Turbofan Bypass Arm Trailing Edge Angle Optimization
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Solution Overview
Problem
Residual swirl in the bypass flow of turbofan engines leads to significant separation and loss of static pressure at the trailing edges of arms and pylons, resulting in increased losses and distortion upstream.
Innovation Solution
The introduction of a bypass flow guide vane stage with obstacles, including arms and pylons, featuring a trailing edge skeleton angle between 3° and 15°, which reduces flow deflection and separation by aligning the suction or pressure side with the longitudinal axis of the turbine engine, thereby minimizing the influence of pylon-induced fluid bifurcation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the arms and pylons are used to support the turbine engine and transmit forces, then the structural strength and stability are improved, but residual swirl in the bypass flow causes significant separation and loss of static pressure at the trailing edges, resulting in increased losses
Solution Approach 1:
The patent applies parameter changes by modifying the skeleton angle of the trailing edge of the arms and pylons to a specific range (3° to 15°). This geometric parameter optimization reduces flow separation and minimizes the adverse effects of residual swirl, thereby decreasing energy losses while maintaining the structural support function of the arms and pylons
2Stability of the object's composition
If the arms are positioned to support the engine structure, then the mechanical stability is improved, but strong deviation of fluid at the trailing edge generates considerable separation and reflection of distortion upstream
Solution Approach 1:
The patent modifies the geometric parameter of the arm trailing edge by setting the skeleton angle between 3° to 15°. This parameter optimization reduces fluid deviation and minimizes separation and distortion effects while preserving the mechanical stability provided by the arm structure
Solution Approach 2:
The patent addresses the trailing edge geometry by introducing a specific angular dimension (skeleton angle) to the arm structure. This dimensional modification changes how the flow interacts with the trailing edge, reducing separation and distortion without compromising structural stability
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
This configuration reduces OGV losses by 0.03%, fairing losses by 0.02%, and static pressure distortion by 0.3%, while eliminating recirculation and separation, thereby enhancing the overall performance of the turbine engine.
Implementation Method 1
a strong increase in losses is noted and a reflection of the distortion of the static pressure upstream. It would thus be desirable to attenuate or cancel these separations
Data Source
AI summary
A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3° and 15°.