Fan Case Evaporator Layout for Compact Aircraft Steam Injection
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Solution Overview
Problem
Existing aircraft propulsion systems face challenges in incorporating large heat exchangers for steam generation due to space constraints, which affect the efficiency of thermal communication between exhaust gas flow and recovered water.
Innovation Solution
An evaporator system with heat exchanger stages mounted to the fan case of the propulsion system, utilizing an exhaust duct to route exhaust gas flow for steam generation, including a bifurcation and axial portions to optimize thermal communication within the limited space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If large heat exchangers are used for steam generation, then thermal communication efficiency between exhaust gas flow and recovered water is improved, but space constraints in the propulsion system are worsened
Solution Approach 1:
The heat exchanger is mounted within the fan case structure, nesting the thermal communication component within the existing propulsion system housing. This allows the heat exchanger to utilize the internal volume of the fan case, thereby improving thermal communication efficiency without increasing the overall propulsion system volume.
Solution Approach 2:
The heat exchanger is positioned in a three-dimensional space within the fan case, utilizing vertical and radial dimensions rather than only horizontal extension. This dimensional arrangement allows efficient thermal communication between exhaust gas and recovered water while maintaining a compact footprint in the propulsion system.
2Volume of moving object
If heat exchanger is mounted on fan case, then space utilization is improved, but system complexity is worsened
Solution Approach 1:
The fan case serves dual functions: it houses the fan and provides mounting structure for the heat exchanger. This multi-functional design allows the heat exchanger to be integrated into the existing fan case structure, achieving compact system arrangement without proportionally increasing device complexity.
Solution Approach 2:
The mounting structure integrates the heat exchanger with the fan case assembly, combining thermal management functionality with the existing structural housing. This merging approach achieves space-efficient integration while leveraging existing structural components, thereby limiting the increase in overall system complexity.
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 solution enables efficient steam generation and injection into the core engine, improving propulsive efficiency without increasing compressor work, while maintaining a compact system architecture.
Implementation Method 1
a condenser assembly where water is condensed from the exhaust gas flow that is generated by the core engine
Implementation Method 2
an evaporator system where heat from the exhaust gas flow is used to transform water from the condenser assembly into a steam flow
Implementation Method 3
transform water from the condenser assembly into a steam flow
Data Source
AI summary
An aircraft propulsion system includes an exhaust duct that defines a flow path for the exhaust gas flow to a condenser assembly, and an evaporator system where heat from the exhaust gas flow is used to transform water from the condenser assembly into a steam flow for injection into the core engine. The evaporator system includes at least one heat exchanger stage that is mounted to the fan case and is in communication with the exhaust gas flow routed through the exhaust duct.