Stator Blade Group Radial Interlocking for Compact Turbomachinery
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Solution Overview
Problem
The aerodynamic load capacity and efficiency of turbomachinery are limited by boundary layer growth and detachment near hub and casing walls, with existing solutions failing to effectively manage high aerodynamic loads and boundary layer separation in stator blade row groups, particularly due to structural challenges in fixing blades in compact designs.
Innovation Solution
A blade row group arrangement where adjacent member blade rows are fixed both meridionally and circumferentially, with blades of one row protruding beyond their base to connect with the other row, allowing for a compact and structurally stable attachment to main flow path boundaries, enabling small axial distances between blade rows and optional meridional engagement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If multiple blade rows are arranged with close axial spacing to improve aerodynamic performance, then productivity and efficiency are improved, but the difficulty of fixing blades to hub and housing increases significantly
Solution Approach 1:
The patent merges the fixing functions of multiple blade rows by having blade profiles extend beyond their bases to project onto adjacent bases. This integration creates a unified structural system where blades serve both aerodynamic and structural attachment functions, eliminating the need for separate fixing mechanisms for each blade row.
Solution Approach 2:
The patent implements a nested structure where blade profiles are embedded into adjacent bases. Specifically, blade profiles extend beyond their bases and are received within or projected onto the bases of adjacent blade rows, creating an interlocked nested arrangement that provides structural stability while maintaining compact axial spacing.
2Stability of the object's composition
If blade rows are fixed firmly to hub and housing to improve structural stability, then strength and reliability are improved, but the axial spacing between blade rows increases, reducing compactness
Solution Approach 1:
The patent transitions from traditional axial fixing methods to a radial/dimensional approach where blade profiles extend radially beyond their bases to engage with adjacent bases. This dimensional change allows structural stability to be achieved through radial interlocking rather than increased axial spacing.
Solution Approach 2:
The structural stability function is merged into the blade profiles themselves, which serve dual purposes: aerodynamic flow guidance and structural attachment. The blade profiles extend beyond bases to provide fixing functionality, eliminating the need for separate structural support elements that would increase axial spacing.
3Ease of manufacture
If conventional fixing methods are used for multiple blade rows, then ease of manufacture is maintained, but boundary layer separation occurs at hub and casing contours under high aerodynamic loads
Solution Approach 1:
The patent applies local quality by having blade profiles extend beyond their bases specifically at critical locations near hub and casing contours. This localized extension provides enhanced structural support and flow control precisely where boundary layer separation is most problematic, without requiring changes to the entire blade row structure.
Data Source
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AI summary
The invention relates to a blade array group that can be arranged in a main flow path of a turbomachine and consists of N adjacent member blade arrays that are fixed relative to each other in both the meridional direction (m) and the circumferential direction (u). A front member blade array with front blades (i) having leading edge VK(i) and trailing edge HK(i) and a rear member blade array with rear blades (i+1) having leading edge VK(i+1) and trailing edge HK(i+1) are provided, and the blade array group has two main flow path boundaries (HB).It is provided that the blade profile of the blades (i, i+1) of the member blade rows is firmly connected to a base (B(i), B(i+1)) at at least one of the two main flow path boundaries (HB), wherein at least one blade profile of a blade (i, i+1) of one of the two member blade rows extends beyond its base (B(i), B(i+1)) at least adjacent to the main flow path boundary (HB) and projects onto the base (B(i), B(i+1)) of at least one blade (i, i+1) of the other of the two member blade rows.