Variable Area Bypass Nozzle Using Inflatable Bladder

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Gas turbine engines face inefficiencies at diverse flight speeds and altitudes, particularly at low power settings, with conventional solutions involving complex and weight-added configurations.

Innovation Solution

A gas turbine engine system utilizing a bladder within a duct that inflates with bleed gas to modulate the flow area, reducing the passage area for gas flow, thereby improving efficiency across varying conditions.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If complex configurations with many moving parts are used to improve engine efficiency at diverse flight conditions, then engine efficiency is improved, but device complexity increases

Engineering Contradiction:

Improveengine efficiency at diverse flight speeds and altitudesVSAvoidcomplexity of propulsion system configuration

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent employs a movable nozzle component that can dynamically adjust its position to change the bypass duct area. This dynamic adjustment allows the engine to optimize performance across diverse flight conditions (different speeds and altitudes) without requiring complex multi-component systems. The single movable element provides adaptability while maintaining relatively simple device architecture.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The patent uses a bladder inflated with bleed air (pneumatic actuation) to move the nozzle component and adjust the bypass duct area. This pneumatic mechanism replaces what could be a complex mechanical linkage system, simplifying the overall device complexity while achieving the desired adaptability for efficient operation at various flight conditions.

Inventive Principle:

Principle #29Pneumatics and hydraulics

2Adaptability or versatility

If complex configurations with many moving parts are used to improve engine efficiency, then engine efficiency is improved, but weight increases

Engineering Contradiction:

Improveengine efficiency at diverse flight speeds and altitudesVSAvoidweight of propulsion system

Core Design Contradiction:

Adaptability or versatilityVSWeight of moving object

Solution Approach 1:

The single movable nozzle component with adjustable area provides dynamic adaptation to different flight conditions, eliminating the need for multiple heavy mechanical components. This dynamic design achieves versatility while minimizing weight compared to conventional multi-component systems.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The pneumatic actuation system using bladder and bleed air is lighter than equivalent mechanical linkage systems with multiple moving parts. This approach reduces the weight of the propulsion system while maintaining the capability for efficient operation across diverse flight conditions.

Inventive Principle:

Principle #29Pneumatics and hydraulics

3Adaptability or versatility

If the bypass duct area is decreased to modulate gas flow, then engine efficiency at low power settings is improved, but the flow area for gas passage is reduced

Engineering Contradiction:

Improveengine efficiency at low power settingsVSAvoidbypass duct flow area

Core Design Contradiction:

Adaptability or versatilityVSArea of stationary object

Solution Approach 1:

The movable nozzle component allows dynamic adjustment of the bypass duct area, enabling the system to decrease the area when low power setting efficiency is needed while maintaining the capability to increase the area when higher flow is required. This dynamic control resolves the contradiction by making the area variable rather than fixed.

Inventive Principle:

Principle #15Dynamics

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 system enhances engine efficiency by modulating gas flow through the nozzle, allowing for efficient operation at different flight speeds and altitudes without adding significant weight or complexity.

Implementation Method 1

The gas source has a higher pressure than a pressure within the first duct. The bladder is adapted to receive a gas flow from the gas source and inflate within the first duct

Methodology Applied

Scientific EffectPressure gradient: Pressure Gradient

Data Source

PatentUS10260427B2Variable area bypass nozzle

Publication Date: 2019.04.16 RTX CORP

AI summary

A gas turbine engine includes a first duct, a second duct, and a bladder. The bladder is disposed in the first duct and communicates with the second duct. A first gas flow is capable of passing through the first duct and a second gas flow is capable of passing through the second duct. The bladder is adapted to receive a bleed gas flow from the second duct and inflate within the first duct, thereby decreasing an area in the first duct through which the first gas flow is capable of traveling.