Supersonic Compressor Rotor Shroud and Sealing
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Solution Overview
Problem
Supersonic compressor systems face efficiency losses due to fluid leakage across radially outer portions of vanes, resulting in large pressure gradients and a significant footprint for a given flow capacity and pressurization ratio.
Innovation Solution
The supersonic compressor rotor incorporates a shroud over the radially outer tops of vanes to separate fluid flow paths and utilizes axial and radial sealing devices to minimize fluid leakage, reducing losses and optimizing flow efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stress or pressure
If fluid is channeled through the flow channel with large pressure gradients across the vanes, then compression is achieved, but fluid leakage across radially outer portions of the vanes causes efficiency loss
Solution Approach 1:
The patent extracts and removes the harmful fluid leakage paths by introducing sealing devices that block the radial leakage paths at the outer portions of the vanes. The sealing devices are positioned to prevent fluid from crossing the pressure gradient radially outward, thereby eliminating the energy loss mechanism while preserving the compression function.
Solution Approach 2:
The patent introduces sealing devices as intermediary elements between the high-pressure and low-pressure regions across the vanes. These sealing devices act as mediators that prevent direct fluid leakage while allowing the pressure gradient to be maintained for compression purposes. The sealing devices include radial seals and axial seals that interface between the rotor and stator components.
2Productivity
If the compressor is designed to achieve high pressurization ratio and flow capacity, then performance is improved, but the physical footprint increases
Solution Approach 1:
The patent changes the flow parameters by controlling the fluid velocity to be supersonic at the inlet and managing shockwave formation within the flow channel. By optimizing the Mach number and pressure ratio parameters, the compressor achieves high flow capacity and pressurization ratio in a more compact configuration. The supersonic flow regime allows for more efficient compression with reduced component size.
3Power
If supersonic compression ramps are positioned within the flow path to form shockwaves, then compression is achieved, but fluid leakage at radially outer portions causes efficiency loss
Solution Approach 1:
The patent segments the flow channel into distinct regions with different flow characteristics. The supersonic compression ramps create shockwaves in the inner portion of the flow channel where compression is needed, while sealing devices are positioned at the radially outer portions to prevent leakage. This segmentation allows the compression function and sealing function to operate in separate zones, maximizing efficiency.
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 operating efficiency of supersonic compressor systems by reducing fluid flow losses across the vanes and increasing the flow capacity and pressurization ratio while minimizing the compressor footprint.
Implementation Method 1
the supersonic compressor ramp causes formation of a system of oblique shockwaves within a converging portion of the flow channel
Implementation Method 2
a normal shockwave in a diverging portion of the flow channel
Data Source
Figure 1
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Figure 3
AI summary
A supersonic compressor (10) includes a fluid inlet (26), a fluid outlet (28), a fluid conduit (32) extending therebetween, and a supersonic compressor rotor (40) disposed within the fluid conduit. The rotor includes a rotor disk (48) that includes a substantially cylindrical body (50) extending between a radially inner (56) and outer surface (58) and a plurality of vanes (46) coupled to the body that extend radially outward from the rotor disk, adjacent vanes form a pair. The rotor disk further includes a shroud (200) extending about the rotor disk. The shroud is coupled to at least a portion of each of the plurality of vanes. The radially outer surface, the pair of adjacent vanes, and the shroud are oriented such that a fluid flow channel (80) is defined therebetween. The rotor disk also includes a plurality of adjacent supersonic compression ramps (98) positioned within the fluid flow channel.