Nose Cone Fluid Injection for Aircraft Engine Particle Separation
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Solution Overview
Problem
Particles such as sand, dust, and chemicals entering aircraft turbine engines cause surface erosion, corrosion, and clogging of cooling holes and passages, primarily during takeoff and landing, as existing systems only clean surfaces and not the air entering the engine.
Innovation Solution
An entrained particle removal (EPR) system that injects a fluid from nozzles on the nose cone to wet particles, utilizing centrifugal forces to direct them radially outward of the compressor inlet, either into the bypass duct or outside the engine enclosure, controlled by a system that senses particle presence and adjusts fluid flow based on flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If particles are cleaned only from surfaces of nacelle and engine components, then surface cleanliness is improved, but particles in the air passing into the turbine engine remain harmful
Solution Approach 1:
The system performs preliminary particle removal by injecting fluid onto particles before they enter the compressor inlet. The fluid injection system is positioned upstream of the compressor to wet particles in advance, allowing them to be separated by centrifugal force before entering the engine core, thus preventing contamination rather than cleaning after entry
Solution Approach 2:
A fluid (water or other liquid) is introduced as an intermediary substance to facilitate particle removal. The fluid wets the particles, increasing their mass and allowing centrifugal forces to effectively separate them from the airflow. This intermediary medium enables particle removal without requiring complex mechanical filtration systems
2Reliability
If fluid is injected to wet particles for removal, then particle separation effectiveness is improved, but fluid consumption and system complexity increase
Solution Approach 1:
The system applies partial action by injecting fluid only during specific flight conditions when particle contamination is most likely (takeoff, landing, taxiing). The controller activates the fluid injection system based on detected particle concentrations or flight phase, rather than operating continuously, thus reducing overall fluid consumption while maintaining effective particle removal when needed
Solution Approach 2:
The system changes operational parameters by adjusting fluid injection rates based on particle concentration levels and flight conditions. The controller modulates the fluid flow rate to match the severity of contamination risk, using higher flow rates when particle concentrations are high and lower or zero flow rates when contamination risk is minimal, optimizing fluid usage efficiency
3Reliability
If the EPR system operates during all flight segments, then particle protection is continuous, but energy consumption and operational complexity increase
Solution Approach 1:
The system implements periodic action by operating the fluid injection system only during specific flight segments when particle contamination risk is elevated. The controller activates the system during takeoff, landing, and taxiing segments, and deactivates it during cruise and other low-risk phases, providing targeted protection when needed while minimizing energy consumption during normal operations
4Area of stationary object
If multiple nozzles are used around the nose cone circumference, then particle coverage is improved, but device complexity and manufacturing cost increase
Solution Approach 1:
The system divides the particle removal function into multiple discrete nozzles distributed around the nose cone circumference. Each nozzle handles a specific angular sector, collectively providing comprehensive coverage. This segmentation allows for modular design and assembly, where nozzles can be individually positioned and adjusted to optimize coverage patterns for different flight conditions
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
Effectively prevents particles from entering the core gas path, reducing erosion and corrosion, and maintaining engine efficiency by diverting them into bypass ducts or outside the engine, thus protecting critical components.
Implementation Method 1
The particles wetted by the injected fluid are subject to centrifugal force in and aft of the fan section and are directed radially outward of the compressor inlet
Implementation Method 2
The particles wetted by the injected fluid are subject to centrifugal force in and aft of the fan section and are directed radially outward of the compressor inlet
Data Source
AI summary
A method of directing particles entrained within an airflow disposed to enter a gas turbine engine of an aircraft is provided. The gas turbine engine includes a nose cone, a fan section, a compressor inlet, a compressor section, and a turbine section. The nose cone is fixed for rotation with the fan section. The method includes: providing an entrained particle removal (EPR) system configured to inject a fluid outward from the nose cone from a plurality of nozzles engaged with the nose cone, wherein the nozzles are spaced apart from one another around a circumference of the nose cone; and controlling the EPR system to inject the fluid from the plurality of nozzles into the airflow. The particles wetted by the injected fluid are subject to centrifugal force in and aft of the fan section and are directed radially outward of the compressor inlet.