Serpentine Inertial Particle Separator for Aircraft Engine Inlets
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing air inlet systems for aircraft engines face challenges in minimizing pressure loss and complexity while effectively protecting against foreign object ingestion, as traditional inertial particle separators increase weight and aerodynamic losses when not in use.
Innovation Solution
The design of an inertial particle separator with a serpentine duct configuration, featuring a main duct, bypass duct, and splitter, which directs airflow and particles via inertia, allowing for efficient separation of particles from the air flow with minimal distortion and pressure loss, and is always operative without the need for actuatable vanes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional inertial particle separators with actuatable vanes are used, then foreign object protection is improved, but device complexity and weight increase
Solution Approach 1:
The patent removes the actuatable vanes from the system entirely, extracting the complex moving mechanism while retaining the particle separation function through a fixed serpentine duct configuration that uses inertial forces to separate particles from the airflow
Solution Approach 2:
The patent replaces the mechanical actuated vane system with a fixed geometric duct configuration that relies on fluid dynamics and inertial forces to achieve particle separation, eliminating the need for moving parts and actuators
2Reliability
If traditional inertial particle separators with actuatable vanes are used, then foreign object protection is improved, but weight increases
Solution Approach 1:
The patent removes the actuatable vanes and associated actuation mechanisms, extracting the sources of additional weight while maintaining particle separation capability through the fixed serpentine duct geometry
Solution Approach 2:
The patent substitutes the heavy mechanical actuated system with a lightweight fixed duct configuration that achieves particle separation through inertial forces acting on the airflow, significantly reducing overall system weight
3Reliability
If traditional inertial particle separators are used, then particle separation is achieved, but pressure loss increases
Solution Approach 1:
The patent employs a serpentine duct configuration with optimized curvature radii that allows smooth airflow transitions while maintaining the inertial separation effect, reducing flow separation and pressure losses compared to sharp angular configurations
Solution Approach 2:
The patent optimizes specific geometric parameters including the curvature radius ratio (R1/R2 ≥ 1.5), the angle α (≤ 45 degrees), and the width-to-height ratio (W1/H1 ≥ 0.5) to balance particle separation efficiency with minimal pressure loss
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 enables efficient separation of particles, such as supercooled icing droplets, with reduced weight and minimal aerodynamic losses, ensuring engine protection without increasing complexity or weight, and maintains low pressure losses under all conditions.
Implementation Method 1
an inertial particle separator configured for communicating with an engine inlet of an aircraft engine having an axis
Data Source
Figure 1
Figure 2
Figure 3
AI summary
There is disclosed an inertial particle separator (100;200) communicating with an engine inlet (I). The inertial particle separator (100;200) has: a main duct (22;122); a bypass duct (24;124); and a splitter (26) defined by an intersection of the main duct (22;122) and the bypass duct (24;124). The main duct (22;122) and the bypass duct (24;124) having particular geometric characteristics. A method of separating particles via inertia in an aircraft engine inlet (I) is also provided.