Turbine Scroll Assembly Cooling Passage Design
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Solution Overview
Problem
Existing gas turbine engines face challenges in efficiently regulating operating temperatures within and around the combustion section, with traditional cooling features often reducing engine efficiency and being difficult to manufacture, and not effective in all operating conditions.
Innovation Solution
A gas turbine engine design incorporating a turbine scroll assembly with a scroll cooling passage, where compressed air from the compressor section flows through the scroll cooling passage to cool the scroll and turbine rotor blade shroud, and the collector space, enhancing cooling efficiency without the need for effusion or impingement cooling holes, thereby improving manufacturability and control over the cooling process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling features are used to regulate operating temperature of combustion section components, then cooling effectiveness is improved, but engine efficiency deteriorates
Solution Approach 1:
The cooling system is segmented into multiple independent passages: a first cooling passage for the scroll and a second cooling passage for the rotor blade shroud. This segmentation allows optimized cooling flow distribution to different components, improving overall cooling effectiveness while minimizing energy loss by directing cooling air only where needed rather than using blanket cooling approaches.
2Temperature
If traditional cooling features with effusion or impingement cooling holes are used, then cooling effectiveness is improved, but manufacturing difficulty increases
Solution Approach 1:
The invention extracts and eliminates the complex effusion or impingement cooling holes from the design. Instead of drilling or forming holes through the scroll and shroud components, the patent uses smooth-walled cooling passages that route cooling air along the exterior surfaces of these components. This extraction of the problematic cooling feature simplifies manufacturing significantly while maintaining cooling effectiveness.
3Temperature
If traditional cooling features are used, then cooling capability is improved, but susceptibility to clogging or blockages increases
Solution Approach 1:
The cooling passages are designed with locally optimized characteristics: smooth walls without holes or protrusions in the flow path, adequate passage diameter throughout, and strategic placement of inlet and outlet ports. The first cooling passage has its inlet port positioned to receive cooling air directly from the compressor, and the second cooling passage receives cooling air from the first passage, creating a cascading cooling system with no dead zones where debris could accumulate and cause blockages.
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 provides improved cooling for the turbine scroll and rotor blade shroud, enhancing engine efficiency, manufacturability, and reducing the risk of clogging or blockages, while maintaining engine compactness and complexity.
Implementation Method 1
the compressor flow path is fluidly connected to the scroll cooling passage to direct flow from the compressor flow path along the scroll cooling passage to cool the scroll
Implementation Method 2
the scroll cooling passage is fluidly connected to the shroud cooling passage to direct flow from the scroll cooling passage along the shroud cooling passage to cool the turbine rotor blade shroud
Data Source
AI summary
A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.