Integrated Stator Vane Pylon for Lower Secondary Flow Loss
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Solution Overview
Problem
In short-nacelle propulsion assemblies, the mounting pylon partially entering the secondary flow path downstream from stator vanes generates aerodynamic losses, negatively impacting overall efficiency.
Innovation Solution
The mounting pylon is designed with an upstream part that extends radially within the secondary flow path, limited to a height less than the total radial height, and integrates a stator vane to form aerodynamic continuity, minimizing friction losses and static pressure heterogeneities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the mounting pylon enters the secondary flow path downstream from stator vanes, then the structural support function is achieved, but aerodynamic losses increase due to friction
Solution Approach 1:
The mounting pylon is merged with the stator vanes to form a single integrated structure. The pylon extends through the secondary flow path and is directly connected to the stator vane roots, eliminating the need for separate structural support elements within the flow path. This integration reduces the number of discrete components that create friction and aerodynamic losses while maintaining the necessary structural support function.
Solution Approach 2:
The integrated pylon-stator vane structure serves multiple functions simultaneously: it provides structural support for the engine mounting, directs the secondary flow path, and minimizes aerodynamic friction. The stator vanes themselves become part of the structural support system, eliminating the need for separate pylons to extend deeply into the flow path.
2Strength
If the mounting pylon extends through the secondary flow path, then engine mounting is achieved, but static pressure heterogeneities increase
Solution Approach 1:
By merging the mounting pylon with the stator vanes, the structure that causes pressure heterogeneities is replaced with aerodynamic surfaces designed to manage flow. The stator vanes are specifically shaped to straighten and uniform the secondary flow, thereby reducing static pressure heterogeneities while still providing the necessary mounting support through their integrated connection to the pylon.
Solution Approach 2:
The stator vanes are positioned and shaped to specifically address the flow conditions in different regions of the secondary flow path. By optimizing the local geometry of the vanes where they interact with the flow, the design minimizes pressure heterogeneities in critical areas while maintaining overall structural integrity for engine mounting.
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 design improves propulsive efficiency by reducing aerodynamic losses and enhancing aerodynamic performance.
Implementation Method 1
They are essentially intended to straighten the cold air flow from the fan vanes
Implementation Method 2
generating aerodynamic losses by friction, with a negative impact on the overall efficiency
Implementation Method 3
minimizing friction losses and static pressure heterogeneities
Data Source
AI summary
A propulsion assembly for an aircraft comprising a dual-flow turbine engine equipped with a fan, an aerodynamic outer shroud acting as a nacelle as well as a mounting pylon, the propulsion assembly having a secondary flow path defined by an outer radial defining surface formed by the shroud, the turbine engine including stator vanes, and the mounting pylon comprising a part housed in the secondary flow path, referred to as upstream part. According to the invention, the upstream part of the pylon extends radially from the inner radial defining surface, along a radial pylon height strictly less than a total radial height of the secondary flow path, and the upstream part of the pylon extends in the downstream direction from a root part of one of the stator vanes.