Hybrid Combustor Assembly with Segmented RDC and Primary Chamber
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Solution Overview
Problem
Rotating detonation combustion systems face inefficiencies across varying pressure and temperature conditions, limiting their operability and efficiency in propulsion systems.
Innovation Solution
A hybrid combustion system incorporating a rotating detonation combustion (RDC) system with a deflagrative combustion system, featuring a fuel manifold assembly that provides separate fuel flows to the RDC system and primary combustion chamber, optimized for different operating conditions, and a nozzle design with a converging-diverging configuration to maintain efficiency across multiple conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a rotating detonation combustion system is used to improve efficiency, then specific fuel consumption is reduced, but the system becomes inefficient across varying pressure and temperature conditions
Solution Approach 1:
The combustion system is divided into two separate systems: a rotating detonation combustion (RDC) system and a primary combustion chamber. Each system is optimized for different operating conditions, allowing the overall system to maintain efficiency across varying pressures and temperatures while preserving the fuel consumption benefits of detonation combustion.
Solution Approach 2:
The system dynamically switches between RDC mode and primary combustion chamber mode based on operating conditions. The RDC system operates at steady-state conditions for optimal efficiency, while the primary combustion chamber handles transient conditions, creating a dynamic adaptation strategy that maintains performance across the full operating range.
2Productivity
If the RDC system is optimized for steady-state conditions, then efficiency is improved, but the system cannot handle transient conditions
Solution Approach 1:
The combustion system is divided into two separate systems: a rotating detonation combustion (RDC) system and a primary combustion chamber. Each system is optimized for different operating conditions, allowing the overall system to maintain efficiency across varying pressures and temperatures while preserving the fuel consumption benefits of detonation combustion.
Solution Approach 2:
The primary combustion chamber is designed to handle transient conditions and provide supplemental combustion capacity. By having this additional combustion system, the RDC system can focus on its optimal steady-state operation while the primary chamber absorbs the transient demands, ensuring overall system flexibility without compromising RDC efficiency.
3Reliability
If a steep pressure drop is provided to prevent backflow in the RDC system, then backflow is prevented, but efficiency benefits are reduced
Solution Approach 1:
A hybrid combustion system serves as an intermediary between the RDC system and the downstream components. This hybrid system includes a deflagrative combustion zone that acts as a buffer, allowing the RDC system to maintain its pressure characteristics for efficiency while the hybrid combustion zone manages the pressure transition to prevent backflow, thus preserving RDC efficiency benefits.
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 hybrid system improves specific fuel consumption and fuel burn efficiency while maintaining operability at various conditions, allowing the RDC system to operate effectively at steady-state pressures and temperatures, while the primary combustion chamber handles transient conditions.
Implementation Method 1
high energy ignition detonates a fuel/air mixture that transitions into a detonation wave (i.e., a fast moving shock wave closely coupled to the reaction zone). The detonation wave travels in a Mach number range greater than the speed of sound (e.g., Mach 4 to 8)
Implementation Method 2
The nozzle defines a converging-diverging nozzle... the nozzle inlet is configured to receive a flow of oxidizer... the nozzle further defines a throat between the nozzle inlet and the nozzle outlet
Implementation Method 3
Such propulsion systems generally rely upon deflagrative combustion to burn a fuel/air mixture... The hybrid combustion system incorporates a rotating detonation combustion (RDC) system with a deflagrative combustion system
Data Source
AI summary
A hybrid combustion system, and method of operation, for a propulsion system is provided. The hybrid combustion system defines a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The hybrid combustion system includes a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall. The nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, and the nozzle inlet is configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle. The hybrid combustion system further includes an inner liner extended generally along the longitudinal direction; an outer liner extended generally along the longitudinal direction and disposed outward of the inner liner along the radial direction; a bulkhead wall disposed at the upstream end of the inner and outer liners, in which the bulkhead wall extends generally in the radial direction and couples the inner liner and the outer liner, and wherein the inner liner, the outer liner, and the bulkhead wall together define a primary combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the primary combustion chamber; and a fuel manifold assembly extended at least partially through the bulkhead wall, in which the fuel manifold assembly defines a fuel manifold assembly exit disposed adjacent to the primary combustion chamber.