Segmented Mixing Nozzle for Aircraft Fuel Tank Inerting

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Solution Overview

Problem

Conventional fuel tank inerting systems face challenges in achieving efficient oxygen reduction in aircraft fuel tanks while maintaining low system pressure loss and resistance to contamination from particulate matter.

Innovation Solution

The design includes a nozzle with radially defined gas and liquid flow paths, a core conduit, and swirl vanes, which facilitates a mixing zone with an air-to-liquid ratio of 400:1, minimizing pressure drop and using a dual gas source system with a converging non-swirling outer gas flow path and a diverging swirling inner gas flow path, along with a catalytic reactor to reduce oxygen levels.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If conventional fuel tank inerting systems are used, then oxygen reduction function is provided, but pressure loss is high and resistance to contamination is insufficient

Engineering Contradiction:
Improveresistance to contaminationVSAvoidpressure loss
Core Design Contradiction:
ReliabilityVSLoss of energy

Solution Approach 1:

The gas flow path is segmented into multiple regions: an outer gas flow path for main gas flow and an inner gas flow path for secondary gas flow. This segmentation allows different gas streams to be introduced separately, improving mixing efficiency while reducing overall pressure loss. The liquid flow path is also segmented with multiple liquid injectors distributed around the periphery, enabling uniform liquid distribution without requiring high pressure

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

A vaporization chamber is introduced as an intermediary component between the liquid injectors and the catalytic reactor. This chamber provides a dedicated space for fuel vaporization and gas-liquid mixing before the mixture enters the catalytic converter, improving combustion efficiency while allowing the system to operate at lower pressures. The chamber acts as a buffer that facilitates the phase change and mixing processes

Inventive Principle:
Principle #24Intermediary (Mediator)

2Productivity

If mixing efficiency is improved, then oxygen reduction effectiveness increases, but system complexity increases

Engineering Contradiction:
Improveoxygen reduction effectivenessVSAvoidsystem complexity
Core Design Contradiction:
ProductivityVSDevice complexity

Solution Approach 1:

Multiple functions are merged into a single integrated nozzle assembly: gas flow distribution, liquid injection, vaporization, and mixing all occur within one compact component. The outer and inner gas flow paths are combined in a concentric arrangement, and multiple liquid injectors are integrated into the nozzle body. This merging achieves high mixing efficiency while minimizing the number of separate components

Inventive Principle:
Principle #5Merging (Combining)

Solution Approach 2:

The vaporization chamber serves multiple functions simultaneously: it provides a mixing zone for gas and liquid, a vaporization chamber for fuel, a flow distribution chamber for uniform mixture delivery, and a pressure equalization volume. This multi-functionality improves oxygen reduction effectiveness without requiring additional separate components for each function

Inventive Principle:
Principle #6Universality (Multi-functionality)

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

This configuration ensures efficient fuel vaporization and mixing with minimal pressure loss, effective oxygen reduction, and resistance to contamination, maintaining low reactivity in the fuel tank ullage while maintaining system efficiency and durability.

Implementation Method 1

At least one of the inner heat shield or a core nozzle shell can include swirl vanes extending therefrom. The inner gas flow path can be a diverging swirling gas flow path.

Methodology Applied
Scientific EffectSwirl flow: Vortex Ring

Implementation Method 2

At least one of the inner diameter liquid distributor or the outer diameter liquid distributor can include helical threads. Helical threads can be defined on a cylindrical surface of at least one of the inner diameter liquid distributor or the outer diameter liquid distributor.

Methodology Applied
Scientific EffectHelical flow: Helix

Implementation Method 3

an inerting system includes a duct, an injector assembly positioned within the duct. The injector assembly includes a nozzle... a catalytic reactor positioned within the duct downstream from the injector assembly

Methodology Applied
Scientific EffectCatalysis: Catalysis

Data Source

PatentEP3715604A1Mixing nozzle for a catalytic fuel tank inerting system for an aircraft
Publication Date: 2020.09.30 COLLINS ENGINE NOZZLES INC
  • EP3715604A1 patent drawingFigure 1~2A
  • EP3715604A1 patent drawingFigure 2B~2C
  • EP3715604A1 patent drawingFigure 3

AI summary

A nozzle (100) includes an outer gas flow path (128), an inner gas flow path (130) radially inward from the outer gas flow path (132), a liquid flow path defined radially between the inner gas flow path and the outer gas flow path, and a core conduit (134) defined radially inward from the inner gas flow path. An injector assembly (104) includes an outer housing (112), a nozzle (101) within the outer housing (112), and an outer housing gas flow path (114) defined radially outward from the nozzle between an inner surface of the outer housing (112) and an outer surface of the nozzle (101). The nozzle (101) includes an outer gas flow path (128), an inner gas flow path (130) radially inward from the outer gas flow path (128), a liquid flow path (132) defined radially between the inner gas flow path (130) and the outer gas flow path (128) and a core conduit (134) defined radially inward from the inner gas flow path (130).