Turbomachine Combustor Vortex Modification System
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Solution Overview
Problem
The creation of vortices in turbomachine combustor assemblies for enhanced heat transfer often results in undesirable high-frequency noise, which current designs fail to effectively mitigate without compromising heat transfer efficiency.
Innovation Solution
Incorporating a vortex modification system with strategically positioned jet members or varying turbulator configurations to disrupt the vortices, including jet members with different cross-sections and turbulators of varying heights and spacings, to reduce noise while maintaining heat transfer effectiveness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If turbulator members are arranged in the passage to create flow vortices, then heat transfer in the combustor body is enhanced, but high-frequency noise is generated
Solution Approach 1:
A vortex modification system is introduced as an intermediary component between the turbulator members and the combustion chamber. This system includes a first passage and a second passage that intercept and modify the vortices generated by the turbulators, preventing them from directly entering the combustion chamber and generating noise, while still allowing the heat transfer benefits to be realized.
Solution Approach 2:
The flow path is segmented into multiple passages: a first passage where vortices are generated by turbulators, a second passage where vortices are modified and intercepted, and a combustion chamber. This segmentation allows the vortices to be created and controlled separately from the combustion process, enabling heat transfer enhancement without direct noise generation in the combustion zone.
2Temperature
If compressor discharge air is channeled along the combustor liner toward the venturi for cooling, then surface cooling is improved, but the complexity of the air channeling system increases
Solution Approach 1:
The combustor liner is designed to serve multiple functions simultaneously: it acts as a structural component, a cooling air passage, and a vortex modification system. The liner includes integrated cooling air passages that channel compressor discharge air along its length, and it incorporates vortex modification features that intercept and modify vortices, eliminating the need for separate dedicated components for each function.
Solution Approach 2:
The cooling air channeling function is merged with the vortex modification system within the combustor liner structure. The liner integrates both the cooling air passages and the vortex modification passages into a single unified component, reducing the number of separate parts and simplifying the overall system architecture while maintaining both cooling and vortex control functions.
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 proposed solution effectively mitigates undesirable noise in turbomachine combustor assemblies while preserving or enhancing heat transfer characteristics, thereby improving operational efficiency and reducing noise pollution.
Implementation Method 1
The turbulator members create flow vortices that enhance heat transfer in the combustor body
Implementation Method 2
The turbulator members create flow vortices that enhance heat transfer in the combustor body
Implementation Method 3
The jet members disrupt the vortices created by the turbulators to mitigate undesirable noise
Implementation Method 4
A portion of the compressor discharge air is directed onto internal surfaces of the venturi for cooling
Implementation Method 5
gas turbine engines combust a fuel/air mixture that releases heat energy to form a high temperature gas stream
Data Source
Figure 1
Figure 2
Figure 3~5
AI summary
A turbomachine (2) combustor assembly (20) includes a combustor body (34), and a combustor liner (43) arranged within the combustor body (34) and defining a combustion chamber (48). The combustor liner (43) includes a venturi portion (50) arranged within the combustion chamber (48). A fluid passage is defined between the combustor body (34) and the combustor liner (43), and at least one turbulator is arranged in the fluid passage. The at least one turbulator is configured and disposed to create vortices in the fluid passage. A vortex modification system is arranged at the fluid passage and is configured and disposed to disrupt the vortices in the fluid passage.