Hydrogen Fuel Conditioning Through Auxiliary Combustor Heating
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Solution Overview
Problem
Challenges in conditioning liquid hydrogen for hydrogen fuelled aircraft include the high power required to raise temperatures and pressures at the required flow rate, as well as controlling complex pumping and heating systems to produce the necessary conditions for combustion during all phases of flight.
Innovation Solution
A fuel system for a gas turbine engine comprising a main fuel conduit, a fuel pump, an auxiliary combustor, and a fuel turbine, with a turbine inlet valve to control mass flow and pressure, and a controller to manage the system for efficient fuel conditioning, utilizing a fuel turbine to drive the pump and an auxiliary combustor to heat the fuel.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If liquid hydrogen is stored and pumped to high pressures at high flow rates, then fuel density and energy storage are improved, but the power required to raise temperatures and pressures increases significantly
Solution Approach 1:
The patent combines the heating and pressure-raising functions into a single integrated system where the auxiliary combustor heats the hydrogen while the fuel pump simultaneously raises the pressure, eliminating the need for separate heating and pressurization systems and reducing total power requirements
Solution Approach 2:
The system uses the hydrogen fuel itself as the heating medium by diverting a portion to the auxiliary combustor, allowing the fuel to heat itself and subsequent fuel portions without requiring external heating systems, thereby reducing the power input needed
2Productivity
If complex pumping and heating systems are used to condition liquid hydrogen, then required flow, pressures and temperatures can be produced, but system complexity and control difficulty increase
Solution Approach 1:
The patent merges the heating and pressurization functions into a single integrated system where the auxiliary combustor heats the hydrogen while the fuel pump simultaneously raises the pressure, eliminating the need for separate heating and pressurization systems and reducing overall system complexity
Solution Approach 2:
The fuel pump serves multiple functions: it pressurizes the hydrogen, maintains flow rate, and works cooperatively with the auxiliary combustor to heat the fuel, making it a multi-functional component that reduces the need for separate dedicated heating equipment
3Productivity
If independent control of temperature and pressure is implemented, then fuel conditioning efficiency is improved, but control system complexity increases
Solution Approach 1:
The patent segments the fuel conditioning process into two independent controllable parameters: temperature control through the auxiliary combustor and pressure control through the fuel pump, allowing each to be adjusted independently for optimal efficiency
Solution Approach 2:
The system dynamically adjusts the balance between temperature and pressure control based on real-time fuel conditions and engine requirements, with the controller continuously optimizing the operation of the auxiliary combustor and fuel pump to maintain efficient conditioning
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
The system efficiently conditions fuel by providing independent control of temperature and pressure, utilizing excess energy, and ensuring consistent fuel flow and pressure across varying flight conditions.
Implementation Method 1
an auxiliary combustor downstream in fuel flow of the fuel pump, and configured to combust a portion of fuel diverted from the main fuel conduit and to heat a remainder of fuel in the main fuel conduit
Implementation Method 2
a fuel turbine downstream in fuel flow of the auxiliary combustor, the fuel turbine being configured to be driven by the heated fuel from the auxiliary combustor and configured to power the fuel pump
Data Source
AI summary
A fuel system for a gas turbine engine configured to combust hydrogen fuel. The fuel system includes a main fuel conduit, a fuel pump configured to operate on hydrogen within fuel conduit to provide pressurised fuel to core combustor of gas turbine engine, an auxiliary combustor downstream in fuel flow of fuel pump, and configured to combust a portion of fuel diverted from main fuel conduit and to heat remainder of fuel in main fuel conduit, and a fuel turbine downstream in fuel flow of the auxiliary combustor. The fuel turbine is configured to be driven by heated fuel from auxiliary combustor and configured to power the fuel pump. The fuel system comprises a turbine inlet valve provided upstream in hydrogen fuel flow of the fuel turbine and configured to control mass flow rate and/or pressure of fuel flowing into fuel turbine. 1. A method of operation is also described.