Thrust Reverser Cowl Locking Mechanism for O-Duct Turbojet
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
O-duct turbojet engines lack a third safety lock, compromising their reliability and security compared to D-duct engines, which are more secure due to the presence of an independent third lock.
Innovation Solution
Incorporating a mechanically and geographically independent locking mechanism between the cowl and pylon, featuring a lock body with a keeper and bolt, allowing for a third safety lock installation without special adaptations, and providing electrical supply cables with excess length for connectivity during sliding, along with offset rails for maintenance access.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a one-piece cowl is used in an O-duct reverser, then the structure is simpler and manufacturing is easier, but a third safety lock cannot be installed, reducing reliability
Solution Approach 1:
The locking means is segmented into distinct components: a lock body with a keeper articulated on it, and a separate bolt. This segmentation allows the locking mechanism to be installed in the limited space between the pylon and cowl while maintaining the simplicity of the one-piece cowl structure, thereby preserving ease of manufacture while enabling the installation of a third safety lock to improve reliability
Solution Approach 2:
The lock body is mounted inside the pylon, with the keeper passing through an orifice in the pylon. This nested arrangement allows the locking mechanism to be integrated within the existing structure without requiring additional external space, thus maintaining the simplicity of the one-piece cowl design while adding the necessary safety lock functionality
2Reliability
If safety locks are provided with independent power sources, then reliability and security are increased, but device complexity increases
Solution Approach 1:
The locking means uses a universal bolt that can be integral with either the cowl or the pylon, and the lock body can be mounted in either component. This multi-functional design allows the same basic locking mechanism to serve multiple purposes and be configured differently based on specific installation requirements, reducing overall device complexity while maintaining reliability through independent power sources
3Ease of manufacture
If the lock body is mounted inside the pylon with the keeper passing through an orifice, then space is efficiently used and installation is simplified, but the pylon structure must be modified
Solution Approach 1:
An orifice is formed in the pylon during the manufacturing process to accommodate the keeper. This preliminary action ensures that the locking mechanism can be easily installed without requiring complex post-manufacturing modifications, thereby simplifying installation while maintaining a relatively simple overall structure
Data Source
Figure 1~3
Figure 4~6
Figure 7~9
AI summary
The invention relates to an assembly for a turbojet engine which includes a pylon (1) and a nacelle supported by said pylon (1). Said nacelle (3) includes a grid thrust reverser (21) including an integral cowl mounted so as to slide on rails (15), which are arranged on both sides of said pylon (1), between a direct jet position and a thrust reversal position. Said assembly is characterised in that it includes means (23, 31) for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon (1) and the cowl.