Isochoric Fuel Compression Modules for Cryogenic Turbine Engines
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Solution Overview
Problem
Existing fuel packaging systems for aircraft turbomotors powered by cryogenic fuel face inefficiencies and reliability issues due to the use of mechanical pumps, which require significant energy and are not adaptable to a wide range of flow/pressure conditions.
Innovation Solution
A fuel packaging system that includes a buffer tank and multiple compression modules, each comprising an elementary fixed volume tank, an elementary heat source for isochore compression, and valves for input, output, and degassing, allowing for efficient compression and heating of fuel without relying solely on mechanical pumps.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a mechanical pump is used to pressurize fuel from a cryogenic tank, then the fuel can be supplied to the turbine engine, but the system requires significant energy and has limited adaptability to flow/pressure conditions
Solution Approach 1:
The patent replaces the mechanical pump with a thermodynamic compression system using compressors and heat exchangers. Instead of using mechanical displacement to pressurize fuel, the system uses gas compression and heat transfer to achieve the same result, thereby eliminating the energy inefficiencies and adaptability limitations of mechanical pumps
Solution Approach 2:
The system changes the thermodynamic parameters (temperature and pressure) of the fuel through controlled heating and compression processes. By adjusting these parameters independently, the system can adapt to a wide range of flow and pressure conditions without being constrained by a fixed mechanical pump operating point
2Power
If a mechanical pump is used to pressurize fuel, then fuel can be delivered to the engine, but the pump operates at a non-optimal point requiring constraints that reduce efficiency
Solution Approach 1:
The system introduces dynamic control of compression and heating processes, allowing independent adjustment of pressure and temperature parameters. This enables the system to operate at optimal points across varying conditions, unlike a fixed mechanical pump that must operate away from its optimal range
Solution Approach 2:
The patent divides the fuel pressurization process into separate compression and heating stages, each optimized for its specific function. This segmentation allows each component to operate at its optimal efficiency point while collectively achieving the required fuel delivery performance
3Power
If a mechanical pump is used for fuel compression, then fuel can be pressurized, but sealing and lubrication become problematic in cryogenic conditions
Solution Approach 1:
The patent eliminates mechanical contact components (pump seals and lubrication systems) by replacing the mechanical pump with a thermodynamic compression system. The compressors and heat exchangers used in the alternative system have fewer moving parts and do not require the same sealing and lubrication mechanisms, thereby improving reliability in cryogenic conditions
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 achieves better yield and reliability by using isochore compression and available heat sources, maintaining optimal fuel conditions for the turbomotor, and reducing the need for high-pressure pumps, thus enhancing energy efficiency and operational flexibility.
Implementation Method 1
an elementary heat source configured to increase the temperature of the fuel in the elementary tank in an isochoric manner
Implementation Method 2
When degassing an elementary tank, the gas stream expands isenthalpically in the cryogenic tank, thereby balancing the pressures to allow a new safe cycle of use
Data Source
Figure 1
Figure 2
Figure 3~4A
AI summary
A fuel conditioning system configured to supply an aircraft turbine engine with fuel from a cryogenic tank, the fuel circuit comprising a buffer tank (R2) for supplying the turbine engine and a plurality of compression modules (1A-1D) configured to supply the buffer tank (R2), each compression module (1A-1D) comprising an elementary tank (3A-3D) of fixed volume, an elementary heat source (2A-2D) configured to increase the temperature of the fuel in the elementary tank (3A-3D) in an isochoric manner, an inlet valve (V1A-V1D) connecting the elementary tank (3A-3D) to an upstream part of the fuel circuit (CQ), an outlet valve (V3A-V3D) connecting the elementary tank (3A-3D) to the buffer tank (R2) and a venting valve (V3A-V3D) connecting the elementary tank (3A-3D) to the cryogenic tank via a return circuit (CR) in which a gaseous stream (G) circulates.