Aircraft Nacelle Acoustic Structure with Integrated De-icing

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Solution Overview

Problem

Existing acoustic treatment structures for aircraft nacelles suffer from air recirculation issues due to pressure gradients, leading to disrupted airflow and inadequate seal-tightness, which complicates the design and increases costs.

Innovation Solution

A single-piece substructure with elongated elements for de-icing and acoustic treatment, featuring partitions in transverse and longitudinal planes, ensures better seal-tightness and simplifies assembly by eliminating the need for complex welding, allowing for seal-tight barriers in two directions.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If caissons are oriented at right angles to the direction of flow and welded to the acoustically resistive substructure, then seal-tightness in the direction of flow is improved, but device complexity and manufacturing cost increase due to complex welding assembly

Engineering Contradiction:

Improveseal-tightnessVSAvoidassembly complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent combines multiple separate components (caissons, partitions, and acoustically resistive substructure) into a single integrated structure. The partitioning substructure is formed as one piece with the acoustically resistive substructure, eliminating the need for separate welding operations to assemble caissons to the substructure. This merging maintains seal-tightness while reducing assembly complexity.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The patent segments the acoustic treatment structure into distinct functional zones using partitions that create separate channels. These partitions are integrated into the single-piece substructure, allowing airflow to be divided into multiple pathways while maintaining overall structural integrity and seal-tightness without requiring complex external assembly.

Inventive Principle:

Principle #1Segmentation

2Reliability

If all caissons are linked and machined to remove material between channels, then seal-tightness is improved, but manufacturing time and cost increase

Engineering Contradiction:

Improveseal-tightnessVSAvoidmanufacturing efficiency

Core Design Contradiction:

ReliabilityVSProductivity

Solution Approach 1:

The patent merges the partitioning function and the structural support function into a single integrated component. The partitioning substructure is formed as one piece with the acoustically resistive substructure, eliminating the need for separate machining operations to remove material between channels. This integration maintains seal-tightness while significantly improving manufacturing efficiency.

Inventive Principle:

Principle #5Merging (Combining)

3Reliability

If caissons are oriented in the direction of flow, then seal-tightness in the transverse direction is improved, but air recirculation and disrupted airflow occur

Engineering Contradiction:

Improveseal-tightnessVSAvoidair recirculation

Core Design Contradiction:

ReliabilityVSObject-generated harmful factors

Solution Approach 1:

The patent applies different structural characteristics to different regions of the acoustic treatment. The partitions are positioned and dimensioned to create specific flow pathways that prevent recirculation in critical areas while maintaining seal-tightness. The acoustically resistive material is distributed selectively within the channels to control airflow patterns locally, preventing harmful recirculation while preserving acoustic performance.

Inventive Principle:

Principle #3Local quality

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 solution effectively addresses air recirculation and seal-tightness issues, reducing complexity and cost while maintaining efficient airflow and acoustic treatment performance.

Implementation Method 1

an acoustically resistive substructure, strips of cells arranged in a direction substantially at right angles to a direction of flow of the air flow entering into the nacelle

Methodology Applied

Scientific EffectAcoustic absorption: Acoustic Absorption

Implementation Method 2

at least one reflective layer

Methodology Applied

Scientific EffectAcoustic reflection: Reflection

Implementation Method 3

there is a pressure gradient in the direction of flow of the air flow on the surface of the acoustically resistive substructure. Because of this pressure gradient, air flows can penetrate into the acoustic structure

Methodology Applied

Scientific EffectPressure gradient: Pressure Gradient

Implementation Method 4

the second layer comprising furrows forming channels in the acoustically resistive substructure when the first and second layers are pressed against one another. According to this embodiment, hot air flows in the channels to ensure the de-icing function

Methodology Applied

Scientific EffectThermal heating: Heating

Data Source

PatentUS10273015B2Compartmentalized structure for the acoustic treatment and the de-icing of an aircraft nacelle and aircraft nacelle incorporating said structure

Publication Date: 2019.04.30 AIRBUS OPERATIONS (SAS)

AI summary

An acoustic structure for an aircraft nacelle which comprises an acoustically resistive substructure, at least one layer of cells and a reflective layer. The acoustic structure comprises at least one single-piece substructure which divides up the layer of cells and which incorporates elongated elements of a de-icing system.