Cryogenic Fluid APU Integration for Aircraft Power and Cooling
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Solution Overview
Problem
Existing aircraft systems face inefficiencies in power generation and environmental control due to separate air supply systems and the need for multiple power supplies and heat exchangers, leading to increased weight and complexity.
Innovation Solution
Integration of a cryogenic fluid system within the APU that includes a heat exchanger, pump, recuperator, and fuel cell, which operates synergistically with the turbine engine to provide power and cooling, eliminating the need for separate power supplies and heat exchangers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If separate air supply systems and multiple power supplies are used in existing aircraft systems, then power generation and environmental control functions are provided, but system weight and complexity increase
Solution Approach 1:
The patent combines the APU power system and environmental control system into an integrated architecture where the turbine engine drives both the generator and the compressor for air supply. The cryogenic fluid system serves dual purposes: cooling the turbine and providing cabin air conditioning, eliminating the need for separate cooling systems and reducing overall system complexity.
Solution Approach 2:
The cryogenic fluid operates as a multi-functional medium: it cools the turbine during power generation, condenses water vapor for water recovery systems, and provides cooling for electronic equipment. This universal application of a single system replaces multiple dedicated cooling systems, reducing weight and complexity while maintaining reliability.
2Temperature
If multiple heat exchangers and power supplies are installed, then cooling and power generation functions are achieved, but system weight increases
Solution Approach 1:
The patent merges the turbine cooling function and cabin air conditioning function into a single cryogenic fluid system. The cold fluid from the cryogenic tank cools the turbine directly, and the same fluid stream subsequently cools electronic equipment and provides cabin air conditioning, eliminating the need for multiple separate heat exchangers and reducing system weight.
Solution Approach 2:
The cryogenic fluid system provides universal cooling across multiple subsystems: turbine cooling, electronic equipment cooling, cabin air conditioning, and water condensation. This single multi-functional system replaces what would traditionally require multiple dedicated cooling systems, significantly reducing overall system weight.
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
This integration reduces system weight and complexity by utilizing cryogenic fluids as a heat exchange medium, enhancing power generation and environmental control efficiency while simplifying onboard systems.
Implementation Method 1
a heat exchanger operatively coupled between the outlet portion of the turbine and the inlet element of the turbine portion in the APU
Implementation Method 2
an intercooler heat exchanger operatively connected between the compressor and the combustor, the heat exchange member being operatively connected to the intercooler heat exchanger
Implementation Method 3
a recuperator operatively connected between the outlet element of the turbine portion and the heat exchange member
Implementation Method 4
a fuel cell operatively connected between the compressor and the combustor, the fuel cell being further operatively connected to the cryogenic fluid preheater
Implementation Method 5
a pump operatively connected between the source of cryogenic fluid and heat exchange member
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
An aircraft system includes a turbine engine (32, 34) having a compressor (44), a combustor (48) having an inlet (105) and an outlet (107), and a turbine (46) having an inlet portion (110) and an outlet portion (112). An auxiliary power unit (37), APU, is operatively connected to the turbine engine (32, 24). The APU (77) includes a compressor portion (70), a generator (74), and a turbine portion (72). The compressor portion (70) is operatively connected to the turbine portion (72) through the generator (74). A source of cryogenic fluid (62) is operatively connected to the turbine engine (32, 34) and the APU (37). A heat exchange member (84) includes an inlet section (116) operatively connected to the source of cryogenic fluid (62), a first outlet section (120) operatively connected to the turbine engine (32, 34) and a second outlet section (122) operatively connected to the compressor portion (70).