Aircraft Propulsion Flow Diverters for Continued Operation After Failures
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft propulsion systems lack flexibility and redundancy to handle component failures effectively, leading to potential system shutdowns and reduced operational efficiency.
Innovation Solution
Aircraft propulsion systems incorporating an engine assembly, interburner, turbocompressor, and flow control assembly with configurable diverter subassemblies and electrical components to manage airflow and power generation, enabling operation in various modes including failure scenarios.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional aircraft propulsion systems are used, then the system structure is relatively simple, but the system lacks flexibility and redundancy to handle component failures, leading to potential system shutdowns
Solution Approach 1:
The propulsion system is divided into independent functional modules: engine assembly, turbocompressor assembly, interburner, and flow control assembly. Each module can operate independently or in combination, allowing the system to maintain functionality even if one module fails. The flow control assembly with its diverter subassemblies segments the airflow paths, enabling selective operation of different components based on operational needs or failure conditions.
Solution Approach 2:
The flow control assembly with configurable diverter subassemblies provides multi-functionality by being able to direct airflow to different locations depending on the operational mode. The same flow control assembly can support normal operation, failure scenarios, and various propulsion modes. The interburner can function as part of the engine assembly or independently with the turbocompressor, providing versatile operational capabilities.
2Adaptability or versatility
If the system includes redundant components and flow control mechanisms, then the ability to handle failures improves, but the device complexity increases
Solution Approach 1:
The flow control assembly incorporates dynamically configurable diverter subassemblies that can change their state based on operational requirements. The diverter subassemblies can be positioned in different configurations to direct airflow accordingly, allowing the system to adapt to varying operational modes and failure conditions without requiring separate physical systems for each scenario.
Solution Approach 2:
The flow control assembly acts as an intermediary between the engine assembly and turbocompressor assembly, managing airflow distribution based on operational needs. The diverter subassemblies serve as intermediaries that can redirect airflow to different destinations, enabling the system to achieve operational flexibility without direct complex interconnections between all components.
3Reliability
If the engine exhaust is directed to the interburner for mixing and burning with fuel, then continued propulsion is enabled during failure scenarios, but additional flow control mechanisms are required
Solution Approach 1:
The system enables continuous propulsion by directing engine exhaust to the interburner where it mixes with fuel and continues burning. This continuous combustion process allows the turbocompressor to keep running and generate power even when the main engine fails. The flow control assembly ensures this continuous airflow path is maintained through proper configuration of the diverter subassemblies.
Solution Approach 2:
The system converts the potentially harmful exhaust gas into a useful resource by directing it to the interburner for further combustion. The exhaust gas that would normally be wasted is instead utilized as fuel for the interburner, enabling continued propulsion. This transforms what would be a loss into a beneficial energy source, enhancing system reliability without requiring external fuel storage.
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
Ensures continued propulsion and electrical power generation even in the event of engine, turbocompressor, or generator failures, enhancing system reliability and efficiency.
Implementation Method 1
The interburner is configured to mix and burn a gas from the interburner inlet with fuel to form a combustion gas
Implementation Method 2
The at least one turbocompressor includes a turbine and a compressor. The turbine includes a turbine inlet and a turbine outlet
Implementation Method 3
The compressor includes a compressor inlet and a compressor outlet
Data Source
AI summary
A propulsion system for an aircraft includes an engine assembly, an interburner, a turbocompressor, and a flow control assembly. The engine assembly includes an engine. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The interburner includes an interburner inlet and an interburner outlet. The turbocompressor assembly includes at least one turbocompressor. The at least one turbocompressor includes a turbine and a compressor. The turbine includes a turbine inlet and a turbine outlet. The compressor includes a compressor inlet and a compressor outlet. The flow control assembly includes an engine exhaust diverter subassembly and at least one compressor outlet diverter subassembly. The engine exhaust diverter subassembly is connected to exhaust outlet, the interburner inlet, and the turbine inlet. The at least one compressor outlet diverter subassembly is connected to the compressor outlet, the air inlet, and the interburner inlet.