Aircraft Inlet Assembly Airflow Distortion Reduction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft engine inlets experience airflow distortion due to factors like thin nacelle lips, leading to aeromechanical and operational issues, particularly in supersonic engines.
Innovation Solution
A low-distortion inlet assembly with structural members and airflow modifying elements, such as inlet guide vanes, struts, vortex generators, and contoured surfaces, is mounted around the circumference of the engine inlet to reduce airflow distortion by redistributing and modifying the airflow entering the compression airfoils.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If thin lips/leading edges of a nacelle are used, then the engine size is reduced, but airflow distortion at the inlet increases
Solution Approach 1:
An inlet assembly is introduced as an intermediary component between the nacelle and the engine inlet. This assembly includes structural members and airflow modifying elements that actively manage and reduce airflow distortion, serving as a mediator that protects the engine from harmful distorted flow while allowing the thin-nacelle design to be maintained.
Solution Approach 2:
The airflow distortion problem is extracted and addressed separately from the nacelle design. Rather than changing the thin-nacelle configuration, the invention removes the harmful effect by placing an inlet assembly that specifically targets and reduces airflow distortion at the engine inlet.
2Reliability
If airflow distortion is reduced using structural members and airflow modifying elements, then engine operability is improved, but device complexity increases
Solution Approach 1:
The inlet assembly is segmented into distinct functional components: structural members for support and positioning, and separate airflow modifying elements for distortion reduction. This segmentation allows each component to be optimized independently and facilitates maintenance and adjustment.
Solution Approach 2:
The inlet assembly is designed to perform multiple functions simultaneously: it provides structural support, modifies airflow patterns, reduces distortion, and protects the engine inlet. This multi-functionality reduces the need for separate components, thereby managing complexity while achieving multiple goals.
3Productivity
If airflow modifying elements are added to reduce distortion, then engine efficiency is improved, but weight increases
Solution Approach 1:
The inlet assembly utilizes thin-walled structural members and film-like airflow modifying elements that provide the necessary aerodynamic function with minimal material. These thin structures reduce weight while maintaining structural integrity and airflow modification capabilities.
Solution Approach 2:
The design optimizes parameters such as the thickness, shape, and material properties of the inlet assembly components to achieve the lightest possible weight that still provides sufficient airflow distortion reduction. Parametric studies are used to find the optimal balance between weight and performance.
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
The solution effectively reduces airflow distortion, improving engine operability and efficiency while minimizing weight, thereby enhancing the performance and reliability of aircraft engines.
Implementation Method 1
inlet guide vanes configured within the inlet so as to reduce airflow distortion entering the stage of compression airfoils
Implementation Method 2
vortex generators configured within the inlet so as to reduce airflow distortion entering the stage of compression airfoils
Implementation Method 3
contoured surfaces configured within the inlet so as to reduce airflow distortion entering the stage of compression airfoils
Data Source
AI summary
An engine for mounting in or to an aircraft includes a stage of compression airfoils rotatable about a central axis; a casing surrounding the stage of compression airfoils and defining an inlet; and a low-distortion inlet assembly mounted within the inlet. The inlet assembly includes one or more structural members mounted at predetermined locations around a circumference of the central axis within the inlet, the predetermined locations defining an airflow distortion exceeding a predetermined threshold; and at least one airflow modifying element configured within the inlet so as to reduce airflow distortion entering the stage of compression airfoils.