Portable Fuel Preservation System for Gas Turbine Engines

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Solution Overview

Problem

Current preservation systems for gas turbine engines require the engine to be attached to an aircraft or a test cell for fuel system preservation, increasing costs due to the need for continuous power supply and limited mobility.

Innovation Solution

A portable fuel preservation system that includes a switch box with a 28-volt power supply, a mechanical switch, and a resistor to generate a current between 10 milliamps and 50 milliamps, allowing the preservation fluid to be injected into the fuel system without requiring the engine to be attached to a power source, using a mating connector to engage with the integrated fuel pump and control to open the metering and solenoid valves.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If the engine is attached to an aircraft or test cell for preservation fluid injection, then the fuel system can be preserved, but the cost increases and mobility is reduced

Engineering Contradiction:

Improvefuel system preservationVSAvoidmobility

Core Design Contradiction:

ReliabilityVSEase of operation

Solution Approach 1:

The system separates the preservation function from the engine itself by using a portable external power supply and control unit. The engine fuel system is divided into preservable components (fuel pump, valves, lines) that can be treated independently, allowing the engine to be removed from aircraft or test cells while still enabling preservation through external equipment connection.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

A portable power supply and control unit act as an intermediary between the preservation fluid injection system and the engine fuel system. This intermediary provides the necessary electrical power and control signals without requiring the engine to be connected to aircraft or test cell power sources, enabling preservation in field conditions.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Reliability

If the engine is attached to an aircraft or test cell for preservation fluid injection, then the fuel system can be preserved, but the cost increases

Engineering Contradiction:

Improvefuel system preservationVSAvoidcost

Core Design Contradiction:

ReliabilityVSQuantity of substance

Solution Approach 1:

The portable preservation system is self-contained with its own power supply, control unit, and fluid injection capability. It does not require external aircraft or test cell infrastructure, making the preservation process independent and eliminating the need to pay for occupying aircraft or test cell facilities.

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

The system uses a portable, potentially disposable or single-use power supply and control unit specifically for the preservation operation. This eliminates the need for expensive, long-term infrastructure occupancy (aircraft or test cell facilities) and allows the preservation to be performed with simpler, cheaper equipment.

Inventive Principle:

Principle #27Cheap short-living objects (Disposable)

3Reliability

If continuous power supply is required for preservation, then the fuel system can be preserved, but mobility is reduced

Engineering Contradiction:

Improvefuel system preservationVSAvoidpower supply requirement

Core Design Contradiction:

ReliabilityVSUse of energy by moving object

Solution Approach 1:

The system transitions from a static power supply configuration (fixed aircraft or test cell power) to a dynamic portable power supply that can be moved with the engine. The portable power supply adapts to field conditions and provides power only when needed for the preservation operation, eliminating continuous power requirements and enabling mobility.

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

Enables fuel system preservation of gas turbine engines without the need for an engine test cell or continuous power supply, reducing costs and increasing mobility by allowing preservation to be conducted on-site after the engine is removed from an aircraft.

Implementation Method 1

the power supply and the resistor may generate between a 10 milliamp and 50 milliamp current

Methodology Applied

Scientific EffectElectrical current generation: Ohm's Law

Implementation Method 2

Opening the metering valve may cause the first solenoid valve and a second solenoid valve of the integrated fuel pump and control to open

Methodology Applied

Scientific EffectSolenoid actuation: Solenoid

Data Source

PatentEP3450725B1Integrated fuel pump and control preservation system

Publication Date: 2022.03.30 RTX CORP

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AI summary

A portable fuel preservation system (200) is disclosed. The portable fuel preservation system (200) may comprise a switch box (202) configured to be coupled to an integrated fuel pump and control (102) of a gas turbine engine (20). The switch box (202) may comprise a circuit (310) configured to cause a metering valve (130) and a solenoid valve (132, 134) of the integrated fuel pump and control (102) to open. A driver (206) may be configured to inject preservation fluid into the integrated fuel pump and control (102).