Variable Throat Supersonic Compressor Startup
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Solution Overview
Problem
Existing supersonic compressor systems face challenges in establishing and maintaining supersonic flow during startup due to fixed throat geometries, which either hinder startup with wider throat regions or decrease performance at steady-state with narrower regions.
Innovation Solution
A supersonic compressor rotor with a variable throat geometry, facilitated by an axially translatable fluid flow control device that modulates the throat area during starting operations and beyond, ensuring proper formation and maintenance of normal shockwaves.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a wider throat region is used, then supersonic flow establishment during startup is facilitated, but steady-state performance decreases
Solution Approach 1:
The throat geometry is made variable through an axially translatable fluid flow control device that can move along the flow path. During startup, the device positions to create a wider effective throat area to facilitate supersonic flow establishment. During steady-state operation, the device repositions to create a narrower effective throat area to optimize performance, thus dynamically adapting the geometry to match operational requirements.
Solution Approach 2:
The patent changes the geometric parameter of the throat area by introducing a movable fluid flow control device that alters the effective throat area. This parameter change allows the system to transition between different throat geometries based on operational mode, resolving the contradiction between startup ease and steady-state performance.
2Productivity
If a narrower throat region is used, then steady-state performance is improved, but difficulty of establishing supersonic flow during startup increases
Solution Approach 1:
The throat geometry is made variable through an axially translatable fluid flow control device that can move along the flow path. During startup, the device positions to create a wider effective throat area to facilitate supersonic flow establishment. During steady-state operation, the device repositions to create a narrower effective throat area to optimize performance, thus dynamically adapting the geometry to match operational requirements.
Solution Approach 2:
During startup, the fluid flow control device is positioned in advance to create a wider effective throat area before supersonic flow is required. This preliminary geometric configuration facilitates the establishment of supersonic flow. Once steady-state operation is achieved, the device is repositioned to the narrower throat configuration for optimized performance.
3Device complexity
If a fixed throat geometry is used, then device complexity is reduced, but adaptability to different operational conditions is limited
Solution Approach 1:
The throat geometry is made variable through an axially translatable fluid flow control device that can move along the flow path. During startup, the device positions to create a wider effective throat area to facilitate supersonic flow establishment. During steady-state operation, the device repositions to create a narrower effective throat area to optimize performance, thus dynamically adapting the geometry to match operational requirements.
Solution Approach 2:
The fluid flow control device serves multiple functions: it acts as a geometric modifier for different throat areas, a flow control element, and an adaptability mechanism for different operational modes. This multi-functionality justifies the added complexity by providing both startup support and steady-state optimization capabilities.
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 solution enhances the efficiency and performance of supersonic compressor systems by adjusting the throat area-to-inlet area ratio, optimizing shockwave formation and reducing pressure losses across normal shockwaves, thereby improving both startup and steady-state operations.
Implementation Method 1
Known supersonic compression ramps are positioned within the flow path to form a throat region and are configured to form a compression wave within the flow path
Implementation Method 2
the supersonic compressor ramp causes formation of a system of oblique shockwaves within a converging portion of the flow channel and a normal shockwave in a diverging portion of the flow channel
Implementation Method 3
the supersonic compressor ramp causes formation of a system of oblique shockwaves within a converging portion of the flow channel and a normal shockwave in a diverging portion of the flow channel
Data Source
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AI summary
A supersonic compressor (10) includes a fluid inlet (26), a fluid outlet (28), and a fluid conduit extending there between with a supersonic compressor rotor (40) disposed therein. The supersonic compressor rotor includes a first end wall (60) and a plurality of vanes ( 46) coupled thereto. Each pair of the vanes defines a fluid flow channel (80). The fluid flow channel defines a flow channel inlet opening (76) and a flow channel outlet opening (78) and includes a throat portion (124). The supersonic compressor rotor also includes a second end wall (90) and at least one axially translatable fluid control device (172) positioned adjacent to the rotor. The axially translatable fluid control device is configured to obstruct the throat portion and includes at least one axially translatable protrusion (178) insertable into at least a portion of the throat portion.