Adjustable Bleed Stage Apparatus for Aircraft Engine
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Solution Overview
Problem
Existing turbofan engines lack flexible and reconfigurable systems for air bleeding, which affects thrust performance and requires expensive reconfiguration to adjust bleed stages, failing to optimize air extraction for varying aircraft occupancy levels.
Innovation Solution
An adjustable bleed stage apparatus and bleed port selection mechanism that allows for incremental adjustment and selection of bleed stages in turbofan engines, using movable valves and sleeves to control fluid flow through bleed ports, enabling optimal air extraction based on aircraft occupancy without costly reconfiguration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If bleed ports are fixed at predetermined stages, then engine manufacturing is simplified, but adaptability to varying aircraft occupancy levels is reduced
Solution Approach 1:
The patent implements movable sleeves that can be positioned at different locations along the compressor stages, allowing the bleed port configuration to dynamically adapt to varying aircraft occupancy levels and performance requirements, transforming a static system into a reconfigurable one
Solution Approach 2:
The bleed port system is divided into multiple selectable stages along the compressor, with each stage having its own可控 bleed port that can be independently activated or deactivated, enabling flexible configuration without requiring complete system redesign
2Adaptability or versatility
If reconfiguration is performed to adjust bleed stages, then adaptability is improved, but cost and time are increased
Solution Approach 1:
The movable sleeves can be repositioned along the compressor stages without requiring engine disassembly or complex mechanical reconfiguration, enabling rapid adaptation to different operating conditions while minimizing time and cost investments
Solution Approach 2:
The same movable sleeve mechanism serves multiple functions by being able to position at different locations to create bleed ports at various compressor stages, eliminating the need for separate reconfiguration systems for each bleed stage
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 solution enhances engine performance by allowing tailored bleed stage selection before or during operation, optimizing fuel burn and matching aircraft systems' requirements without impacting engine interface, thus improving efficiency and reducing fuel consumption.
Implementation Method 1
movable valves and sleeves to control fluid flow through bleed ports
Data Source
AI summary
An example method to extract bleed air from an aircraft engine includes extracting, via a plenum positioned in a compressor of the aircraft engine, bleed air from a first bleed port associated with a first stage of a compressor and a second bleed port associated with a second stage of the compressor. The plenum is configured to combine the extracted bleed air from the first and second bleed ports and fluidly couple the extracted bleed air to one or more systems of an aircraft. The method includes regulating a pressure of the extracted bleed air in the plenum by adjusting a flow of bleed air through the first bleed port via a first valve associated with the first bleed port and adjusting a flow of bleed air through the second port via a second valve associated with the second bleed port.