Dynamic Air Intake Grid Translation for Icing Blockage
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft turbine engines face significant power reduction due to icing conditions, as frost blocks the protective grille of dynamic air intakes, leading to incomplete air flow and lack of means for pilots to assess clogging, necessitating oversized grids with detrimental aerodynamic characteristics.
Innovation Solution
A versatile air inlet system with a dynamic inlet duct and a movable protective grid that translates away from the frontal passage section upon clogging, allowing the side inlet to open and maintain airflow, equipped with heating and damping mechanisms to prevent sticking and ensure smooth operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a protective grille is installed at the dynamic air inlet to prevent bird ingestion, then engine safety is improved, but the grille becomes blocked by frost in icing conditions, causing air flow reduction and power loss
Solution Approach 1:
The air inlet system is segmented into multiple independent air inlet paths: a dynamic air inlet with protective grille and static air inlets without grilles. This segmentation allows the system to maintain air flow through alternative paths when the dynamic inlet is blocked by frost, while the protective grille continues to provide bird ingestion protection at the dynamic inlet.
2Productivity
If an oversized grid is used to prevent complete blockage in icing conditions, then minimum air flow is maintained, but the grid geometry becomes detrimental to aerodynamic performance
Solution Approach 1:
Instead of using a single oversized grid that compromises aerodynamics, the system segments the air inlet function across multiple inlets of normal size. The dynamic inlet with its properly sized grille maintains optimal aerodynamic characteristics, while static inlets provide backup capacity during icing conditions without requiring geometric modifications to the main grille.
3Reliability
If the dynamic inlet is completely closed off to prevent bird ingestion, then engine safety is improved, but air flow through the inlet is blocked, requiring alternative filtration methods
Solution Approach 1:
The air inlet system is divided into a dynamic inlet component dedicated to bird protection and static inlet components dedicated to air flow supply. This functional segmentation allows the dynamic inlet to be closed or blocked without affecting overall air flow, as the static inlets continue to supply air to the engine.
Solution Approach 2:
The air inlet system provides multiple functions through different inlet types: the dynamic inlet offers superior bird protection while the static inlets ensure continuous air flow. Together, they create a multi-functional air intake system that addresses both bird ingestion protection and air flow requirements under various operating conditions including icing.
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
Enables aircraft to operate in icing conditions without performance degradation, providing pilots with clogging information and ensuring continuous air flow by adjusting the side inlet to compensate for grille blockage, thus maintaining turbine engine power and safety.
Implementation Method 1
a heating means, arranged inside the dynamic inlet duct, capable of melting the frost accumulated on the grid
Implementation Method 2
a damping means arranged inside the dynamic inlet duct, capable of reducing the translation speed of the grid
Data Source
Figure 1~4
Figure 5~6
AI summary
The inlet has a dynamic inlet duct (30) provided with a grid (40) for protection against ingesting foreign bodies. The grid is moved in translation along a dynamic axis (AX1) relative to a front flow section of the duct. A lateral inlet is arranged in a side wall. A covering unit (41) covering the lateral inlet is movable relative to the lateral inlet. A displacement unit (60) allows movement of the covering unit relative to the lateral inlet during movement in translation of the grid. An independent claim is also included for a method for optimizing operation of a turbine engine of an aircraft.