Segmented Variable Area Nozzle Panels for Aircraft Propulsion Efficiency
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Solution Overview
Problem
Existing variable area nozzle apparatuses for aircraft propulsion systems require improvements to enhance operational efficiency, particularly as fan pressure ratios decrease and/or bypass pressure ratios increase.
Innovation Solution
A variable area nozzle apparatus configured with inner and outer skins, each comprising panels and inter-panel members, which can move between restricted and unrestricted flow arrangements to adjust the outlet area, facilitated by an actuation system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If variable area nozzle apparatuses are used to control flow area, then operational efficiency can be optimized, but device complexity increases
Solution Approach 1:
The nozzle apparatus is divided into multiple discrete panels (first panel, second panel, third panel, fourth panel) that can independently move between restricted and unrestricted positions. Each panel is connected to the support structure through separate actuation mechanisms, allowing independent control of flow area segments. This segmentation enables precise control of exhaust flow while distributing the complexity across multiple simple, modular components rather than one complex mechanism.
Solution Approach 2:
The nozzle apparatus employs movable panels that can dynamically transition between restricted and unrestricted flow arrangements based on operating conditions. The panels are connected to the support structure through joints that allow angular movement, enabling the nozzle area to be variably adjusted during operation. This dynamic capability allows the system to optimize operational efficiency across different flight regimes while maintaining a relatively simple static structure.
2Adaptability or versatility
If panels are movably connected to support structure, then outlet area can be adjusted, but manufacturing precision requirements increase
Solution Approach 1:
The nozzle is segmented into multiple panels that can be manufactured as separate, standardized components with consistent connection interfaces. Each panel is movably connected to the support structure through identical joint mechanisms, allowing for modular assembly and reducing the need for high-precision custom manufacturing. The segmented design enables outlet area adjustment while maintaining manageable manufacturing tolerances across repeated components.
Solution Approach 2:
The support structure serves multiple functions: it provides structural support for the nozzle panels, acts as a mounting framework for actuators, and serves as a reference geometry for panel positioning. The joints connecting panels to the support structure are designed as universal connections that accommodate angular movement while maintaining sealed flow paths. This multi-functionality reduces the number of separate components needed and simplifies manufacturing requirements.
Data Source
Figure 1
Figure 2A~2B
Figure 3
AI summary
An apparatus for an aircraft propulsion system includes a variable area nozzle apparatus (66). The variable area nozzle apparatus (66) includes a plurality of panels (76), a plurality of inter-panel members (78) and an actuation system (74). The panels (76) are arranged circumferentially about an axial centerline (32). The panels (76) include a first panel (76A) and a second panel (76B). The inter-panel members (78) are arranged circumferentially about the axial centerline (32). The inter-panel members (78) include a first inter-panel member (78) between and connected to the first panel (76A) and the second panel (76B). The first inter-panel member (78) is configured from or otherwise includes an elastomeric material. The actuation system (74) is configured to move the panels (76) and the inter-panel members (78) between a restricted flow arrangement and an unrestricted flow arrangement. The actuation system (74) includes a first linkage (110) and a second linkage (110). The first linkage (110) is coupled to the first panel (76A). The second linkage (110) is coupled to the second panel (76B).