Turbine Guide Vane with Offset Max Thickness
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Solution Overview
Problem
Turbine engine guide vanes face challenges in achieving good aerodynamic performance while minimizing twisting and bending deformations, which affect their operability and aerodynamic behavior.
Innovation Solution
The guide vane design features a forward-projecting leading edge and offset maximum thickness along the chord, with the leading edge projecting upstream and maximum thickness positioned at least 50% of the chord away from the leading edge, optimizing air flow distribution and reducing twisting and bending phenomena.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If the guide vane has conventional geometry with maximum thickness near the leading edge, then structural strength is improved, but aerodynamic performance deteriorates due to poor air flow distribution
Solution Approach 1:
The patent applies local quality by differentiating the thickness distribution along the chord based on the vertical position. The bottom portion (z'/Ht ≤ 0.5) has maximum thickness offset by at least 50% of chord from the leading edge to improve aerodynamic flow distribution, while the top portion maintains conventional thickness distribution near the leading edge to preserve structural strength and resistance to twisting/bending deformations.
2Loss of energy
If the maximum thickness is positioned close to the leading edge, then twisting and bending resistance is improved, but aerodynamic performance deteriorates due to increased air flow losses
Solution Approach 1:
The patent implements local quality by applying different thickness distribution characteristics to different portions of the vane. The bottom portion (z'/Ht ≤ 0.5) features maximum thickness offset by at least 50% of chord from the leading edge to minimize air flow losses and improve aerodynamic performance, while the top portion maintains conventional thickness distribution to ensure adequate resistance to twisting and bending deformations.
3Productivity
If the guide vane geometry is modified to improve aerodynamic performance, then air flow distribution is improved, but the twist-bend coupling parameter deteriorates
Solution Approach 1:
The patent resolves this contradiction by applying local quality through differentiated thickness distribution. The bottom portion (z'/Ht ≤ 0.5) has maximum thickness offset by at least 50% of chord to improve aerodynamic efficiency and air flow distribution, while the top portion maintains conventional geometry to preserve acceptable twist-bend coupling behavior and structural reliability.
Solution Approach 2:
The patent applies segmentation by dividing the guide vane into two distinct portions along the vertical axis: a bottom portion (z'/Ht ≤ 0.5) with optimized thickness distribution for aerodynamic performance, and a top portion with conventional thickness distribution for structural stability. This segmentation allows each portion to be optimized for its specific functional requirements without compromising the other.
Data Source
AI summary
An outlet guide vane for a turbine engine, the vane having a plurality of vane sections stacked along a radial axis Z. Over a bottom portion of the vane in the range 0 to 50% of its total height, the leading edge of each section is in front of the leading edge of the corresponding section at the total height, and the maximum thicknesses are located at positions that are offset from the leading edge by at least 50% of the chord.