Non-periodic sidewall contouring for turbo engine blade assembly
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Solution Overview
Problem
Conventional turbomachine blade arrangements have limitations in optimizing structural-mechanical and flow-mechanical boundary conditions due to periodic sidewall contouring, which restricts the ability to tailor blade designs for specific positions within a blade cluster, leading to suboptimal performance.
Innovation Solution
The blade arrangement features non-periodic sidewall contouring with varying transition areas and intermediate sections between blades, allowing for customized design to address structural and flow-mechanical conditions, such as differing fillet lengths and radial extensions, to enhance performance and sealing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If periodic sidewall contouring is used in conventional blade arrangements, then manufacturing simplicity is maintained, but the ability to optimize structural-mechanical and flow-mechanical boundary conditions for specific blade positions is restricted
Solution Approach 1:
The patent applies local quality by giving different sidewall sections between adjacent blades distinct contourings tailored to their specific positions within the blade cluster. Each sidewall section can be optimized for its local structural-mechanical and flow-mechanical conditions, such as varying fillet lengths and radial extensions at different locations, rather than using a uniform periodic pattern throughout.
Solution Approach 2:
The sidewall is segmented into multiple discrete sections, each corresponding to the space between adjacent blades. This segmentation allows each section to be independently designed and optimized with its own contouring characteristics, enabling customization for specific blade positions while maintaining overall sidewall integrity.
2Reliability
If non-periodic sidewall contouring with varying transition areas is implemented, then individual optimization of blade clusters is enabled, but manufacturing complexity increases
Solution Approach 1:
The patent implements local quality by varying the contouring of individual sidewall sections to address specific structural integrity requirements at different blade positions. For example, sidewall sections near blade cluster edges can have different fillet lengths compared to those at central positions, optimizing stress distribution and structural strength where needed most.
3Productivity
If customized sidewall sections with different fillet lengths and radial extensions are used, then flow-mechanical performance is enhanced, but the number of different components increases
Solution Approach 1:
The patent applies local quality by optimizing the contouring of each sidewall section according to its specific flow-mechanical requirements. Sidewall sections can have varying fillet lengths and radial extensions to control flow patterns, reduce turbulence, and improve performance at different locations within the blade cluster, rather than using a uniform design throughout.
Data Source
Figure 1~2
Figure 3
AI summary
The arrangement has an adjacent vane cluster with intermediate regions (10.1,20.1,30.1,40.1) and transition regions(10P,10S,20P,20S,30P,30S,40P,40S) in circumferential direction and a blade assembly with two circumferentially adjacent blades (1-4) that are connected to the side wall. The side wall portions are provided between pressure side of a blade and suction side of adjacent blade in the circumferential direction. The side wall portions are grooved. The intermediate regions are provided between the transition regions (10P,20P,30P,40P) and (10S,20S,30S,40S). Independent claims are included for the following: (1) a gas turbine; and (2) a method for manufacturing blade arrangement.