Pneumatic By-Pass Door for Aircraft Engine Bleed Air Control
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Solution Overview
Problem
Existing aircraft engine inlet barrier filter systems face clogging issues during flight, leading to potential power loss and operational limitations, with current by-pass air systems relying on complex and potentially faulty electrical actuators for quick failure detection and response.
Innovation Solution
A by-pass air system using pneumatic actuators driven by bleed air from gas turbine engines to control by-pass doors, eliminating the need for electrical power and simplifying the system, allowing for faster response to engine failures by rerouting bleed air to maintain engine power output.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If electrical actuators are used to control by-pass doors, then the system can detect and respond to engine failures, but the system complexity increases and reliability decreases due to potential electrical faults
Solution Approach 1:
The patent removes electrical actuators and control systems from the by-pass door mechanism, extracting the problematic electrical components while retaining the essential function of by-pass air flow control. The by-pass door is simplified to a pure mechanical/pneumatic system that opens automatically when needed, eliminating electrical complexity and potential electrical failures.
Solution Approach 2:
The by-pass door system is designed to be self-actuating through pneumatic pressure differentials. When the main air inlet filter becomes clogged, the pressure differential automatically triggers the by-pass door to open without requiring external electrical control signals, making the system self-regulating and more reliable.
2Speed
If electrical actuators are used for by-pass door control, then failure detection is possible, but response time increases due to electrical system latency
Solution Approach 1:
The patent replaces electrical actuation systems with a direct pneumatic actuation system. Pneumatic actuators respond more quickly to pressure changes than electrical systems can respond to sensor signals and control commands, reducing the overall response time for by-pass door activation during engine failures.
Solution Approach 2:
The pneumatic actuation system is pre-configured with pressure sensors and actuator positioning that prepare the by-pass door for immediate opening. The system maintains readiness through pre-charged pneumatic lines and pre-positioned door mechanisms, enabling faster response compared to electrical systems that must process signals and activate motors sequentially.
3Ease of operation
If electrical power supply systems are installed for by-pass control, then actuator control is enabled, but the system requires additional electrical infrastructure that increases complexity
Solution Approach 1:
The patent extracts all electrical power supply requirements from the by-pass door control system. The pneumatic actuation system operates independently of electrical power, using only the existing pneumatic infrastructure already present in aircraft engine systems, thereby eliminating the need for additional electrical infrastructure.
Solution Approach 2:
The pneumatic actuation system leverages the existing multi-functional pneumatic infrastructure in aircraft engines, which is already used for various engine control functions. By using this existing pneumatic system for by-pass door control, the invention avoids adding new infrastructure while maintaining full control capability.
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 pneumatic by-pass air system reduces latency in engine response, enhances operational safety, and complies with strict certification regulations by providing a reliable and efficient means to maintain power output during engine failures without requiring electrical power supplies.
Implementation Method 1
controllable by the outgoing bleed air stream that goes out of the at least one second engine in operation
Data Source
AI summary
An aircraft having at least one first and one second engine, each engine comprising a main air inlet opening, a by-pass air inlet opening and a bleed air outlet, said main air inlet opening being provided with an inlet barrier filter for filtering a main air stream through said main air inlet opening into the engine, said by-pass air inlet opening being provided with a by-pass door that is operable by an associated operating element to enable a by-pass air stream through said by-pass air inlet opening into the engine, and said bleed air outlet being provided for creating an outgoing bleed air stream going out of the engine in operation, at least one associated operating element being controllable by an outgoing bleed air stream.