Asymmetrical Compressor Inlet Guide Baffle for Flow Symmetry
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Solution Overview
Problem
Axial flow machines with asymmetrical air inlets face flow detachment and efficiency losses in the first compressor stage due to asymmetrical inflow, leading to instability and reduced performance.
Innovation Solution
The axial flow machine employs an inlet guide vane grid with guide vanes having varying blade profiles and angles of attack to achieve circumferentially symmetrical inlet flow conditions, minimizing disturbances and ensuring stable compressor operation by targeted profiling and angle adjustments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If asymmetrical air inlet is used in axial flow machines, then the machine can be adapted to specific applications (e.g., turboprop or helicopter engines), but flow detachment and efficiency losses occur in the first compressor stage
Solution Approach 1:
The patent applies local quality by giving individual guide vanes different blade profiles and angles of attack tailored to their specific circumferential positions. Each vane is optimized for its local flow conditions caused by the asymmetrical inlet, transforming the uniform design into a position-specific design that addresses local flow asymmetries.
Solution Approach 2:
The patent intentionally introduces asymmetry into the guide vane design to counterbalance the asymmetry of the air inlet. By creating an asymmetrical distribution of vane angles and profiles, the system compensates for the inlet asymmetry and achieves symmetrical flow conditions at the compressor stage inlet.
2Adaptability or versatility
If asymmetrical air inlet is used, then application-specific design is achieved, but stability of the compressor is reduced
Solution Approach 1:
The patent applies local quality by giving individual guide vanes different blade profiles and angles of attack tailored to their specific circumferential positions. Each vane is optimized for its local flow conditions caused by the asymmetrical inlet, transforming the uniform design into a position-specific design that addresses local flow asymmetries.
Solution Approach 2:
The guide vanes preemptively correct the asymmetrical flow pattern before it reaches the compressor rotor. By pre-adjusting the flow angles through specifically profiled stationary guide vanes, the system prevents flow detachment and instability from developing in the rotating compressor stages.
3Stability of the object's composition
If all guide vanes have different blade profiles and angles of attack, then circumferentially symmetrical inlet conditions are achieved, but manufacturing complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the guide vanes into distinct groups based on their geometric characteristics. Instead of making every vane unique, the vanes are categorized into groups (e.g., first group, second group, third group) where each group shares common profile characteristics, reducing the number of unique components while still achieving the required flow symmetry.
Solution Approach 2:
The patent applies local quality by giving individual guide vanes different blade profiles and angles of attack tailored to their specific circumferential positions. Each vane is optimized for its local flow conditions caused by the asymmetrical inlet, transforming the uniform design into a position-specific design that addresses local flow asymmetries.
Data Source
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AI summary
An axial turbomachine having an asymmetrical air inlet and a compressor which is connected downstream of the air inlet and has an inlet guide baffle formed by guide vanes is characterized in that at least individual guide vanes of the inlet guide baffle have a blade profile that deviates from the remaining guide vanes and/or a deviating angle of attack. In this way, the inlet flow angle of the first compressor stage is evened out symmetrically over the periphery. This is achieved in that the different inlet angles caused by the asymmetry of the air inlet on different peripheral positions of the inlet guide baffle are influenced by specific profiles and/or specific changes of the angle of attack of individual guide vanes such that this results in an outflow angle out of the inlet guide ring which is symmetrical over the periphery. In this way, the peripheral interference caused by the asymmetrical air inlet is minimized and the first compressor stage is provided with substantially peripherally symmetrical inlet conditions, resulting in improved stability and improved efficiency of the compressor.