Axial Flow Compressor Stator Vane Load Distribution
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Solution Overview
Problem
The axial flow compressor faces reliability and aerodynamic performance issues due to increased blade loading on the rear-stage stator vane, leading to flow separation and potential vibration, especially during partial load operations or when the inlet guide vane is closed, which can result in deteriorated performance and increased risk of damage.
Innovation Solution
The axial flow compressor employs a specific load distribution strategy across the stator vanes, reducing blade loading on the last-stage stator vane and exit guide vanes, with a focus on minimizing the turning angle and stagger angle to prevent flow separation, and optimizing the load distribution from the first to the third stator vane to maintain efficient operation across varying conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the inlet guide vane is closed or the compressor operates in partial load state, then the compressor can adapt to varying operational demands, but the blade loading on the rear-stage stator vane increases causing flow separation and reliability issues
Solution Approach 1:
The patent applies different stagger angles to different stages of stator vanes. Specifically, the first stator vane has a first stagger angle, the second stator vane has a second stagger angle different from the first, and the third stator vane has a third stagger angle different from the second. This local differentiation optimizes the load distribution across each stage, preventing excessive blade loading on rear-stage vanes while maintaining adaptability across operational ranges.
2Power
If the blade loading on the last-stage stator vane is increased to handle higher compression demands, then the compression capability is improved, but flow separation occurs leading to increased vibration and potential damage
Solution Approach 1:
The patent changes the geometric parameters (stagger angles) of the stator vanes to optimize performance. The first stator vane has a first stagger angle, the second stator vane has a second stagger angle different from the first, and the third stator vane has a third stagger angle different from the second. By adjusting these parameters, the patent achieves optimal load distribution that prevents flow separation while maintaining compression capability.
3Ease of manufacture
If the stator vanes are designed with uniform stagger angles, then the manufacturing is simplified, but the load distribution across stages is suboptimal reducing aerodynamic efficiency
Solution Approach 1:
The patent implements local quality by assigning different stagger angles to different stator vane stages. The first stator vane has a first stagger angle, the second stator vane has a second stagger angle different from the first, and the third stator vane has a third stagger angle different from the second. This approach prioritizes aerodynamic efficiency over manufacturing simplicity, as the differentiated design optimizes load distribution and prevents flow separation.
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 load distribution strategy enhances the reliability and aerodynamic performance of the compressor by reducing blade loading, preventing flow separation, and enlarging the operational range, thereby improving the overall efficiency and reducing the risk of damage during partial load operations.
Implementation Method 1
An inlet air of the axial flow compressor is decelerated and compressed by the respective vane rows into a high-temperature and high-pressure airflow
Implementation Method 2
a rotating rotor 22 to which multiple rotor blades 31 is fitted, and has an annular flow passage formed by the rotating rotor 22 and the casing 21 inside
Implementation Method 3
an annular flow passage downstream of the rotor having a portion which decreases in cross-sectional area in the downstream direction to reduce the supersonic flow to subsonic velocity by way of a single annular shockwave located in the flow passage
Data Source
Figure 1A~1B
Figure 2
Figure 3
AI summary
There is provided an axial flow compressor 1 that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor 1 due to a partial load operation of a gas turbine 3. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes 35, 36, 37 are disposed downstream of a last-stage rotor blade that is the rotor blade disposed at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane 35 disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane 36 disposed downstream of the first stator vane 35 by one row.