Inducerless Radial Impeller for Supercritical CO2 Compression
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Solution Overview
Problem
Existing turbomachinery designs are inadequate for compressing supercritical carbon dioxide, as they face instability due to rapid changes in the compressibility factor of CO2 near its critical point, leading to unstable operation and potential condensation issues.
Innovation Solution
A turbomachine design featuring an inducerless radial impeller and a fully vaneless diffuser, with a large inlet radius relative to the impeller radius, and backswept blades to maintain stability and prevent condensation, allowing for efficient compression of supercritical CO2 across a wide range of conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the turbomachine operates with inlet conditions close to the critical point to achieve high pressure rise per unit work, then the pressure rise efficiency is improved, but the operation stability deteriorates due to rapid changes in compressibility factor
Solution Approach 1:
The patent applies dynamics by making the inlet conditions adjustable and adaptable. The system allows dynamic adjustment of inlet pressure and temperature to maintain optimal operation away from the critical point, enabling the turbomachine to adapt to changing operating conditions and avoid instability while maintaining high pressure rise efficiency
Solution Approach 2:
The patent changes the operating parameters by deliberately operating at inlet conditions away from the critical point (inlet pressure below 7.39 MPa and inlet temperature above 304.25 K). This parameter change avoids the region of rapid compressibility factor changes, thereby maintaining operation stability while still achieving high pressure rise through optimized impeller and diffuser design
2Reliability
If the inlet radius is increased relative to impeller radius to stabilize operation, then the operation stability is improved, but the device size increases
Solution Approach 1:
The patent optimizes the geometric parameters of the turbomachine, specifically setting the inlet radius to 25-50% of the impeller radius. This parameter optimization achieves stable operation by ensuring adequate inlet area for flow stabilization while minimizing the overall device size through efficient space utilization
Solution Approach 2:
The patent applies local quality by creating a specific geometric configuration where the inlet area is locally enlarged relative to the impeller size. This local geometric optimization provides sufficient flow area for stability without proportionally increasing the entire device volume, as the enlargement is concentrated at the inlet region only
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
The design ensures stable operation and reduced losses by maintaining a stable flow regime and minimizing the risk of condensation, achieving a high pressure rise with minimal energy input and wide operating range.
Implementation Method 1
an inducerless radial impeller having a plurality of blades
Implementation Method 2
a fully vaneless diffuser
Data Source
AI summary
A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of blades, and a fully vaneless diffuser (203). The radius of the inlet (r0) is from 25 to 50 percent of the radius of the impeller (r2).