Aircraft Propulsion With Independent Turbocompressor Speed Control
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Solution Overview
Problem
Existing aircraft propulsion systems, particularly for unmanned aerial vehicles (UAVs), lack efficiency and flexibility in power generation and propulsion, with conventional configurations often requiring complex mechanical couplings that limit packaging options and operational optimization.
Innovation Solution
A propulsion system for UAVs featuring a mechanically independent engine and turbocompressor assembly, combined with an electrical system including motor-generators and a cooling fan, allowing for independent speed control and flexible packaging configurations, and incorporating an intercooler and interburner for improved energy management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional mechanical couplings are used to connect the engine and turbocompressor, then structural integrity is maintained, but packaging flexibility and operational optimization are limited
Solution Approach 1:
The propulsion system is divided into mechanically independent subsystems: the engine assembly and the turbocompressor assembly are separated by a fluid coupling mechanism rather than direct mechanical connection. This segmentation allows each component to be packaged and positioned independently, providing flexibility in aircraft integration while reducing the complexity of mechanical linkages.
Solution Approach 2:
A fluid coupling mechanism acts as an intermediary between the engine and turbocompressor, transmitting power and control signals without direct mechanical contact. This intermediary enables flexible packaging configurations and independent speed control of each component while maintaining operational integrity.
2Ease of operation
If the engine and turbocompressor are mechanically coupled, then power transmission is direct, but independent speed control and operational optimization are restricted
Solution Approach 1:
The direct mechanical power transmission system is replaced with a fluid coupling mechanism that transmits power and control signals without mechanical contact. This substitution enables independent speed control of the engine and turbocompressor while maintaining efficient power transmission through the fluid medium.
Solution Approach 2:
The system incorporates variable speed drive mechanisms and control systems that allow dynamic adjustment of the engine and turbocompressor speeds independently. This dynamic control capability enables optimization of each component's operating point based on real-time aircraft requirements while maintaining effective power transmission.
3Loss of energy
If complex mechanical couplings are used to connect propulsion components, then structural integrity is maintained, but fuel consumption and mechanical complexity increase
Solution Approach 1:
The complex mechanical coupling mechanism is extracted and replaced with a fluid coupling system. This removal of the mechanical linkage eliminates associated friction losses, mechanical inefficiencies, and complexity while maintaining the necessary power transmission and control functions, thereby reducing fuel consumption.
Solution Approach 2:
The system employs variable speed control and optimized operating parameters for the engine and turbocompressor, allowing each component to operate at its most efficient point. This parameter optimization reduces fuel consumption while the fluid coupling mechanism eliminates mechanical 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
Facilitates efficient power generation and propulsion, optimizing performance across varying altitudes and conditions while reducing mechanical complexity and fuel consumption, and enabling versatile packaging within the aircraft.
Implementation Method 1
The intercooler includes a first heat exchanger side having a first inlet and a first outlet and a second heat exchanger side having a second inlet and a second outlet. The first outlet is connected in fluid communication with the air inlet. The second inlet is connected in fluid communication with the air intake.
Implementation Method 2
The cooling fan may be connected in fluid communication with and between the air intake and the second heat exchanger side with the cooling fan inlet connected in fluid communication with the air intake and the at least one cooling fan outlet connected in fluid communication with the second inlet.
Data Source
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AI summary
A propulsion system (20) for an aircraft includes an air intake (28), an engine assembly (22), a turbocompressor assembly (24), an electrical assembly (26), and at least one propulsor (32). The engine assembly (22) includes an engine (34). The engine (34) includes an air inlet (44), an exhaust outlet (46), and an engine output shaft (42). The turbocompressor assembly (24) includes a turbocompressor (62). The turbocompressor (62) includes a turbine (68) and a compressor (66). The turbine (68) and the compressor (66) form a rotational assembly (78). The rotational assembly (78) includes a shaft (80), a bladed turbine rotor (84) of the turbine, and a bladed compressor rotor (82) of the compressor. The shaft (80) interconnects the bladed turbine rotor (84) and the bladed compressor rotor (82). The turbine (68) includes a turbine inlet (74) and a turbine outlet (76). The turbine inlet (74) is connected in fluid communication with the exhaust outlet (46). The compressor (68) includes a compressor inlet (70) and a compressor outlet (72). The compressor inlet (70) is connected in fluid communication with the air intake (28). The rotational assembly (78) is mechanically independent of the engine output shaft (42).