Multi-Direction Bleed Valve for Vertical Lift Thrust Control
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Solution Overview
Problem
Existing aircraft propulsion systems face challenges in efficiently transitioning between horizontal and vertical propulsion modes, as generating horizontal thrust with the first propulsor rotor during vertical operations hinders lift and reduces engine core power available for vertical lift.
Innovation Solution
A bleed circuit and flow regulator system that selectively directs bypass gas into the core flowpath to supplement core gas pressure, reducing horizontal thrust during vertical operations and maintaining engine core power.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If the first propulsor rotor generates horizontal thrust during vertical operations, then forward propulsion capability is maintained, but vertical lift is hindered and engine core power is reduced
Solution Approach 1:
The patent extracts and removes the harmful horizontal thrust component by using a bleed circuit to siphon bypass gas that would otherwise contribute to horizontal propulsion. This extracted gas is redirected into the core flowpath, effectively separating the harmful horizontal thrust generation from the vertical lift generation, allowing the first propulsor rotor to be optimized for vertical operations without the detrimental effect of horizontal thrust interference
Solution Approach 2:
The patent introduces bypass gas as an intermediary substance that mediates between the first propulsor rotor and the core flowpath. By redirecting this intermediary gas through the bleed circuit into the core flowpath, the system adjusts the interaction between the propulsor rotor and core gas, thereby reducing horizontal thrust interference while maintaining or enhancing vertical lift capabilities
2Power
If bypass gas is redirected into the core flowpath, then core gas pressure is supplemented and engine core power is maintained, but system complexity increases due to the bleed circuit and flow regulator
Solution Approach 1:
The flow regulator is designed as a multi-functional component that serves both as a valve for redirecting bypass gas and as a control element for managing core flowpath pressure. This universal component performs multiple functions (flow regulation, pressure control, gas redirection) within a single device, thereby supplementing engine core power through bypass gas redirection while minimizing the increase in overall system complexity
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
Enhances vertical lift capabilities by reducing horizontal thrust interference and optimizing engine core power distribution for dual-direction propulsion modes.
Implementation Method 1
directs bypass gas into the core flowpath to supplement core gas pressure
Data Source
Figure 1
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AI summary
An assembly for an aircraft propulsion system (20) includes an engine core (26), a bypass duct (58) and a bleed circuit (102). The engine core (26) includes a compressor section (48), a combustor section (49), a turbine section (50) and a core flowpath (90). The bypass duct (58) includes a bypass flowpath (60) outside of the engine core (26). The bleed circuit (102) includes a bleed passage (112) and a flow regulator (114) and is configured to direct bypass gas through the bleed passage (114) from the bypass flowpath (60) into the core flowpath (90) when the flow regulator (114) is in an open position. The bleed circuit (102) is configured to cutoff gas flow through the bleed passage (114) between the bypass flowpath (60) and the core flowpath (90) when the flow regulator (114) is in a closed position.