Supersonic Compressor Rotor With Offset Vane Compression Ramps
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Solution Overview
Problem
Supersonic compressors face efficiency losses due to normal shockwaves interacting with boundary layers, leading to local flow separation and reduced operating efficiency, particularly in multi-stage compression systems.
Innovation Solution
The design incorporates two sets of rotor vanes with compression ramps that generate oblique shockwaves, restricting normal shockwave formation to the end of each flow channel, reducing the interaction with boundary layers and minimizing flow separation, thereby enhancing compression efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stress or pressure
If supersonic compressors use normal shockwaves to reduce fluid velocity to subsonic speed, then compression is achieved, but boundary layer interaction causes flow separation and efficiency loss
Solution Approach 1:
The rotor is divided into two sets of rotor vanes (first and second sets) that create multiple flow channels. This segmentation allows the compression process to occur in stages, with oblique shockwaves in the first set and controlled normal shockwaves at the end of channels in the second set, reducing boundary layer interaction and flow separation.
Solution Approach 2:
The invention introduces compression ramps on the rotor vane surfaces that generate oblique shockwaves instead of direct normal shockwaves. This dimensional change in the shockwave generation approach (from perpendicular to angled) allows gradual compression while maintaining supersonic flow longer, reducing harmful boundary layer interactions.
2Stress or pressure
If multiple stages of compression are used to achieve higher pressure ratios, then compression efficiency improves, but device size and complexity increase
Solution Approach 1:
The invention merges multiple compression functions into a single rotor assembly with two sets of rotor vanes. The first and second sets of rotor vanes work together in one rotating component to achieve multi-stage compression effects, combining what would traditionally require separate compression stages into one integrated structure.
Solution Approach 2:
The rotor vanes serve multiple functions: they guide fluid flow through flow channels, generate oblique shockwaves on their surfaces, and create controlled normal shockwaves at channel ends. This multi-functionality allows a single component to perform what would traditionally require multiple specialized components.
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 configuration achieves higher pressure ratios with lower pressure losses and increased resistance to boundary layer separation, improving the overall efficiency of the supersonic compressor.
Implementation Method 1
the compression ramps are configured to generate oblique shockwaves within each flow channel of the first set and second set of flow channels
Implementation Method 2
the generation of a normal shockwave is restricted to an end of each flow channel of the second set of flow channels so as to reduce the velocity of the compressed fluid to a subsonic velocity
Data Source
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AI summary
A supersonic compressor rotor and method of compressing a fluid is disclosed. The rotor includes a first and a second rotor disk, a first set and a second set of rotor vanes. The first set and second set of rotor vanes are coupled to and disposed between the first and second rotor disks. Further, the first set of rotor vanes are offset from the second set of rotor vanes. The rotor includes a first set of flow channels defined by the first set of rotor vanes disposed between the first and second rotor disks. Similarly, the rotor includes a second set of flow channels defined by the second set of rotor vanes disposed between the first and second rotor disks. Further, the rotor includes a compression ramp disposed on a rotor vane surface opposite to an adjacent rotor vane surface.