Aircraft Anti-icing Nozzle Uniform Heating
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Solution Overview
Problem
Existing anti-icing systems for aircraft propulsion systems face challenges in uniformly heating the inner lip skin of the nacelle inlet, leading to hot spots and inadequate ice prevention.
Innovation Solution
A nozzle design with multiple ports of varying diameters and distances from the outer lip skin, featuring a trunk conduit and branch conduits that inject fluid into an internal cavity, ensuring a uniform distribution of fluid and reducing hot spots by positioning the second branch conduit between the first branch conduit and the inner lip skin.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a single port configuration is used in existing anti-icing nozzles, then the structure is simple, but hot spots occur on the inner lip skin and heating is insufficient
Solution Approach 1:
The nozzle is divided into multiple independent ports (first port, second port, third port) with different configurations. Each port targets specific regions of the inner lip skin, allowing differentiated heating strategies that eliminate hot spots while maintaining overall heating effectiveness.
Solution Approach 2:
Different ports are positioned at different distances from the outer lip skin and have different flow areas to address specific local heating requirements. The first port targets regions farther from the lip skin, while the second and third ports address regions closer to the lip skin, creating locally optimized heating patterns.
2Quantity of substance
If ports are positioned closer to the outer lip skin, then fluid distribution improves, but the distance parameter varies and complicates the design
Solution Approach 1:
The invention systematically varies multiple parameters including port distance from the outer lip skin, flow area of each port, and port orientation angles. This multi-parameter optimization allows achieving uniform fluid distribution while managing positioning complexity through established geometric relationships.
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 nozzle design achieves a more uniform heating of the inlet lip, reducing hot spots and enhancing ice prevention by ensuring a consistent fluid distribution across the cavity, thereby improving the anti-icing performance.
Implementation Method 1
A nozzle configured to direct fluid into the internal cavity through a plurality of ports... achieving a more uniform distribution of fluid
Implementation Method 2
thermal anti-icing system... reducing hot spots on and increasing heating of an inner lip skin... enhancing ice prevention
Data Source
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AI summary
An assembly (48) is provided for an aircraft propulsion system (20). The assembly (48) includes a nacelle inlet structure (32) with an internal cavity (82). The assembly (48) also includes a nozzle (88) configured to direct fluid into the internal cavity (82) through a plurality of ports (100) that include one or more first ports (100A) and at least one second port (100B). The nozzle (88) includes a trunk conduit (94), a first branch conduit (96) and a second branch conduit (98). The first branch conduit (96) and the second branch conduit (98) are fluidly coupled in parallel to the trunk conduit (94). The first branch conduit (96) includes the first port(s) (100A). The second branch conduit (98) includes the second port (100B).