Flight Vehicle Power System With Closed-Loop Heat Pump
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Solution Overview
Problem
Traditional recuperators used in flight vehicles are heavy due to the materials employed, such as nickel alloys, leading to low power-to-weight ratios in small gas turbines.
Innovation Solution
A power system comprising a first power plant with a closed fluid loop and a compressor, and a second power plant that combusts a fuel-fluid mixture, where the first power plant operates as a heat pump using exhaust gases from the second power plant, eliminating the need for a traditional recuperator.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a traditional recuperator is used in a small gas turbine, then thermal efficiency can be improved, but the weight increases significantly due to nickel alloys
Solution Approach 1:
The patent changes the physical state of the working fluid to supercritical conditions (temperature and pressure above critical point), which fundamentally alters the fluid's thermodynamic properties and enables more efficient heat transfer, thereby improving thermal efficiency while reducing the need for heavy recuperator materials
Solution Approach 2:
The patent employs composite material structures in the heat exchanger components, combining materials with different properties to achieve both high thermal efficiency and reduced weight, replacing traditional solid-state nickel alloy recuperators with lighter composite constructions
2Weight of moving object
If small gas turbine size is reduced, then power-to-weight ratio improves, but compression ratio decreases due to physical and manufacturing constraints
Solution Approach 1:
The patent changes the operating parameters of the gas turbine by using supercritical working fluid conditions, which allows the turbine to achieve higher compression ratios despite smaller physical dimensions, overcoming the traditional scaling limitations of small gas turbines
3Temperature
If traditional solid-state recuperator is used, then thermal management is achieved, but power-to-weight ratio is reduced due to heavy nickel alloy materials
Solution Approach 1:
The patent changes the working fluid to a supercritical state and adjusts operating temperature and pressure parameters, enabling more compact and lighter thermal management systems that maintain effective heat transfer while significantly reducing the weight associated with traditional nickel alloy recuperators
Solution Approach 2:
The patent utilizes fluid dynamic principles with supercritical working fluid circulation through the power plant system, replacing heavy solid-state heat transfer components with lighter fluid-based thermal management that achieves the same or better thermal control with reduced 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
The system achieves a higher power-to-weight ratio and thermodynamic efficiency, allowing the primary propulsor to operate independently while providing power to other systems, and improving thermal management of batteries and electronics.
Implementation Method 1
a compressor configured to compress the working fluid
Implementation Method 2
a thermal engine coupled to the compressor and configured to operate the compressor
Implementation Method 3
a second power plant configured to combust a fuel-fluid mixture
Implementation Method 4
the first power plant operates as a heat pump using exhaust gases from the second power plant
Data Source
AI summary
A power system for a flight vehicle includes a first power plant and a second power plant. The second power plant is configured to combust a fuel-fluid mixture. The first power plant includes a closed fluid loop configured to contain a working fluid. The first power plant includes a compressor configured to compress the working fluid. The first power plant includes a thermal engine coupled to the compressor and configured to operate the compressor. In certain configurations, the first power plant includes a container encasing the closed fluid loop, the compressor, and the thermal engine. In various configurations, the power system is coupled to a primary propulsor of the flight vehicle and configured to provide power to the primary propulsor. The power system is separate from the primary propulsor such that the primary propulsor is continuously operable independently of the power system to provide power to operate the flight vehicle.