Counter-Rotary Supersonic Compressor Stages
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Solution Overview
Problem
Conventional compressor systems are limited by low achievable pressure ratios per stage, leading to large, complex, and costly systems when multiple stages are required for high overall pressure ratios.
Innovation Solution
The use of counter-rotary supersonic compressor rotors configured in series, where the output from a first supersonic compressor rotor is directed to a second counter-rotating rotor, enhancing compression efficiency and achieving higher pressure ratios.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stress or pressure
If conventional compressor systems use multiple compression stages to achieve high overall pressure ratios, then the achievable pressure ratio increases, but the system size, complexity, and cost increase
Solution Approach 1:
The compressor is divided into multiple supersonic stages with counter-rotating rotors, where each stage contributes to the overall pressure ratio. This segmentation allows achieving high pressure ratios while maintaining a more compact structure compared to conventional multi-stage compressors
Solution Approach 2:
The invention introduces a new dimension of operation by utilizing supersonic flow regimes and counter-rotation, transforming the conventional subsonic single-direction compression approach into a supersonic bidirectional compression system, thereby achieving higher pressure ratios in a more compact configuration
2Stress or pressure
If conventional compressor systems use multiple compression stages to achieve high overall pressure ratios, then the achievable pressure ratio increases, but the system size and weight increase
Solution Approach 1:
The compressor is divided into multiple supersonic stages with counter-rotating rotors, where each stage contributes to the overall pressure ratio. This segmentation allows achieving high pressure ratios while maintaining a more compact structure compared to conventional multi-stage compressors
Solution Approach 2:
The invention changes the operational parameters from subsonic to supersonic flow regimes, enabling higher compression ratios per stage and reducing the number of stages required, thereby decreasing overall system weight
3Device complexity
If a single supersonic compressor rotor is used, then the system size is reduced compared to conventional multi-stage compressors, but the achievable pressure ratio is limited
Solution Approach 1:
The compressor is divided into multiple supersonic stages with counter-rotating rotors, where each stage contributes to the overall pressure ratio. This segmentation allows achieving high pressure ratios while maintaining a more compact structure compared to conventional multi-stage compressors
Solution Approach 2:
The invention merges multiple compression functions into a compact multi-stage supersonic configuration, where counter-rotating rotors work in series to achieve cumulative pressure ratios while maintaining a smaller overall footprint than conventional systems
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 results in significant enhancements in compressor performance, achieving higher pressure ratios with reduced system size and weight, making it suitable for applications like gas turbine engines.
Implementation Method 1
supersonic compressor rotors which transport and compress a gas from a low pressure side of the supersonic compressor rotors to a high pressure side of the supersonic compressor rotors
Data Source
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AI summary
A novel supersonic compressor is provided by the present invention. In one embodiment, the novel supersonic compressor comprises a fluid inlet (10), a fluid outlet (20), and at least two counter rotary supersonic compressor rotors (100,200), said supersonic compressor rotors being configured in series such that an output from a first supersonic compressor rotor having a first direction of rotation (310) is directed to a second supersonic compressor rotor (200) configured to counter-rotate with respect to the first supersonic compressor rotor (100).