Gas Turbine Blade Ring Cooling Flow Passage Design
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Solution Overview
Problem
Gas turbines face challenges in preventing temperature distribution in the radial direction of blade ring parts, which can lead to inefficiencies and potential damage due to uneven heating.
Innovation Solution
The implementation of a gas turbine design featuring multiple cooling flow passages aligned in the axial direction, including first and second cooling flow passages on the outer and inner radial sides, respectively, connected by return flow passages, along with communication flow passages for efficient cooling medium circulation, and a bypass flow passage for managing temperature during start-up.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single cooling flow passage is used in the blade ring part, then the structure is simple, but temperature distribution occurs in the radial direction
Solution Approach 1:
The cooling flow passage is segmented into multiple passages (first cooling flow passages and second cooling flow passages) positioned at different radial locations. This segmentation allows independent cooling zones that prevent temperature distribution in the radial direction while maintaining structural manageability.
Solution Approach 2:
The cooling system transitions from a single axial passage to a multi-dimensional network including axial passages and radial return passages. This dimensional expansion enables cooling medium circulation across both axial and radial directions, effectively addressing temperature distribution issues.
2Temperature
If multiple cooling flow passages are added to prevent temperature distribution, then temperature uniformity improves, but device complexity increases
Solution Approach 1:
Multiple cooling functions are merged into an integrated system where first cooling flow passages, second cooling flow passages, and return flow passages work together as a unified cooling network. This merging achieves comprehensive radial cooling while consolidating the overall structure for efficient medium circulation.
Solution Approach 2:
The cooling flow passage system performs multiple functions: cooling the outer radial surface, cooling the inner radial surface, and enabling medium return circulation. This multi-functionality reduces the need for separate dedicated passages for each function, managing overall system complexity.
3Temperature
If cooling passages are extended to cover the entire radial length, then cooling coverage improves, but manufacturing difficulty increases
Solution Approach 1:
The radial cooling coverage is achieved through segmented passages (first and second cooling flow passages) positioned at specific radial locations rather than a single continuous radial passage. This segmentation simplifies manufacturing by allowing standard drilling and tapping operations at discrete locations.
Solution Approach 2:
Instead of creating complex radial-through passages, the design uses axial passages combined with radial return passages to achieve radial cooling coverage. This dimensional approach simplifies manufacturing by using primarily axial drilling operations with simpler radial connections.
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
This design effectively prevents temperature distribution in the radial direction of blade ring parts by ensuring cooling occurs at multiple points, enhancing the cooling of inner peripheral surfaces and maintaining efficient operation by managing temperature gradients.
Implementation Method 1
a plurality of first cooling flow passages that are disposed on an outer side in the radial direction centering on the rotation axis, extend in the axial direction... a plurality of second cooling flow passages that are disposed on an inner side in the radial direction... and a return flow passage that connects end parts of each of the first cooling flow passages and the second cooling flow passages
Data Source
AI summary
In a gas turbine, a plurality of blade ring parts each include a plurality of first cooling flow passages, a plurality of second cooling flow passages, and a return flow passage. The first cooling flow passages are disposed on the outer side in a radial direction centering on a rotation axis, extend in an axial direction, and are disposed aligned in an axial rotation direction. The second cooling flow passages are disposed on an inner side in the radial direction with respect to the first cooling flow passages, extend in the axial direction, and are disposed aligned in the axial rotation direction. The return flow passage connects end parts of each of the first cooling flow passages and the second cooling flow passages on the same side in the axial direction with each other.