Open Rotor Propulsion With Bypass Flowpath Power Distribution
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Solution Overview
Problem
Existing aircraft propulsion systems with open propulsor rotors lack efficiency and require improvements in power distribution and energy management between the turbine engine and the propulsor rotor.
Innovation Solution
A propulsion system with a turbine engine and open propulsor rotor, utilizing a first geartrain and a bypass flowpath, along with a first and second gear system, to independently drive the fan and propulsor rotors, enhancing efficiency through planetary and star gear systems, and incorporating a heat exchanger in the bypass flowpath to optimize energy use.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a turbine engine with open propulsor rotor is used, then thrust is generated, but propulsion efficiency is insufficient
Solution Approach 1:
The propulsion system is segmented into two independent flowpaths: a core flowpath for high-speed thrust and a bypass flowpath for additional propulsion. This segmentation allows each flowpath to be optimized independently, with the core flowpath handling high-energy exhaust and the bypass flowpath utilizing lower-energy air, thereby improving overall propulsion efficiency and reducing energy loss.
Solution Approach 2:
The turbine engine is designed to serve multiple functions simultaneously: generating core thrust through the core flowpath, providing bypass propulsion through the bypass flowpath, and enabling heat exchange operations. This multi-functionality allows the same engine structure to improve propulsion efficiency while managing energy utilization across different operational modes.
2Power
If power is distributed to both fan and propulsor rotor, then propulsion capability increases, but device complexity increases
Solution Approach 1:
A first geartrain acts as an intermediary mechanism between the turbine engine and the rotors, mediating the power distribution to both the fan and the propulsor rotor. This intermediary gear system enables independent control and optimization of power delivery to each rotor, achieving enhanced propulsion capability while managing the complexity through a structured transmission approach.
3Loss of energy
If bypass flowpath is added, then energy utilization improves, but device complexity increases
Solution Approach 1:
The bypass flowpath is merged with the core flowpath structure, allowing both flowpaths to coexist within the same engine architecture. This merging enables the system to utilize bypass air for additional propulsion and heat exchange operations without requiring completely separate structures, thereby improving energy utilization while controlling the increase in device 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
Enhances propulsion efficiency by optimizing power distribution and reducing drag, while utilizing bypass air for heat exchange, thereby improving overall aircraft performance.
Implementation Method 1
incorporating a heat exchanger in the bypass flowpath to optimize energy use
Data Source
AI summary
A propulsion system for an aircraft includes an open propulsor rotor and a turbine engine. The turbine engine includes a fan section, an engine core, a first geartrain, a core flowpath and a bypass flowpath. The fan section includes a fan rotor. The engine core includes a first rotating assembly, a low pressure compressor section, a high pressure compressor section, a combustor section, a high pressure turbine section and a low pressure turbine section. The first rotating assembly drives rotation of the open propulsor rotor and the fan rotor through the first geartrain. The core flowpath extends through the low pressure compressor section, the high pressure compressor section, the combustor section, the high pressure turbine section and the low pressure turbine section. The bypass flowpath extends outside of and along the engine core.