Hybrid Flight Vehicle Second Turbine High-Pressure Gas Utilization
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Solution Overview
Problem
Existing hybrid flight vehicles equipped with gas turbine engines suffer from low thermal efficiency as they merely exhaust high-pressure gas generated by the turbine without utilizing it effectively to drive rotors.
Innovation Solution
Incorporating a second turbine system, comprising tip turbines that utilize high-pressure gas outputted from the gas turbine engine to drive rotors, in conjunction with a generator and motor-generators to optimize energy usage and improve thermal efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If high-pressure gas generated by the gas turbine engine is merely exhausted without utilization, then the system structure remains simple, but thermal efficiency deteriorates
Solution Approach 1:
A second turbine is introduced as an intermediary device to utilize the high-pressure gas between the gas turbine engine and the exhaust system. This second turbine drives the rotors through a transmission mechanism, thereby extracting useful work from the high-pressure gas that would otherwise be wasted, improving thermal efficiency without completely redesigning the exhaust system
Solution Approach 2:
The high-pressure gas from the gas turbine engine serves multiple functions: it drives the first turbine connected to the compressor, and simultaneously drives the second turbine connected to the rotors. This multi-functional utilization of the same energy source improves overall thermal efficiency by extracting work at different stages of the gas expansion process
2Loss of energy
If a second turbine system is added to utilize high-pressure gas, then thermal efficiency improves, but device complexity increases
Solution Approach 1:
The second turbine system is integrated with the existing rotor drive mechanism. The transmission mechanism that transmits power from the second turbine to the rotors is combined with the existing mechanical structure, merging the new energy utilization path with the existing drive system to minimize additional complexity
Solution Approach 2:
The system dynamically switches between different power sources and configurations. The control system adjusts the operation of the second turbine and transmission mechanism based on flight conditions, enabling the system to optimize energy efficiency while managing complexity through adaptive control rather than fixed mechanical configurations
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 enhances thermal efficiency by effectively utilizing high-pressure gas to drive rotors, reducing mechanical losses and improving energy efficiency during flight operations.
Implementation Method 1
a gas turbine engine (16) attached to the frame (12) and incorporating a compressor (16a) and a first turbine (16b) adapted to rotate integrally with the compressor (16a)
Implementation Method 2
a second turbine (26) provided independently of the gas turbine engine (16) and configured to drive the multiple rotors (14) when supplied high pressure gas outputted from the gas turbine engine (16)
Implementation Method 3
a generator (20) connected to the output shaft of the gas turbine engine (16) and configured to generate electric power
Implementation Method 4
multiple motor-generators (24) connected to the battery (22) and the rotating shafts (14s) of the multiple rotors (14), the multiple motor-generators (24) being configured to drive the multiple rotors (14) when power is supplied from the battery (22)
Data Source
AI summary
In a hybrid flight vehicle, having four rotors configured to produce thrust to propel a frame, a gas turbine engine incorporating a compressor and a first turbine adapted to rotate integrally with the compressor, a generator configured to generate electric power, a battery configured to store power generated by the generator, four motor-generators connected to the battery and the multiple rotors to drive the rotors when power is supplied from the battery, while generating power when driven by the rotors. In the vehicle, there is provided a second turbine provided independently of the gas turbine engine and configured to drive the rotors when supplied high pressure gas outputted from the gas turbine engine.