Aircraft Structure Vent Layout for Cooling Surface-Bound Gas

Solution Overview

Problem

Existing engine bleed air based thermal anti-icing systems for aircraft structures face issues with high exit temperatures, leading to increased weight and design complexity due to the use of metallic doors, which are necessary to withstand these temperatures.

Innovation Solution

Aircraft structure design featuring a first exhaust vent configured to exhaust a stream of gas that attaches to the surface and a second vent that disrupts ambient airflow, creating a mixing effect to cool the first stream before it attaches to the surface, utilizing fibre-reinforced composite materials downstream.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If a metallic door is used to withstand high exit temperatures, then the structure can handle thermal loads, but the weight and design complexity increase

Engineering Contradiction:

Improveexit temperatureVSAvoiddoor weight

Core Design Contradiction:

TemperatureVSWeight of stationary object

Solution Approach 1:

The invention changes the material parameter from metallic to fibre-reinforced composite, enabling the structure to withstand high temperatures without requiring heavy metallic protection. The composite material's thermal and mechanical properties are optimized to handle the thermal loads from exhaust gases.

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The invention uses a lightweight composite door that can be replaced more easily and cheaply than heavy metallic doors, trading durability for weight savings. The composite material allows for simpler manufacturing and replacement procedures.

Inventive Principle:

Principle #27Cheap short-living objects (Disposable)

2Temperature

If a metallic door is used to withstand high exit temperatures, then the structure can handle thermal loads, but the design and manufacturing complexity increase

Engineering Contradiction:

Improveexit temperatureVSAvoiddesign and manufacturing complexity

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

The invention changes the material parameter from metallic to fibre-reinforced composite, enabling the structure to withstand high temperatures without requiring complex metallic protection systems. The composite material's thermal and mechanical properties are optimized to handle the thermal loads from exhaust gases.

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The invention uses a lightweight composite door that can be replaced more easily and cheaply than heavy metallic doors, trading durability for weight savings. The composite material allows for simpler manufacturing and replacement procedures.

Inventive Principle:

Principle #27Cheap short-living objects (Disposable)

3Reliability

If hot bleed air is exhausted directly onto the surface, then anti-icing protection is provided, but thermal damage to components occurs

Engineering Contradiction:

Improveanti-icing protectionVSAvoidthermal damage

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The invention introduces fibre-reinforced composite material as an intermediary between the hot bleed air and the structural components. This composite layer acts as a thermal buffer, allowing the hot air to contact the leading edge for anti-icing while preventing excessive heat transfer to the internal structure.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The invention changes the material parameter from metallic to fibre-reinforced composite, enabling the structure to withstand high temperatures without requiring complex metallic protection systems. The composite material's thermal and mechanical properties are optimized to handle the thermal loads from exhaust gases.

Inventive Principle:

Principle #35Parameter changes

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 reduces thermal damage to aircraft components by achieving a significant temperature drop of up to 280°C, minimizing weight and design complexity while maintaining structural integrity.

Implementation Method 1

the second stream of gas disrupts the ambient airflow over the aircraft structure to generate a disrupted ambient airflow which mixes with the first stream of gas

Methodology Applied

Scientific EffectMixing:

Implementation Method 2

the second stream of gas disrupts the ambient airflow over the aircraft structure to generate a disrupted ambient airflow which mixes with the first stream of gas, thereby cooling the first stream of gas

Methodology Applied

Scientific EffectConvection: Convection

Data Source

PatentUS20250304266A1Cooling of gas flowing over aircraft structure

Publication Date: 2025.10.02 AIRBUS (SAS)

AI summary

An aircraft structure configured to be exposed to an ambient airflow which flows over the structure in an airflow direction. The aircraft structure includes: a first exhaust vent configured to exhaust a first stream of gas into the ambient airflow; and a second exhaust vent configured to exhaust a second stream of gas into the ambient airflow. The first exhaust vent is positioned downstream of the second exhaust vent in the airflow direction, the first exhaust vent is positioned in line with the second exhaust vent relative to the airflow direction, and the first exhaust vent has a larger area than the second exhaust vent.