Turbomachine Platform Non-Axisymmetric Surface Geometry
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Solution Overview
Problem
The existing non-axisymmetrical vein geometry in turbomachine fans leads to significant aerodynamic detachments at the fan root, degrading performance and operability by reducing mass flow rate and compression efficiency.
Innovation Solution
A non-axisymmetrical surface geometry for the turbomachine platform with specific construction curves defined by C1 class curves, featuring gentle slopes to prevent aerodynamic detachment, characterized by controlled tangents and control points that limit slope angles and abscissa differences, enhancing the geometry's aerodynamic performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a non-axisymmetrical vein geometry is used to improve mass flow rate and aeromechanical performance, then the mass flow rate through the blades increases, but aerodynamic detachments occur at the fan root trailing edge degrading performance
Solution Approach 1:
The patent applies local quality by making the vein geometry non-axisymmetrical only in specific regions where it benefits mass flow, while maintaining axisymmetry or gentler slopes in critical areas (fan root trailing edge) to prevent detachments. This localized differentiation allows the vein to have different geometric properties in different spatial locations, optimizing both mass flow and aerodynamic stability simultaneously.
Solution Approach 2:
The patent utilizes asymmetry by introducing a non-axisymmetrical configuration to the vein geometry, specifically creating an asymmetric distribution of the vein volume relative to the rotational axis. This asymmetric design enables improved mass flow characteristics while the controlled asymmetry parameters prevent the formation of detachments at critical locations.
2Productivity
If the vein wall geometry is modified to optimize aeromechanical performance, then local performance at the fan root improves, but aerodynamic detachments are generated that reduce overall fan efficiency
Solution Approach 1:
The patent applies parameter changes by systematically varying the vein geometry parameters (such as the non-axisymmetry ratio, vein angle, and curvature radii) to find optimal values that maximize aeromechanical performance while minimizing aerodynamic detachments. By controlling specific geometric parameters within defined ranges, the patent achieves improved mass flow and compression ratio without excessive energy losses from detachments.
Data Source
AI summary
The present invention relates to a turbomachine component (1) or collection of components comprising at least a first and a second blade (3I, 3E) and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2) has a non-axisymmetric surface (S) bounded by a first and a second end plane (PS, PR) and defined by at least two class C construction curves each one representing the value of a radius of said surface (S) as a function of a position between the pressure face of the first blade (3I) and the suction face of the second blade (3E) in a plane substantially parallel to the end planes (PS, PR), these including at least one upstream curve and one downstream curve; each construction curve being defined by at least one pressure face control end point and one suction face control end point such that: —the tangent to the downstream curve at the suction face control end point 20 is inclined by at most 5°; —any other tangent to a construction curve at a control end point is inclined by at least 5°.