Turbine Nacelle Air Intake De-Icing Channel for Thin Supersonic Inlets
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Solution Overview
Problem
Existing de-icing systems for aircraft turbomachine air intakes are complex, bulky, and inefficient, particularly for supersonic aircraft with thin, long air intakes, leading to increased mass, cost, and complexity.
Innovation Solution
A de-icing system with a non-telescopic upstream pipe and a telescopic downstream element, where the telescopic element is positioned downstream to minimize space constraints, allowing for a reduced thickness and dual function of movement and de-icing, using misalignment compensation devices to mitigate inaccuracies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a telescopic defrosting circuit with large diameter outer cylinder is used to effectively defrost the movable upstream portion, then de-icing performance is improved, but the thickness of the air inlet increases and becomes incompatible with thin air intakes of supersonic aircraft
Solution Approach 1:
The defrosting circuit is divided into multiple separate circulation pipes instead of using a single large diameter telescopic pipe. Each circulation pipe carries a portion of the hot air flow, allowing the system to achieve effective de-icing while maintaining a thin profile compatible with supersonic aircraft air intakes
Solution Approach 2:
The circulation pipes are arranged in a nested or bundled configuration within the limited space of the thin air inlet structure, allowing multiple pipes to occupy minimal space while collectively providing sufficient hot air flow for effective defrosting of the movable upstream portion
2Reliability
If the number of circulation lines is increased to compensate for reduced diameter, then de-icing effectiveness is maintained, but mass, cost, and complexity increase
Solution Approach 1:
The circulation pipes serve dual functions: they convey hot air for de-icing purposes and simultaneously act as structural elements within the air inlet assembly. This multi-functionality reduces the need for additional dedicated de-icing components, thereby limiting the increase in complexity despite using multiple circulation lines
3Speed
If the air inlet thickness is reduced for supersonic aircraft performance, then aerodynamic performance is improved, but the space available for accommodating defrosting circuits is insufficient
Solution Approach 1:
The circulation pipes are arranged in a three-dimensional configuration that efficiently utilizes the limited volume available in the thin air inlet structure. By optimizing the spatial arrangement in multiple dimensions rather than simply increasing cross-sectional area, the system accommodates sufficient hot air flow pathways within the constrained thickness
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 system achieves efficient de-icing performance with reduced thickness and mass, enhancing aerodynamic performance and simplifying maintenance for supersonic aircraft.
Implementation Method 1
the defrosting circuit is configured to circulate a flow of hot air in the circulation pipe so as to inject a flow of hot air into the upstream movable part
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake comprising a movable upstream portion (2a) and a stationary downstream portion (2b), at least one controllable movement member for moving the movable upstream portion (2a) between a retracted position (PR) and an extended position in order to enable circulation of an air flow passing between the movable upstream portion (2a) and the stationary downstream portion (2b), at least one de-icing circuit (5) comprising at least one circulation channel (50) fluidically connecting the movable upstream portion (2a) and a hot air source (SAC), the circulation channel (50) comprising at least one non-telescopic upstream pipe (51) and at least one telescopic downstream member (52).