Hybrid Aircraft Propulsion with Generator-Driven Ducted Thrusters

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Solution Overview

Problem

Existing hybrid-electric propulsion systems for aircraft lack efficiency and require additional thermal engines for side thrusters, increasing cost, weight, and complexity.

Innovation Solution

A hybrid-electric propulsion system for aircraft featuring a dual-engine configuration with generators mounted on the exhaust section and geartrain, providing electrical power to ducted propulsor modules for enhanced propulsion and reduced fuel consumption.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Power

If additional thermal engines are added for side thrusters, then propulsion capability is improved, but device complexity and weight increase

Engineering Contradiction:

Improvepropulsion capabilityVSAvoidsystem complexity

Core Design Contradiction:

PowerVSDevice complexity

Solution Approach 1:

The main thermal engines serve multiple functions: they provide primary propulsion through the geartrain and rotor, and simultaneously generate electrical power through generators mounted on their exhaust sections. This electrical power drives the ducted propulsor modules, eliminating the need for separate thermal engines for side thrusters while maintaining full propulsion capability.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The invention merges the propulsion function and electrical power generation function into a single integrated system. The generators are mounted directly on the exhaust sections of the main thermal engines, combining what would traditionally be separate systems (thermal engines for propulsion and separate power sources for electrical needs) into one unified configuration that reduces overall system complexity.

Inventive Principle:

Principle #5Merging (Combining)

2Power

If additional thermal engines are added for side thrusters, then propulsion capability is improved, but weight increases

Engineering Contradiction:

Improvepropulsion capabilityVSAvoidsystem weight

Core Design Contradiction:

PowerVSWeight of moving object

Solution Approach 1:

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Use of energy by moving object

If conventional hybrid-electric propulsion systems are used, then electrical power is provided, but fuel consumption increases

Engineering Contradiction:

Improveelectrical power provisionVSAvoidfuel consumption

Core Design Contradiction:

Use of energy by moving objectVSLoss of energy

Solution Approach 1:

The invention converts what would normally be wasted energy (exhaust flow from the thermal engines) into a useful resource by mounting generators on the exhaust sections. This allows the exhaust flow to drive the generators, producing electrical power that drives the ducted propulsor modules, thereby converting a byproduct into a beneficial energy source and reducing overall fuel consumption.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

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

Operates gas turbine engines at higher cruise power, reducing fuel burn and flight range, eliminating the need for additional thermal engines, and simplifying powerplant design.

Implementation Method 1

Operates gas turbine engines at higher cruise power

Methodology Applied

Scientific EffectCombustion: Combustion

Implementation Method 2

providing electrical power to ducted propulsor modules

Methodology Applied

Scientific EffectElectromagnetic induction: Electromagnetic Induction

Implementation Method 3

a first electric motor, and a first bladed propulsor. The first bladed propulsor is coupled with the first electric motor

Methodology Applied

Scientific EffectElectromagnetic force: Lorentz Force

Data Source

PatentEP4714826A1Hybrid electric propulsion system for aircraft

Publication Date: 2026.03.25 PRATT & WHITNEY CANADA CORP

Figure 1
Figure 2
Figure 3A~3B

AI summary

A propulsion system (20) for an aircraft includes a propulsion rotor, and at least one engine (22) mechanically coupled to the propulsion rotor via a geartrain (60). The propulsion system (20) also includes a first propulsor module (24) having a first housing, a first electric motor (112), and a first bladed propulsor. The first bladed propulsor is coupled with the first electric motor (112) within the first housing. The propulsion system (20) further includes a second propulsor module having a second housing, a second electric motor, and a second bladed propulsor. The second bladed propulsor is coupled with the second electric motor within the second housing. The propulsion system (20) also includes a first generator (82) driven by the at least one engine (22) and electrically connected with the first electric motor (112). Additionally, the propulsion system (20) includes a second generator driven by the at least one engine (22) and electrically connected with the second electric motor.