Aircraft Propulsion Drain Assembly Using Pressurized Fluid Expulsion
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Solution Overview
Problem
Existing aircraft propulsion systems lack an effective drain system for routing leakage fluids away from components of a gas turbine engine, particularly in O-duct nacelles without a lower bifurcation, which can lead to inefficiencies and potential damage during maintenance.
Innovation Solution
A drain system comprising a first drain tube, a second drain tube, a container, and a gas tube, where the container is fluidly coupled between the first and second drain tubes, and a pressure source is used to pressurize the container, directing leakage fluids from the gas turbine engine into the overboard drain tube for expulsion from the system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a traditional drain system with lower bifurcation and drain mast is used, then leakage fluids can be routed away from gas turbine engine components, but the system becomes structurally complex and cannot be used in O-duct nacelles
Solution Approach 1:
The drain system is segmented into separate functional components: a drain tube for fluid collection, a container for fluid storage, and a gas tube for pressurization. This segmentation eliminates the need for complex integrated structures like lower bifurcations and drain masts, while maintaining effective leakage fluid routing capability.
Solution Approach 2:
A container is introduced as an intermediary element between the drain tube and the external environment. This container receives leakage fluids from the drain tube and allows for controlled discharge, simplifying the overall system architecture while enabling effective fluid management in O-duct nacelle configurations.
2Device complexity
If the drain system uses gravity-dependent routing, then the system structure is simple, but it cannot effectively drain fluids in all aircraft orientations and positions
Solution Approach 1:
The system employs pneumatic pressure through the gas tube to propel leakage fluids from the container. This pressurization mechanism enables effective fluid drainage independent of gravitational orientation, allowing the system to function reliably in all aircraft positions while maintaining relatively simple structural components.
Solution Approach 2:
The drain system transitions from a static, gravity-dependent design to a dynamic, pressure-driven system. The gas tube introduces active pressurization that adapts to various aircraft orientations, ensuring consistent drainage performance regardless of the aircraft's position or attitude during operation.
3Ease of repair
If the container is made transparent for visual inspection, then maintenance accessibility is improved, but the container strength and pressure containment capability are reduced
Solution Approach 1:
The container is designed with local quality variations: transparent or translucent sections in areas requiring visual inspection, and opaque, higher-strength sections in areas requiring maximum pressure containment. This localized differentiation allows the container to provide both visual accessibility for maintenance and sufficient structural integrity for pressure containment.
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 system effectively routes and expels leakage fluids from the aircraft propulsion system, preventing fluid accumulation and potential damage, while allowing for visual inspection and maintaining system efficiency without the need for a lower bifurcation or drain mast, thus enhancing operational reliability and reducing maintenance complexities.
Implementation Method 1
The pressure source is configured to pressurize the container with pressurized gas such that the leakage fluid within the container is directed into the overboard drain tube
Implementation Method 2
The gas tube is configured to direct gas into the container for propelling the fluid received within the container into the second drain tube
Data Source
AI summary
An assembly is provided for an aircraft propulsion system. This assembly includes a first drain tube, a second drain tube, a container and a gas tube. The container fluidly couples the first drain tube to the second drain tube. The container is configured to receive fluid from the first drain tube. The gas tube is fluidly coupled with the container. The gas tube is configured to direct gas into the container for propelling the fluid received within the container into the second drain tube.