Drag Link Fitting and Vent Integration for Nacelle Cooling
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Jet aircraft propulsion systems face increased drag and reduced sound attenuation due to drag link fittings and vent holes, which disrupt airflow and compromise acoustic treatment as engine sizes and temperatures rise, necessitating an improved design that minimizes drag and enhances sound attenuation.
Innovation Solution
The design incorporates a drag link fitting aerodynamically associated with a vent, featuring a low profile air inlet and a vent that descends through the IFS, either orthogonally or sloping, allowing for increased acoustic treatment surface area and volume while minimizing drag, with the fitting comprising a forged metallic outer portion and a cast metallic inner portion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If drag link fittings and vent holes are added to the IFS for structural support and cooling, then the engine core cavity can be cooled effectively, but drag increases and sound attenuation is compromised
Solution Approach 1:
The drag link fitting and vent are combined into a single integrated component. The vent is positioned within the drag link fitting structure, allowing both the drag link function and cooling vent function to be performed by one element rather than two separate components, thereby reducing overall drag while maintaining cooling effectiveness
Solution Approach 2:
The acoustic treatment material is selectively applied to specific regions of the IFS, particularly around the vent area and drag link fitting. This localized acoustic treatment provides sound attenuation where needed without requiring complete coverage, thus maintaining drag reduction while improving noise suppression in critical areas
2Temperature
If drag link fittings and vent holes are added to the IFS for structural support and cooling, then the engine core cavity can be cooled effectively, but sound attenuation is compromised
Solution Approach 1:
The drag link fitting and vent are combined into a single integrated component. The vent is positioned within the drag link fitting structure, allowing both the drag link function and cooling vent function to be performed by one element rather than two separate components, thereby reducing overall drag while maintaining cooling effectiveness
Solution Approach 2:
The acoustic treatment material is selectively applied to specific regions of the IFS, particularly around the vent area and drag link fitting. This localized acoustic treatment provides sound attenuation where needed without requiring complete coverage, thus maintaining drag reduction while improving noise suppression in critical areas
3Temperature
If the number and size of ventilation apertures are increased to compensate for higher engine temperatures, then cooling effectiveness is improved, but drag increases and acoustic treatment area is reduced
Solution Approach 1:
The drag link fitting and vent are combined into a single integrated component. The vent is positioned within the drag link fitting structure, allowing both the drag link function and cooling vent function to be performed by one element rather than two separate components, thereby reducing overall drag while maintaining cooling effectiveness
Solution Approach 2:
The acoustic treatment material is selectively applied to specific regions of the IFS, particularly around the vent area and drag link fitting. This localized acoustic treatment provides sound attenuation where needed without requiring complete coverage, thus maintaining drag reduction while improving noise suppression in critical areas
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 drag and improves sound attenuation by directing airflow into the vent, increasing the area available for acoustic treatment and withstanding high operational stresses, thus enhancing the overall performance of the jet aircraft propulsion system.
Implementation Method 1
The drag link fitting may be aerodynamically associated with the vent such that the drag link fitting helps direct air into the vent
Implementation Method 2
one or more vents may extend through the IFS to channel cooler air flowing within the bypass air duct into the annular enclosed space surrounding the engine core
Implementation Method 3
Noise may be attenuated within the cavities formed by the honeycomb shaped core
Data Source
AI summary
A nacelle is disclosed. The nacelle may comprise, in various embodiments, a drag link fitting mounted to an Inner Fixed Structure (IFS) and pivotally attached to an end of a drag link, and a vent defining a passageway through the IFS to bring cooling air through the IFS. The drag link fitting may be aerodynamically associated with the vent such that the drag link fitting helps direct air into the vent.