Angled Gas Turbine Box Wing Fuselage Integration

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Conventional gas turbine engine configurations are limited in their ability to accommodate alternate aircraft architectures, as they are typically designed for conventional mounting locations, which restricts the implementation of favorable wing and fuselage configurations and poses survivability issues due to potential engine failure fragmentation.

Innovation Solution

The aircraft features a propulsion system with first and second turbine engines mounted at angles relative to their respective propulsor axes, with a defined burst zone extending outward from each engine core, allowing for a box wing configuration that extends forward and positions control surfaces outside the burst zone, thereby enabling alternate engine architectures and improved structural stability.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If conventional gas turbine engine configurations are used, then engine reliability is maintained, but adaptability to alternate aircraft architectures is limited

Engineering Contradiction:

Improveadaptability to alternate aircraft architecturesVSAvoidengine reliability

Core Design Contradiction:

Adaptability or versatilityVSReliability

Solution Approach 1:

The gas turbine engine is divided into separate functional modules: the gas generator (core) and the fan section (propulsor), connected through a power transmission system. This segmentation allows the engine to be configured in different arrangements (conventional, forward-fuselage, aft-fuselage, wing-mounted) while maintaining reliable operation, as each module can be independently positioned to suit different aircraft architectures.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The power transmission system incorporates variable geometry features including adjustable gear ratios and flexible shaft connections, enabling the engine to adapt its configuration dynamically. This allows the same engine design to serve multiple aircraft architectures while maintaining operational reliability through optimized power transmission at each configuration.

Inventive Principle:

Principle #15Dynamics

2Adaptability or versatility

If engines are mounted in conventional locations, then engine reliability is maintained, but wing and fuselage configuration flexibility is restricted

Engineering Contradiction:

Improvewing and fuselage configuration flexibilityVSAvoidsurvivability issues from engine failure fragmentation

Core Design Contradiction:

Adaptability or versatilityVSObject-affected harmful factors

Solution Approach 1:

The gas generator and fan section are extracted as separate modules that can be positioned independently. The gas generator can be mounted in the aft-fuselage while the fan section is positioned forward, or both can be mounted on the wing. This extraction eliminates the constraint that conventional integrated engine mounting imposes on wing and fuselage design, while the modular architecture maintains reliability by isolating failure zones.

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

A power transmission system acts as an intermediary between the gas generator and fan section, allowing flexible spatial arrangement. This intermediary mechanism (including gearboxes and shafts) enables the engine components to be positioned optimally for both aerodynamic performance and survivability, decoupling the traditional rigid engine mounting constraints.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Area of stationary object

If engine cores are positioned close together, then space utilization is improved, but safety is reduced due to potential fragmentation from engine failure

Engineering Contradiction:

Improvespace utilization in fuselageVSAvoidsafety from engine failure fragmentation

Core Design Contradiction:

Area of stationary objectVSReliability

Solution Approach 1:

The engine is segmented into distinct modules (gas generator and fan section) that can be positioned at optimal distances from each other and from the aircraft centerline. This segmentation allows close spacing for space efficiency while maintaining safety through modular design, as failure in one module is isolated and does not propagate to the entire propulsion system.

Inventive Principle:

Principle #1Segmentation

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 allows for the integration of the propulsion system within the fuselage, enabling alternate aircraft architectures while maintaining structural stability and positioning control surfaces outside potential damage zones, enhancing survivability and aerodynamic efficiency.

Implementation Method 1

Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow

Methodology Applied

Scientific EffectCombustion: Combustion

Implementation Method 2

The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section through a driven shaft

Methodology Applied

Scientific EffectExpansion:

Data Source

PatentUS9567062B2Box wing with angled gas turbine engine cores

Publication Date: 2017.02.14 RTX CORP

AI summary

An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft includes a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage that is disposed outside of the burst zone.