Turbine Shroud Plenum Cooling for High-Temperature Strength
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Solution Overview
Problem
Turbine shrouds in turbomachines, such as gas turbine systems, weaken due to stress from rotational forces and exposure to high temperatures, necessitating efficient cooling to extend component life.
Innovation Solution
A turbine shroud design featuring a body with a cooling circuit that includes an inlet passage, outlet passage, and a plenum system for fluid communication, along with an impingement panel to direct cooling air effectively, enhancing heat dissipation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If turbine shrouds are exposed to high temperatures for extended periods, then operational efficiency is improved, but the shrouds weaken due to thermal stress and rotational forces
Solution Approach 1:
The cooling circuit is designed to pre-cool the shroud structure before it is subjected to high thermal stress during operation. Cooling air is supplied through inlet passages to plenums that distribute coolant to multiple cooling zones in advance, preventing thermal degradation before it occurs.
Solution Approach 2:
The shroud is divided into multiple structural members with integrated cooling circuits. Each structural member has its own cooling passages and plenums, allowing independent cooling control. This segmentation enables targeted cooling of specific high-stress zones without requiring the entire shroud to be cooled uniformly.
2Temperature
If a cooling circuit is integrated into the turbine shroud, then heat dissipation is improved, but the device complexity increases
Solution Approach 1:
The cooling circuit is merged with the structural members of the shroud itself. Cooling passages are integrated directly into the structural members, and plenums are formed as part of the shroud's internal structure. This combination eliminates the need for separate cooling components, reducing overall system complexity while maintaining effective heat dissipation.
Solution Approach 2:
The structural members of the shroud serve dual functions: providing mechanical support and housing cooling circuits. The same components that maintain structural integrity also facilitate heat dissipation through integrated cooling passages and plenums, eliminating the need for dedicated cooling structures.
3Temperature
If multiple plenums and passages are added to the cooling circuit, then cooling effectiveness is improved, but manufacturing precision requirements increase
Solution Approach 1:
The cooling circuit design incorporates variable parameters such as adjustable plenum volumes and passage cross-sections to optimize cooling effectiveness. By changing geometric parameters rather than adding complex multi-component assemblies, the design achieves superior cooling while reducing the number of precision-critical interfaces.
Solution Approach 2:
Multiple plenums are nested within the structural members of the shroud, with cooling passages routed through the same structural components. This nesting approach allows multiple cooling zones to be served by a unified structure, reducing the need for precise alignment between separate components and simplifying manufacturing.
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 effectively cools the turbine shroud, reducing stress and extending its operational life by maintaining structural integrity under high-temperature conditions.
Implementation Method 1
a cooling circuit within the body and in fluid communication with a cooling chamber defined radially outward of the body, the cooling circuit including: an inlet passage extending through the structural member of the body, and an outlet passage fluidly coupled to the inlet passage and extending through an external surface of the body
Data Source
Figure 1~2A
Figure 2B
Figure 3A
AI summary
A turbine shroud (100) includes a body (102) with a structural member thereon. The body is coupled to a turbomachine casing. A cooling circuit (106) within the body is in fluid communication with a cooling chamber (111) adjacent the body. The cooling circuit includes an inlet passage (108) extending through the structural member of the body, and an outlet passage (110) fluidly coupled to the inlet passage and extending through an external surface of the body. A turbomachine includes a blade structure configured to rotate about a rotation axis of a rotor and the turbine shroud oriented toward the blade structure and coupled to the turbomachine casing.