Split Fuselage Rear for Boundary Layer Ingestion

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Solution Overview

Problem

Current boundary layer ingestion propulsion systems in aircraft are inefficient due to non-axial symmetry of air intake, leading to flow distortion and reduced performance.

Innovation Solution

The aircraft fuselage is split into distinct rear portions, each equipped with a rotary ring and engine receiver, allowing for axial symmetry in boundary layer intake and improved engine performance by optimizing engine placement and design.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Device complexity

If two half-sunken engines are placed side by side in the rear portion of fuselage, then the engine configuration is simplified, but the boundary layer intake becomes asymmetric and flow distortion occurs

Engineering Contradiction:

Improveengine configurationVSAvoidflow symmetry

Core Design Contradiction:

Device complexityVSStability of the object's composition

Solution Approach 1:

The fuselage rear portion is divided into multiple separate portions, each integrating a rotary ring and engine receiver. This segmentation allows each engine to independently ingest boundary layer air from its associated fuselage portion, ensuring axial symmetry for each engine while maintaining overall system simplicity.

Inventive Principle:

Principle #1Segmentation

2Volume of moving object

If engines take in boundary layer air from asymmetric positions, then installation space is reduced, but flow distortion increases and performance decreases

Engineering Contradiction:

Improveinstallation spaceVSAvoidpropulsion efficiency

Core Design Contradiction:

Volume of moving objectVSProductivity

Solution Approach 1:

Each fuselage rear portion is designed with specific local characteristics to match its associated engine, creating optimal boundary layer intake conditions for each engine individually. The rotary rings and receivers are positioned and shaped to ensure symmetric flow capture at each location, maximizing propulsion efficiency while maintaining compact overall dimensions.

Inventive Principle:

Principle #3Local quality

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 configuration enhances overall aircraft performance by ensuring all boundary layer air is ingested by each engine, reducing fuel consumption and drag, and allowing for more efficient propulsion.

Implementation Method 1

engines with boundary layer ingestion propulsion circulating on the rear portion of fuselage

Methodology Applied

Scientific EffectBoundary layer ingestion: Boundary Layer

Implementation Method 2

a rotary ring from which bladed elements project radially to the outside

Methodology Applied

Scientific EffectRotational motion:

Data Source

PatentUS10633101B2Assembly for aircraft comprising engines with boundary layer ingestion propulsion

Publication Date: 2020.04.28 AIRBUS OPERATIONS (SAS)

AI summary

In order to further benefit from the principle of boundary layer ingestion by engines of an aircraft assembly, the rear portion of the fuselage of this aircraft assembly includes a front portion which splits up into at least two distinct rear portions, spaced apart from each other, and each integrating the rotary ring of the receiver of one of the engines.