Static Nozzle Airfoil With Reduced Midspan Axial Width
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Solution Overview
Problem
Conventional turbomachine nozzle designs experience inefficiencies due to uneven fluid flow distribution across airfoil regions, leading to increased losses and reduced performance.
Innovation Solution
A static nozzle blade structure with a reduced axial width in the midspan region and varying blade opening-to-pitch ratios across the airfoil, concentrating fluid flow towards the midspan region to minimize losses and enhance efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional uniform nozzle blade designs are used, then manufacturing is simpler, but fluid flow distribution is uneven leading to increased losses
Solution Approach 1:
The nozzle blade is designed with varying axial width along its span, creating different local geometries optimized for specific flow conditions. The midspan region has reduced axial width while root and tip regions maintain larger widths, allowing each section to handle fluid flow differently and reduce local losses.
Solution Approach 2:
The blade structure is effectively segmented into distinct regions (root, midspan, tip) with different geometric characteristics. This segmentation allows independent optimization of each region's flow handling capabilities, with the midspan region specifically designed to concentrate and utilize fluid flow more efficiently.
2Productivity
If uniform axial width is maintained across the airfoil, then manufacturing is easier, but flow concentration cannot be achieved leading to reduced efficiency
Solution Approach 1:
Different sections of the airfoil are given different axial widths tailored to their specific flow requirements. The midspan region's reduced width creates a natural flow concentration effect, while root and tip regions maintain adequate width for structural integrity and endwall flow management.
Solution Approach 2:
The axial width parameter is varied continuously or in steps along the airfoil span rather than remaining constant. This parameter change optimizes the blade opening-to-pitch ratio at different locations, enhancing flow distribution and turbine efficiency.
3Loss of energy
If blade opening-to-pitch ratio is uniform, then design is simpler, but fluid flow cannot be concentrated leading to higher losses in midspan region
Solution Approach 1:
The blade opening-to-pitch ratio is optimized locally for each section of the airfoil. The midspan region achieves a higher effective ratio through reduced axial width, improving flow concentration and reducing losses, while other regions maintain appropriate ratios for their specific conditions.
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 enhances the performance and durability of turbomachine blades by redirecting fluid flow from high-loss regions near the endwalls to the midspan, where it can be utilized more efficiently, thereby improving overall turbine efficiency and reducing secondary losses.
Implementation Method 1
A static nozzle blade structure with a reduced axial width in the midspan region and varying blade opening-to-pitch ratios across the airfoil, concentrating fluid flow towards the midspan region
Data Source
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AI summary
The disclosure provides a blade with an airfoil (202) including a root region (R) at a first radial end, a tip region (T) at a second radial end opposite the first radial end, and a midspan region (M) between the root region and the tip region and at least one endwall (212) connected with the root region or the tip region of the airfoil along the suction side, the pressure side, the trailing edge (210) and the leading edge (208), wherein the midspan region includes a reduced axial width (W) relative to an axial width of the root region and an axial width of the tip region, and a reduced opening-to-pitch ratio at the midspan region relative to the root and tip regions.