Turbine-Driven Hydrogen Supply For Aircraft Engine Heating

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Solution Overview

Problem

Existing hydrogen supply systems for aircraft gas turbine engines face challenges in efficiently compressing and heating liquid hydrogen to gaseous hydrogen at ambient temperature and sufficient pressure, with issues including heat transport limitations, low system efficiency, and dependence on engine operation for heating.

Innovation Solution

A hydrogen supply system comprising a first pump for pressurizing liquid hydrogen, a second turbo-pump driven by a turbine, a heat exchanger, and a combustion chamber with controlled valves and a control unit to manage hydrogen flow, providing independent heating and efficient conversion to gaseous hydrogen.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If heat recovery in the gas turbine nozzle is used to reheat hydrogen, then heating function is provided, but heat transport limitations and low system efficiency occur

Engineering Contradiction:

Improvehydrogen temperatureVSAvoidsystem efficiency

Core Design Contradiction:

TemperatureVSLoss of energy

Solution Approach 1:

The heating function is segmented from the gas turbine nozzle and transferred to a dedicated combustion chamber. This allows the nozzle to focus on its primary function of delivering hydrogen to the engine while the combustion chamber independently handles heating, eliminating heat transport losses and improving overall system efficiency.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

A combustion chamber acts as an intermediary device between the hydrogen supply and the gas turbine engine. It receives hydrogen, adds heat through controlled combustion, and delivers heated hydrogen to the engine, thereby eliminating the need for heat recovery from the nozzle and resolving heat transport limitations.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Temperature

If staged combustion reheating is used to heat hydrogen, then heating function is achieved, but high pressure air supply is required which represents a major technical difficulty

Engineering Contradiction:

Improvehydrogen temperatureVSAvoidair supply system complexity

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

The combustion chamber operates at low pressure conditions, changing the pressure parameter from which air is supplied. Instead of requiring high pressure air matching the compressor output, the system uses low pressure air supply, dramatically simplifying the air supply system while maintaining effective hydrogen heating through controlled combustion.

Inventive Principle:

Principle #35Parameter changes

3Temperature

If heat recovery in the gas turbine nozzle is used, then heating is provided during operation, but alternative heating device is required for starting

Engineering Contradiction:

Improvehydrogen temperatureVSAvoidheating system adaptability

Core Design Contradiction:

TemperatureVSAdaptability or versatility

Solution Approach 1:

The combustion chamber is designed to be self-sufficient for heating purposes. It can operate independently during engine starting without relying on gas turbine operation, and continues to provide heating during normal operation. This eliminates the need for separate alternative heating devices and provides consistent heating adaptability across all operating conditions.

Inventive Principle:

Principle #25Self-service

4Stress or pressure

If a turbo-pump is used to compress hydrogen, then hydrogen pressure is increased, but electricity consumption increases

Engineering Contradiction:

Improvehydrogen pressureVSAvoidelectricity consumption

Core Design Contradiction:

Stress or pressureVSUse of energy by moving object

Solution Approach 1:

The electrically-driven turbo-pump is replaced with a turbine-driven compression system. The turbine converts the chemical energy of hydrogen combustion directly into mechanical work for compression, eliminating the need for electrical power and significantly reducing electricity consumption while maintaining effective hydrogen pressurization.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

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 efficient and reliable production of gaseous hydrogen at ambient temperature and pressure, reducing electricity consumption and simplifying air supply, while offering independent heating and improved system reliability.

Implementation Method 1

a heat exchanger configured to receive, at a first input port, the highly pressurized liquid hydrogen from the second pump and provide, at a first output port, a gaseous heated pressurized hydrogen

Methodology Applied

Scientific EffectHeat exchange: Heat Exchanger

Implementation Method 2

a combustion chamber providing heat to the heat exchanger for reheating hydrogen outputted from the second pump

Methodology Applied

Scientific EffectCombustion: Combustion

Implementation Method 3

a turbine configured to receive, at an input port, the gaseous heated pressurized hydrogen from the first output port of the heat exchanger and to provide, at an output port, gaseous hydrogen, wherein the turbine provides mechanical energy to the second pump to make it run

Methodology Applied

Scientific EffectTurbine energy conversion: Turbine

Data Source

PatentEP4632202A1Hydrogen supply system for an aircraft engine with a turbo-pump and a low-pressure burner

Publication Date: 2025.10.15 AIRBUS OPERATIONS (SAS)

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AI summary

A hydrogen supply system for providing gaseous hydrogen to an engine from a tank of liquid hydrogen.