Jet Engine Actuation Synchronization Ring Control
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Solution Overview
Problem
Conventional jet engine actuation systems require two separate actuators to adjust internal variable geometry, which can lead to distorting the internal geometry due to high temperatures, and they operate independently, complicating the synchronization of adjustments.
Innovation Solution
A jet engine system with a synchronization ring and actuation system that uses first and second ring gearboxes and drive shafts to transfer rotational outputs from a single actuator to both gearboxes, allowing simultaneous rotation of the synchronization ring and reducing the need for separate actuators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If two separate actuators are used to adjust internal variable geometry at opposing contact points, then the internal geometry can be adjusted, but the system complexity increases and synchronization becomes difficult
Solution Approach 1:
The patent combines two separate actuators into a single actuator that controls both opposing contact points of the synchronization ring through a unified mechanical linkage system. This merging reduces the number of independent control systems while maintaining the ability to adjust internal variable geometry at both contact points simultaneously, thereby simplifying the actuation control without increasing system complexity
Solution Approach 2:
The single actuator is designed to perform multiple functions: it simultaneously controls both opposing contact points of the synchronization ring, provides synchronized adjustment, and maintains mechanical linkage between the two contact points. This multi-functionality eliminates the need for two separate actuators while achieving the same adjustment capability
2Reliability
If actuators are located on the engine outer case, then they can operate independently, but the internal geometry may be distorted due to high temperatures
Solution Approach 1:
The actuation system is segmented into distinct functional components: the actuator housing located on the outer case for reliable operation, and the synchronization ring with contact points that interface with the internal variable geometry. This segmentation allows the actuator to operate in a cooler external environment while still effectively controlling the internal geometry through the synchronization ring mechanism
Solution Approach 2:
The synchronization ring acts as an intermediary component between the externally located actuator and the internal variable geometry. It receives control forces from the actuator at opposing contact points and translates them into precise adjustments of the internal geometry, protecting the geometry from direct thermal exposure while maintaining control accuracy
Data Source
AI summary
A jet engine actuation system includes a first ring gearbox, a second ring gearbox and an actuator. The first ring gearbox includes a first ring driveshaft coupled to a first portion of a synchronization ring included in a jet engine. The second ring gear box includes a second ring drive shaft coupled to a second portion of the synchronization ring. The actuator has a first actuator gearbox configured to generate a first rotational output and a second actuator gearbox configured to generate a second rotational output. A first drive shaft transfers the first rotational output to the first ring gearbox and a second drive shaft transfers the second rotational output to the second ring gearbox. The actuator simultaneously controls the first and second actuator gearboxes such that the first and second rotational outputs are simultaneously transferred to the first and second ring gearboxes to rotate the synchronization ring.