complexity to the system.
3Reliability
If cavity air tubes are arranged with non-uniform spacing, then flame stabilization is enhanced, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies non-uniform spacing of cavity air tubes specifically in regions where flame stabilization is most critical, rather than applying uniform spacing throughout. This localized optimization enhances flame stabilization while allowing for standard manufacturing tolerances in less critical areas.
Solution Approach 2:
The invention varies the spacing parameter of cavity air tubes along the axial direction to optimize combustion performance. By changing the spacing parameter locally rather than maintaining a constant value, the design achieves better flame stabilization without requiring excessively tight manufacturing tolerances across the entire 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 design improves flame stabilization and mixing within the combustor, maintaining high g-range and reducing operating inefficiencies by optimizing airflow and fuel injection patterns.
Implementation Method 1
The compressor section generally provides compressed air to the combustor
Implementation Method 2
the compressed air is mixed with fuel and combusted to generate combustion gases
Data Source
Figure 1~2
Figure 3
Figure 4~5
AI summary
A combustor (100) for a turbine engine includes an inner combustion liner (104) and an outer combustion liner (106) together defining at least in part an interior (108). The interior includes a combustion chamber (110) and a main portion (112). The combustor also includes an inlet combustion liner (116) at least partially defining the combustion chamber of the interior and including an inlet assembly (118). The inlet assembly includes at least two cavity air tubes (128) arranged along the axial direction (A), each cavity air tube extending between an inlet and an outlet, the outlet of each cavity air tube in airflow communication with the combustion chamber for providing the combustion chamber with a flow of air (120).