Turbine Air Intake Deflecting Foreign Objects
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aeronautical turbine engines without a propeller rotor upstream of the air inlet are vulnerable to damage from foreign objects like birds, hail, and stones, as existing protection methods either lead to unfavorable mass and size dimensions or compromise aerodynamic performance.
Innovation Solution
An air inlet design featuring a deflection member and a secondary deflection channel with a decreasing cross-sectional area, redirecting foreign objects away from the main engine air supply channel, maintaining aerodynamic performance while reducing the energy of ingested objects before they reach the compressor.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the first stages of the compressor are reinforced to withstand foreign object impacts, then engine protection against foreign objects is improved, but the mass and size of the engine increase unfavorably
Solution Approach 1:
The patent extracts the foreign object deflection function from the compressor stages and relocates it to a dedicated deflection channel upstream of the compressor. This separates the protection function from the compression function, allowing the compressor to be lighter while still protected against foreign objects.
Solution Approach 2:
The patent introduces a deflection channel as an intermediary structure between the air inlet and the compressor. This intermediary component handles foreign object deflection, preventing them from reaching the compressor stages, thereby protecting the engine without requiring reinforcement of the compressor itself.
2Reliability
If a deflection channel with nozzles is used to eject fluid and accelerate deflected flow, then foreign object deflection is improved, but the device complexity increases
Solution Approach 1:
The patent extracts the complex nozzle system from the deflection channel design and replaces it with a simpler geometry that relies on flow dynamics rather than active ejection mechanisms. This simplifies the structure while maintaining deflection effectiveness.
Solution Approach 2:
The deflection channel is designed to utilize the kinetic energy of the incoming air flow itself to deflect foreign objects, rather than requiring additional energy input from nozzles. The channel geometry naturally guides the flow to achieve deflection without complex active systems.
3Speed
If the cross section of the secondary channel is decreased from inlet to outlet, then air flow velocity is increased and aerodynamic performance is maintained, but the design complexity increases
Solution Approach 1:
The patent applies different cross-sectional characteristics to different regions of the deflection channel. The upstream portion has a larger cross-section for capturing foreign objects, while the downstream portion tapers to a smaller cross-section to accelerate flow. This local differentiation optimizes both protection and aerodynamic performance.
Solution Approach 2:
The deflection channel employs curved and tapered geometries rather than abrupt transitions. The smooth curvature of the channel walls gradually reduces the cross-section area from inlet to outlet, maintaining flow attachment and preventing shock waves while achieving the desired velocity increase.
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 design effectively deflects foreign objects, reducing their energy to prevent damage to the engine while maintaining aerodynamic performance and minimizing overall drag, and allows for easier maintenance and reduced engine mass.
Implementation Method 1
the secondary deflection channel has a section transverse to the direction of flow of the air having a decreasing area between the air inlet formed in part by the ridge and the outlet of the secondary channel formed by the opening so that the flow velocity of the air passing through the secondary channel is increased from upstream to downstream
Data Source
Figure 1~2
Figure 3
Figure 4~5
AI summary
The present invention relates to an assembly comprising a gas turbine engine (10) and a nacelle (26) in which the engine is housed, the nacelle including an air intake fairing (26a) that forms an air inlet and includes: a member for deflecting (40) foreign objects, which, together with said fairing, forms an air intake duct (41); and, downstream from the deflecting member, a secondary deflecting channel (43); and a main (42) channel for supplying air to the engine. Said air intake duct (41) is designed to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel (43). The secondary deflecting channel (43) is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening (43a) leading into the outer wall of the nacelle (26).