Radial Cascade Thrust Reverser for Compact Nacelle Design
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Solution Overview
Problem
Traditional thrust reverser systems for turbofan engines are bulky, increasing engine size and weight, and reducing propulsive efficiency due to their large nacelle length, which complicates the development of a more compact and efficient system.
Innovation Solution
A cascade thrust reverser assembly that expands radially, allowing the nacelle to be more compact by moving cascade members between a stowed and deployed configuration, effectively increasing the radial extent to enhance airflow redirection and thrust reversal while maintaining a smaller nacelle size.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional thrust reverser systems are used, then thrust reversal function is achieved, but engine size and weight increase
Solution Approach 1:
The cascade members are designed to be movable between stowed and deployed configurations rather than fixed. This dynamic capability allows the system to achieve thrust reversal only when needed, reducing the overall engine weight while maintaining the thrust reversal function when required.
Solution Approach 2:
The thrust reverser system is divided into multiple independent cascade members that can be individually positioned. This segmentation allows for a more compact design compared to traditional monolithic thrust reverser systems, reducing overall engine weight while maintaining functionality.
2Reliability
If traditional thrust reverser systems are used, then thrust reversal function is achieved, but nacelle length increases
Solution Approach 1:
The cascade members expand radially outward from the engine core rather than extending axially. This dimensional change allows thrust reversal functionality to be achieved within a shorter nacelle length, as the flow redirection occurs in the radial direction perpendicular to the engine axis.
Solution Approach 2:
The movable cascade members allow the nacelle to maintain a compact, fixed length while achieving thrust reversal through internal configuration changes rather than extending the nacelle structure.
3Loss of energy
If nacelle thickness is reduced to reduce drag, then propulsive efficiency improves, but space for thrust reverser components is limited
Solution Approach 1:
The thrust reverser components utilize the radial dimension for expansion rather than requiring additional axial or radial space in the nacelle. This allows the nacelle to maintain a thin profile for reduced drag while still accommodating the thrust reverser mechanism through clever spatial utilization.
Solution Approach 2:
The cascade members are designed to nest within the limited nacelle volume when in the stowed configuration, allowing the nacelle to maintain a compact thickness. When deployed, the members expand into the bypass flow path without requiring excessive nacelle thickness.
4Reliability
If cascade members expand radially, then thrust reversal effectiveness is enhanced, but device complexity increases
Solution Approach 1:
The radial expansion capability of the cascade members is achieved through a dynamic mechanism that allows controlled movement between stowed and deployed positions. This dynamic design enhances thrust reversal effectiveness by positioning the cascade members optimally in the bypass flow path while maintaining a compact form when not in use.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The radial expansion of the cascade thrust reverser assembly allows for a more compact and lightweight turbofan engine with reduced drag, enabling efficient thrust reversal and installation on aircraft wings, while maintaining performance.
Implementation Method 1
the cascade assembly includes a plurality of cascade segments, each cascade segment including a plurality of cascade members. In the deployed configuration, the bypass air within the bypass airflow passage is diverted through the cascade assembly to provide a thrust reversal effect.
Data Source
AI summary
A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.