Thrust Reverser Compression Rod Transverse Mounting
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Solution Overview
Problem
Current gas turbine propulsion systems for commercial aircraft face challenges in efficiently managing the load between thrust reverser halves during varying pressure conditions, which can lead to inefficiencies and increased weight due to the conventional support methods of compression rods.
Innovation Solution
The proposed solution involves a compression rod system supported by a bracket mounted to an exhaust nozzle flange, with engagement members and features that allow the rod to be compactly positioned and securely engage with thrust reverser halves, reducing weight and footprint while effectively transmitting loads between the halves.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If conventional support methods for compression rods are used in thrust reverser systems, then the structure can maintain stability under pressure differential loads, but the system experiences increased weight and larger footprint
Solution Approach 1:
The compression rod is repositioned from a conventional longitudinal arrangement to a transverse orientation across the exhaust nozzle flange. This dimensional change allows the rod to leverage the flange structure for support, reducing the need for extensive bracketry and engagement features while maintaining structural integrity and load management capability.
Solution Approach 2:
The exhaust nozzle flange is utilized as a multi-functional component, serving both its primary exhaust function and as a structural support element for the compression rod. By mounting the rod to the flange, the system eliminates the need for separate dedicated support structures, thereby reducing overall weight and component count while maintaining reliability.
2Volume of moving object
If conventional compression rod arrangements are used, then the thrust reverser halves can be engaged under pressure differential loads, but the overall footprint and complexity of the system increase
Solution Approach 1:
The compression rod is oriented transversely across the exhaust nozzle flange rather than longitudinally, utilizing the flange width to accommodate the rod. This dimensional reconfiguration reduces the axial footprint along the engine centerline and simplifies the engagement mechanism by leveraging the flange's inherent structural geometry.
Solution Approach 2:
The support function is extracted from the compression rod assembly itself and transferred to the exhaust nozzle flange structure. This separation allows the rod to be a simpler, more compact component focused solely on load transmission, while the flange provides the necessary support and positioning, thereby reducing overall system complexity.
Data Source
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AI summary
An aircraft nacelle arrangement includes a compression rod disposed between a first nacelle half and a second nacelle half, wherein the first nacelle half and the second nacelle half are rotatable about a hinge between a closed position and an open position, a compression rod disposed between the first nacelle half and the second nacelle half, and a mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the mounting bracket.