Integrated Pusher Turbofan Wing Trailing Edge

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Solution Overview

Problem

Integrating ultra-high bypass ratio turbofan engines into low-wing airplanes poses challenges due to noise and emission issues associated with conventional open-fan engines, while maintaining fuel efficiency and reducing noise.

Innovation Solution

A propulsion system featuring a ducted fan coupled to a gas turbine core in a pusher configuration, integrated into the trailing edge of the wing with a fairing for aerodynamic and structural integration, and a gear box for proper rotational alignment, along with optional boundary layer management systems to mitigate noise and efficiency losses.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Use of energy by moving object

If ultra-high bypass ratio turbofan engines are integrated into low-wing airplanes, then fuel efficiency is improved, but noise and emissions problems worsen

Engineering Contradiction:

Improvefuel efficiencyVSAvoidnoise and emissions

Core Design Contradiction:

Use of energy by moving objectVSObject-generated harmful factors

Solution Approach 1:

The patent extracts the fan assembly from the traditional engine position and places it in the wing trailing edge, separating the noise-generating rotating blades from the fuselage area while maintaining the fuel-efficient ultra-high bypass ratio configuration

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The ducted fan is nested within the wing trailing edge structure, with the fan assembly integrated into the wing's aerodynamic contour. The shroud is nested within the wing structure, allowing the propulsion system to be embedded in the wing rather than mounted externally

Inventive Principle:

Principle #7Nested doll (Nesting)

2Object-generated harmful factors

If ducted fan is used instead of open-fan engine, then noise is reduced, but device complexity increases

Engineering Contradiction:

ImprovenoiseVSAvoidstructural integration complexity

Core Design Contradiction:

Object-generated harmful factorsVSDevice complexity

Solution Approach 1:

The patent merges the propulsion system with the wing structure by integrating the ducted fan into the trailing edge. The shroud is combined with the wing's aerodynamic surface, and the mounting structure is integrated into the wing's internal framework, reducing the need for separate external mounting components

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The wing trailing edge structure serves multiple functions: it provides aerodynamic shaping, structural support for the ducted fan, noise shielding, and integration pathway for the propulsion system. The shroud simultaneously provides aerodynamic containment and noise reduction

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Productivity

If pusher configuration is adopted with ducted fan in trailing edge, then aerodynamic efficiency is improved, but manufacturing difficulty increases

Engineering Contradiction:

Improveaerodynamic efficiencyVSAvoidintegration into wing structure

Core Design Contradiction:

ProductivityVSEase of manufacture

Solution Approach 1:

The patent segments the ducted fan assembly into modular components that can be manufactured separately and then integrated into the wing trailing edge. The fan, shroud, and mounting structure are designed as distinct modules that can be assembled through standardized connection points in the wing structure

Inventive Principle:

Principle #1Segmentation

Data Source

PatentUS9950800B2Integrated pusher turbofan for aircraft

Publication Date: 2018.04.24 THE BOEING CO

AI summary

A propulsion system for a transport aircraft employs a gas turbine core coupled to a wing. A ducted fan is coupled to the core gas turbine extending downstream from and integrated in a trailing edge of the airplane wing.