Jet Engine Thermal Transport Bus Pump Sizing for SFC Optimization
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Solution Overview
Problem
Designing a thermal transport bus (TTB) pump for aircraft jet engines that is neither oversized nor undersized, while providing optimal specific fuel consumption (SFC) benefits, is challenging due to the lack of conventional design standards that balance pump size with SFC improvement, leading to uncertain and time-consuming analysis processes.
Innovation Solution
The TTB pump is redesigned to achieve specific mass flow characteristics and heat transfer rates, establishing relationships between pump power, rotor diameter, and fuel flow rate, resulting in a pump size that optimizes SFC without increasing weight or volume, thereby improving engine efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a thermal transport bus pump is designed with larger size to provide sufficient mass flow and heat transfer, then heat transfer rate is improved, but weight and volume increase
Solution Approach 1:
The patent applies parameter changes by optimizing the pump's mass flow rate and pressure rise characteristics to match specific engine operating conditions. By adjusting these parameters rather than simply increasing pump size, the design achieves sufficient heat transfer rate while controlling weight and volume.
Solution Approach 2:
The patent implements variable speed operation capability in the TTB pump, allowing it to dynamically adjust its performance characteristics based on real-time engine conditions. This dynamic operation enables the pump to provide optimal mass flow and heat transfer across different operating regimes without requiring a larger, heavier fixed-performance pump.
2Power
If pump size is increased to improve mass flow rate, then energy transfer is improved, but device complexity increases
Solution Approach 1:
The patent optimizes the pump's performance parameters (mass flow rate, pressure rise) to match engine requirements rather than using a larger, more complex pump design. This parameter-matching approach achieves the required energy transfer while maintaining simpler pump architecture.
Solution Approach 2:
The TTB pump is designed to serve multiple functions: circulating the thermal transport bus fluid, providing heat transfer, and enabling variable speed operation for different engine conditions. By integrating these functions into a single pump unit rather than using multiple specialized components, the design achieves high mass flow rate capability while managing overall device complexity.
3Reliability
If pump is oversized to ensure sufficient performance across all operating conditions, then reliability is improved, but weight and volume increase
Solution Approach 1:
The patent implements variable speed operation that allows the pump to adapt its performance to match actual engine conditions in real-time. This dynamic adjustment ensures reliable performance across all operating conditions while avoiding the need for an oversized pump that would weigh more and occupy more space.
Solution Approach 2:
The pump's operating parameters (speed, mass flow rate, pressure rise) are dynamically adjusted based on engine conditions to ensure sufficient performance reliability. This parameter optimization allows the use of a lighter, more compact pump design compared to a static oversized pump configuration.
4Ease of manufacture
If conventional design standards are used for TTB pump, then ease of manufacture is improved, but ability to optimize SFC is worsened
Solution Approach 1:
The patent applies parameter changes by establishing specific relationships between pump power, rotor diameter, and fuel flow rate to optimize SFC. These parameter relationships are designed to work with conventional manufacturing capabilities while achieving superior fuel efficiency compared to standard pump designs.
Solution Approach 2:
The patent applies local quality by optimizing specific pump characteristics (mass flow rate, pressure rise, rotor diameter) for SFC optimization in particular operating conditions rather than using a generic design. This localized optimization maintains compatibility with conventional manufacturing while improving fuel efficiency.
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 approach enhances engine SFC by increasing energy transfer to heat sink fluids, reducing fuel consumption, and providing space for other components without adding substantial weight or size to the engine.
Implementation Method 1
a pump configured to generate a pump power (Ppump) to pressurize the working fluid in the thermal transport bus
Implementation Method 2
a thermal transport bus configured to transfer heat from a working fluid to a heat sink fluid
Data Source
AI summary
Jet engine thermal transport bus pumps are disclosed. Disclosed herein is an aircraft comprising a gas turbine engine configured to burn fuel at a fuel flow rate to generate an engine power (Pengine), the fuel characterized by a first specific heat capacity (cp_fuel) and a net heat of combustion (NHCfuel); and a thermal management system configured to transfer heat from a working fluid to a heat sink fluid, the working fluid characterized by a second specific heat capacity (cp_pump) and a first density (ρpump), the thermal management system including a pump configured to generate a pump power (Ppump) to pressurize the working fluid, and whereinPOW=Ppump(cp_pumpcp_water)(ρwaterρpump)2,FFR=(PengineNHCfuel)(cp_fuelcp_pump),0.008≤POW/FFR5/3≤12, FFR is between 0.05 pounds-mass per second and 16 pounds-mass per second, and ρwater and cp_water is the density and specific heat capacity of water, respectively.