Deformable Bypass Nozzle Element for Aircraft Gas Turbine
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Solution Overview
Problem
Existing aircraft gas turbine designs with variable bypass nozzles require complex and costly actuation systems, lead to flow disruptions, and suffer from material aging issues, while also reducing sound absorption and increasing weight due to the need for multiple components and elaborate adjustments.
Innovation Solution
A deformable, radially adjustable bypass nozzle element integrated into the inner structure of the core engine cowling, which can be easily actuated to change the bypass nozzle cross-section without requiring extensive energy input, and is designed with a sound absorption feature to enhance noise reduction and structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If segmented parts of the trailing edge are moved radially by actuating devices, then the bypass nozzle can be adjusted, but the device complexity and weight increase
Solution Approach 1:
The patent employs a flexible membrane element within the bypass nozzle that can deform radially to adjust the nozzle cross-section. This flexible membrane replaces complex segmented mechanical actuators, allowing the nozzle area to be variable while maintaining a simple, integrated structure without multiple moving parts or complex actuation mechanisms.
2Adaptability or versatility
If the entire trailing edge is designed as a moveable ring, then the bypass nozzle can be adjusted axially, but the device complexity and weight increase
Solution Approach 1:
Instead of a heavy moveable ring structure, the invention uses a flexible membrane element that can be actuated with minimal force to change the bypass nozzle cross-section. This membrane is integrated into the existing bypass cowling structure, avoiding the need for heavy moveable rings while achieving the same adaptability function.
3Adaptability or versatility
If adjustable mechanisms are placed at the trailing edge of the bypass casing, then the bypass nozzle can be controlled, but the required thickness and axial length increase
Solution Approach 1:
The invention transitions from axial movement mechanisms to radial deformation of a flexible membrane element. By actuating the membrane radially inward or outward, the bypass nozzle cross-section is adjusted without requiring axial movement, thereby reducing the axial length and thickness requirements of the adjustment mechanism.
4Adaptability or versatility
If multiple components are used for bypass nozzle adjustment, then the nozzle can be controlled, but manufacturing cost and complexity increase
Solution Approach 1:
The flexible membrane element is integrated directly into the bypass cowling structure as a unified component, eliminating the need for separate adjustable segments, rings, or actuation mechanisms. This merging of functions into a single integrated structure simplifies manufacturing and reduces assembly complexity while maintaining bypass nozzle controllability.
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
This solution simplifies the design and production of the bypass nozzle, reduces weight, minimizes flow disruptions, and enhances noise absorption while maintaining structural integrity and ease of maintenance, using a lightweight and cost-effective material.
Implementation Method 1
an adjusting element (33) extending in the circumferential direction of the inner wall and deformable radially outwards and hence into the bypass duct (29)
Data Source
AI summary
The present invention relates to an aircraft gas turbine with a core engine which is surrounded by a bypass duct enclosed radially outwards by a bypass wall, with a radially inner wall of the bypass duct forming with the radially outer bypass wall a bypass nozzle, and with the radially inner wall including an adjusting element extending along the circumference of the inner wall and being deformable radially outwards.