Conical Screw for Gas Turbine Compression Staging
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Solution Overview
Problem
Efficient multi-staging fluid flow in gas turbine engines with centrifugal compressors is hindered by incompatible fluid flow profiles between radial impellers and subsequent components, particularly due to perpendicular exit flow and mismatched radii, leading to operational inefficiencies.
Innovation Solution
Incorporation of a conical screw as an intermediary fluid transport device, which redirects radial impeller exit flow to axial flow and funnels larger exit radii into smaller inlet radii, facilitating compatible fluid flow between compressor stages and components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a centrifugal compressor with radial impeller is used, then single-stage compression capability is improved, but multi-stage fluid transport efficiency deteriorates due to incompatible flow profiles
Solution Approach 1:
The patent introduces an intermediary component (flow director or transition passage) between the radial impeller and the axial compressor stage to mediate the incompatible flow profiles. This intermediary redirects the radially outward flow from the impeller into an axial flow pattern suitable for the next stage, resolving the contradiction between maintaining centrifugal compression capability and achieving efficient multi-stage transport.
2Stress or pressure
If radial impeller exit flow is used, then centrifugal compression is achieved, but flow direction compatibility with subsequent components deteriorates due to perpendicular exit flow
Solution Approach 1:
The patent employs transition passages or flow directors that guide the fluid through a dimensional change in flow direction. The radially outward flow (perpendicular to axis) is gradually redirected into axial flow (parallel to axis) through carefully designed three-dimensional passage geometry, enabling compatibility with subsequent axial components while preserving centrifugal compression benefits.
3Stress or pressure
If larger exit radii from radial impeller are used, then compression ratio is improved, but compatibility with smaller inlet radii of subsequent components deteriorates
Solution Approach 1:
The patent utilizes curved transition passages with varying cross-sectional areas to smoothly connect the larger exit radius of the radial impeller to the smaller inlet radius of subsequent components. The curved geometry allows gradual radius reduction while maintaining attached flow and minimizing losses, reconciling the size mismatch between stages.
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 conical screw enhances multi-staging efficiency by aligning fluid flow profiles, allowing for effective fluid transport between compressor stages and components, thereby improving overall engine performance.
Implementation Method 1
the vane members 56 of the rotor cause the medium to be centrifugally spun outwardly
Data Source
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AI summary
A gas turbine engine, with a conical screw integrated compression system, that utilizes at least one conical screw as an intermediary fluid transport device to facilitate the multi-staging of non-axial compressors, such as centrifugal and diagonal compressors, as well as or alternatively to combine non-axial compressors to axial compressors and to the fan. The conical screw in the compression system applies axial flow translation and funnels, as necessary, the exit flow of the impeller, fan or compressor into the next impeller or compressor.