Variable Area Nozzle Woven Sleeve Extension
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Solution Overview
Problem
Conventional gas turbine engines face inefficiencies due to fixed design constraints that lead to suboptimal operation under varying flight conditions, particularly during take-off and landing, resulting in increased fuel burn and reduced performance.
Innovation Solution
A variable area fan nozzle system that can change its axial length to control the effective area of the fan bypass passage, using woven members that open or close to manage airflow, allowing for adjustable bypass airflow control across different flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the fan and bypass airflow ratio are designed for take-off conditions, then the bypass flow pressure ratio is maintained to prevent choking during take-off, but the fuel burn increases during cruise operation
Solution Approach 1:
The patent applies a variable area nozzle that can dynamically change its cross-sectional area to control bypass airflow. The nozzle includes movable panels or flaps that adjust the flow area based on flight conditions, enabling the system to adapt between take-off and cruise modes rather than being fixed for a single condition.
Solution Approach 2:
The invention changes the geometric parameter of the nozzle area to optimize performance across different flight conditions. By varying the nozzle area, the system adjusts the bypass airflow rate and pressure ratio, allowing efficient operation during both take-off (preventing choking) and cruise (reducing fuel burn).
2Productivity
If a fixed nozzle design is used, then the engine operates efficiently under predetermined cruise conditions, but performance degrades under varying flight conditions such as take-off and landing
Solution Approach 1:
The patent transforms the fixed nozzle into a dynamic component with adjustable area. The nozzle incorporates movable elements such as panels, flaps, or woven members that can change the flow area in real-time, enabling the engine to maintain optimal efficiency across varying flight conditions including take-off, cruise, and landing.
Solution Approach 2:
The variable area nozzle serves multiple functions: it prevents bypass flow choking during take-off, maintains efficient cruise operation, and adapts to landing conditions. This single component handles multiple operational requirements that would otherwise require different fixed designs.
3Use of energy by moving object
If the bypass airflow is reduced during cruise, then fuel burn improves, but the engine cannot maintain desired pressure ratio during take-off
Solution Approach 1:
The variable area nozzle dynamically adjusts the bypass flow area to maintain appropriate pressure ratios across different flight conditions. During take-off, the nozzle opens to increase flow area and maintain pressure ratio; during cruise, it reduces the area to optimize fuel burn while maintaining sufficient flow.
Data Source
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AI summary
The invention relates to gas turbine engines and a method for controlling gas turbine engines. The gas turbine engine having a variable area fan nozzle (40) including a nozzle section that is attachable to the gas turbine engine for influencing flow through the fan bypass passage (30) of the gas turbine engine. The nozzle section (40) is movable between a first length (60) and a second length (60') that is larger than the first length (60) to influence the flow. For example, the nozzle section includes members (56) that are woven together to form collapsible openings (66) that are open when the nozzle section (40) is moved to the first length (60) and that are closed when the nozzle section is moved to the second length (60').