Actuation Mechanism for Supersonic Nozzle Thrust Vectoring
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Solution Overview
Problem
Existing thrust vectoring variable geometry nozzles for gas turbine engines face challenges in controlling the geometry of the throat and exit areas without distorting the circular geometry of the exit area, limiting the maximum reachable variation of the exit area.
Innovation Solution
An actuation mechanism comprising three concentric rings and actuating means that allow independent axial movement and rotation of the rings, enabling control over the convergent and divergent sections of the nozzle without distorting the exit area geometry.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If thrust vectoring is implemented by modifying the divergent nozzle section geometry, then manoeuvrability is improved, but the circular geometry of the exit area is distorted into an elliptical shape
Solution Approach 1:
The nozzle is divided into separate functional sections: a fixed convergent section and a variable divergent section. The divergent section is further segmented into multiple movable panels that can be independently controlled, allowing thrust vectoring without distorting the overall circular exit geometry by coordinating panel movements to maintain symmetry.
Solution Approach 2:
The divergent nozzle section is designed with movable panels that can dynamically adjust their position and angle. This dynamic capability allows the nozzle to change geometry for thrust vectoring while maintaining the circular exit area shape through coordinated movement of opposing panels, resolving the contradiction between adaptability and shape preservation.
2Ease of operation
If the throat area and exit area are controlled independently in existing mechanisms, then geometry control is improved, but the maximum reachable variation of the exit area is limited due to geometric distortion
Solution Approach 1:
The invention introduces additional degrees of freedom by allowing panels to move not only axially but also rotate about their hinges. This multi-dimensional movement capability enables independent control of throat and exit areas while avoiding geometric distortion, as panels can adjust their orientation to maintain circular symmetry during area variation.
Solution Approach 2:
The movable panels provide dynamic geometry control, allowing the nozzle to achieve maximum exit area variation without distortion. By coordinating the movement of multiple panels across different dimensions, the system overcomes the limitations of existing mechanisms while maintaining ease of operation through independent area control.
Data Source
AI summary
The present invention belongs to the technical field of gas turbine engines used as propulsion systems for supersonic aircraft. In particular, the invention relates to thrust vectoring convergent-divergent nozzles and, more in particular, to an actuation mechanism for vectoring said variable geometry nozzle.