Nozzle Guide Vane Endwall Plug Cooling
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Solution Overview
Problem
Current cooling systems for gas turbine engines face challenges in effectively managing high temperatures within the turbine section, leading to potential failures of components like sensor probes and plugs due to non-uniform heating and thermal stress.
Innovation Solution
A cooling system is implemented that uses a dual-walled nozzle guide vane endwall assembly with inner passageways to direct coolant air flows, providing impingement and film cooling to the plug or probe, which reduces temperature gradients and overall temperature, thereby enhancing the components' durability and reducing the risk of failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional cooling systems are used in gas turbine engines, then the structure is simple, but the components are susceptible to overheating and thermal stress failure
Solution Approach 1:
The cooling system is segmented into multiple independent cooling circuits: a first cooling circuit that directs coolant to a first region of the plug, and a second cooling circuit that directs coolant to a second region of the plug. This segmentation allows different regions to be cooled independently, reducing thermal stress and improving reliability without requiring a completely complex new system design.
Solution Approach 2:
Different regions of the plug receive cooling tailored to their specific thermal requirements. The first cooling circuit targets the first region while the second cooling circuit targets the second region, allowing each region to maintain optimal temperature independently. This local quality approach prevents uniform overheating and reduces thermal stress concentrations.
2Temperature
If uniform cooling is applied to the plug, then thermal stress is reduced, but temperature gradients cannot be optimized for different regions
Solution Approach 1:
The plug cooling system is divided into multiple independent cooling circuits, each serving specific regions. The first cooling circuit provides coolant to the first region through first cooling passages, while the second cooling circuit provides coolant to the second region through second cooling passages. This segmentation enables both temperature uniformity within regions and adaptability across different regions.
Solution Approach 2:
Each region of the plug is equipped with dedicated cooling passages and coolant supply, allowing the cooling characteristics to be optimized for local thermal conditions. The first cooling passages and second cooling passages can be designed with different geometries, lengths, and coolant flow rates to match the specific thermal requirements of each region, achieving both uniformity and adaptability.
3Reliability
If the plug is fully sealed in the borescope port, then sealing is improved, but cooling fluid access is restricted
Solution Approach 1:
The sealing structure is segmented to include both sealed portions and unsealed portions. The plug seals against the borescope port to prevent hot gas leakage, while simultaneously incorporating cooling passages that allow cooling fluid to flow through the plug. This segmentation enables the plug to maintain sealing reliability while permitting necessary cooling fluid access through dedicated passages.
Solution Approach 2:
The cooling passages act as intermediaries that allow cooling fluid to pass through the sealed plug structure. The plug serves as both a seal and a conduit, with the cooling passages providing a pathway for cooling fluid while the outer surface maintains the seal against the borescope port. This intermediary approach resolves the conflict between sealing and cooling fluid access.
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 cooling system effectively reduces the risk of overheating and subsequent failure of the plug or probe by maintaining more uniform temperatures and minimizing thermal stress, thus extending the service life and ensuring reliable operation in hostile turbine environments.
Implementation Method 1
providing impingement and film cooling to the plug or probe, which reduces temperature gradients and overall temperature
Implementation Method 2
providing impingement and film cooling to the plug or probe, which reduces temperature gradients and overall temperature
Data Source
AI summary
A cooling system includes a nozzle guide vane endwall. The nozzle guide vane endwall includes a first wall and a second wall. The first wall includes a first opening that extends completely through the first wall into a primary flow path of a high-pressure turbine. The second wall includes a second opening and a third opening that extend completely through the second wall into an inner passageway of the nozzle guide vane endwall. The inner passageway is configured to direct a cooling fluid to the first opening and/or the second opening via at least the third opening. The first and second opening are configured to receive a plug or a probe.