Four-Ring Actuation Mechanism for Circular Thrust-Vectoring Nozzles
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Solution Overview
Problem
Existing thrust vectoring variable geometry nozzles for gas turbine engines distort the exit area from circular to elliptical shape, limiting the maximum variation of the exit area without modifying the throat area.
Innovation Solution
An actuation mechanism comprising four concentric rings with specific actuating means allows independent control over the convergent and divergent sections of the nozzle, enabling simultaneous variation of the throat and exit areas without distorting the circular geometry.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If existing thrust vectoring variable geometry nozzles are used, then the nozzle can be vectorized for improved maneuverability, but the exit area geometry is distorted from circular to elliptical shape, limiting the maximum variation of the exit area
Solution Approach 1:
The nozzle is divided into four independent rings (first, second, third, and fourth rings) that can move relative to each other along the longitudinal axis. Each ring can be actuated independently to control different aspects of the nozzle geometry, allowing the exit area to maintain its circular shape while still enabling thrust vectoring through differential movement of the rings
Solution Approach 2:
The nozzle structure is made dynamic through the four rings that can move independently along the longitudinal axis. This dynamic configuration allows the nozzle to adapt its geometry for thrust vectoring while preserving the circular exit area shape, resolving the contradiction between maneuverability and geometric integrity
2Adaptability or versatility
If the throat area and exit area are varied independently, then the thrust can be optimized for different flying conditions, but the mechanism complexity increases
Solution Approach 1:
Each of the four rings serves multiple functions: they collectively enable independent control of both the throat area (through movement of the first and second rings) and the exit area (through movement of the third and fourth rings), while also providing the structural framework for thrust vectoring. This multi-functionality reduces the need for separate mechanisms for each control function
Solution Approach 2:
The four rings are nested concentrically about the longitudinal axis, with each ring able to move independently. This nested configuration allows compact arrangement of the actuation mechanism while enabling independent control of multiple nozzle parameters, reducing overall system complexity despite the multiple degrees of freedom
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.