H-TRBCC Propulsion System with Superconducting MHD Augmentation
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Solution Overview
Problem
Current hypersonic aircraft propulsion systems are inefficient and complex, with high weight and volume, limiting their ability to achieve and maintain speeds above Mach 5.0, which is necessary for timely and effective strikes in modern military and space operations.
Innovation Solution
A Hybrid Turbine Rocket Based Combined Cycle (H-TRBCC) propulsion system that integrates a shaftless turbomachinery architecture with electric Magnetohydrodynamic (MHD) augmentation, enabling tri-mode combustion across subsonic, transonic, and supersonic regimes, and utilizing superconducting technology for efficient power generation and plasma combustion, reducing weight and volume while increasing thrust-to-weight ratio and specific fuel consumption efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional hypersonic propulsion systems are used, then the aircraft can achieve hypersonic speeds, but the systems are inefficient and complex with high weight and volume
Solution Approach 1:
The patent combines multiple propulsion modes (turbojet, ramjet, scramjet) into a single integrated H-TRBCC propulsion system that operates seamlessly across different Mach numbers. The system merges mechanical thrust generation with electric power generation and MHD acceleration in one unified architecture, eliminating the need for separate propulsion systems and reducing overall complexity.
Solution Approach 2:
The H-TRBCC propulsion system performs multiple functions simultaneously: it generates thrust for hypersonic flight, generates electric power (20 MW+), and provides MHD acceleration. The single common flow path core handles all three functions, making the system universally applicable across the entire hypersonic flight regime from Mach 5.0 to Mach 10.0+.
2Speed
If conventional propulsion systems are used, then the aircraft can reach hypersonic speeds, but the volume and weight are excessive
Solution Approach 1:
The patent employs a nested architecture where the turbojet core is contained within the ramjet inlet, which is contained within the scramjet inlet, creating a compact nested structure. The MHD acceleration rings are nested around the common flow path core, and the superconducting generator is integrated within the turbine rotor, maximizing space utilization and minimizing overall volume.
Solution Approach 2:
The system utilizes superconducting technology to change the electrical resistance parameter from finite to zero, enabling efficient power generation and MHD acceleration without conventional electrical systems. This parameter change allows for compact, high-efficiency energy conversion components that reduce overall system volume while maintaining hypersonic speed capability.
3Loss of energy
If current engine designs are used, then thrust can be generated, but thermal and aerodynamic efficiency are insufficient
Solution Approach 1:
The patent replaces conventional mechanical compression and combustion systems with superconducting magnetic field-based energy conversion and MHD acceleration. The superconducting generator converts mechanical energy to electrical energy with near-zero loss, and the MHD accelerator uses electromagnetic fields to accelerate exhaust gases, eliminating mechanical friction and thermal losses associated with conventional turbines and combustors.
Solution Approach 2:
The system utilizes plasma phase transition in the MHD acceleration process, where exhaust gases are ionized and accelerated by electromagnetic fields. This phase transition from neutral gas to plasma enables efficient energy transfer and thrust generation with reduced thermal and aerodynamic losses compared to conventional combustion systems.
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 H-TRBCC propulsion system achieves unprecedented thermal and aerodynamic efficiency gains, with projected efficiency improvements of over 65% and the ability to generate high electric power for directed energy weapons, allowing for seamless operation from runway lift-off to Mach 8.0 with reduced drag and component complexity.
Implementation Method 1
Embedded electric power generation utilizing proprietary superconducting generation architecture in the turbine core, at multi-megawatt levels
Implementation Method 2
an embedded MHD augmenting accelerator drive integrated to the aft nozzle
Implementation Method 3
plasma combustion, virtual cowl and shock train control systems
Data Source
AI summary
An aerospace hybrid hypersonic propulsion system which has a common core airflow path through the engine combining subsonic, transonic, supersonics and hypersonic propulsion system and architecture in such a way that five known engine cycles known in the art are configured and connected to operate seamlessly with a hybrid electric and thermal cycle.