Compressor Vane Neck Thickness Ratio for Fatigue Resistance
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing vane designs in compressors suffer from short lifespan due to thermomechanical fatigue, primarily because of their thin leading edges, which reduces their strength, and modifying the design to increase thickness at the leading edge compromises compressor performance.
Innovation Solution
A vane arrangement with a specific geometry, characterized by a neck thickness to deck thickness ratio (tb) of at least 0.21, and a chord length to leading edge angle product (t(l cos ∅) within the range of 11 to 25, which enhances durability and aerodynamic performance, thereby improving thermomechanical fatigue resistance without significantly reducing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the leading edge thickness of the vane is increased to improve strength and durability, then thermomechanical fatigue resistance is improved, but compressor performance is compromised
Solution Approach 1:
The invention changes the geometric parameters of the vane, specifically defining the neck thickness t and deck thickness b with a specific ratio relationship (t/b ≥ 0.21), and the chord length l with leading edge angle ∅ product (t(l cos ∅) within 11-25). This parameter optimization resolves the contradiction by finding the optimal balance point where sufficient thickness provides durability while maintaining aerodynamic efficiency.
2Strength
If the leading edge thickness of the vane is increased to improve strength, then durability is improved, but the design complexity increases
Solution Approach 1:
The invention establishes clear quantitative parameter ranges (t/b ≥ 0.21 and 11 ≤ t(l cos ∅) ≤ 25) that provide straightforward design guidelines. This resolves the contradiction by transforming a complex design problem into a systematic parameter selection process, where designers can achieve both strength and simplicity by following the defined parameter relationships.
Data Source
AI summary
A vane arrangement for a compressor is disclosed. The vane arrangement comprises a generally annular vane deck and at least one vane. The generally annular vane deck extends at least partway around a longitudinal axis, defining a deck thickness b in the axial direction. The at least one vane projects from a first surface of the vane deck. The at least one vane comprises a leading edge, a trailing edge, and first and second pressure surfaces. The leading edge is proximate the longitudinal axis. The trailing edge is distal the longitudinal axis. The first and second pressure surfaces extend between the leading edge and the trailing edge. The at least one vane defines a neck thickness t, proximate the leading edge, in a plane normal to the longitudinal axis, wherein t/b≥about 0.21.