Turbine Engine Airflow Valve for Multi-Mode Propulsion
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft engine systems face challenges in operating efficiently over a wide speed range, particularly in modulating airflow and combustion processes to optimize performance across varying flight conditions.
Innovation Solution
The aircraft engine incorporates a unique design with a sensor and controller system that manages airflow through an inlet valve and combustion device, allowing operation in multiple modes, including gas turbine, ramburner, and forward speed compression combustor, enabling efficient thrust production across different flight speeds by selectively routing airflow and utilizing auto-ignition processes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional augmenter designs are used to extend speed range, then thrust capability is improved, but cycle penalties occur that reduce operational efficiency
Solution Approach 1:
The system dynamically switches between different operating modes (gas turbine mode and ramburner mode) based on flight conditions. The controller activates the ramburner mode at supersonic speeds to avoid cycle penalties, while using conventional gas turbine mode at subsonic speeds. This dynamic adaptation allows the engine to maintain high efficiency across the entire speed range without suffering from the cycle penalties associated with conventional augmenter designs.
2Productivity
If airflow is modulated to optimize performance across varying flight conditions, then operational efficiency is improved, but system complexity increases due to additional control mechanisms
Solution Approach 1:
The ramburner system serves multiple functions: it acts as a combustion device for supersonic operation, a thrust augmenter for extended performance, and a thermal management system. The same basic ramburner hardware is used across different operating modes, reducing the need for separate control mechanisms for each function. This multi-functionality approach maintains operational efficiency while minimizing the increase in system complexity.
3Power
If auto-ignition processes are utilized for thrust production above sonic speeds, then power generation is improved, but combustion control difficulty increases
Solution Approach 1:
The controller continuously monitors combustion parameters and adjusts fuel injection and airflow to maintain stable auto-ignition. Feedback sensors detect combustion chamber conditions and provide real-time data to the controller, which modulates the fuel-air mixture and ignition timing to optimize thrust production while preventing combustion instability. This feedback control system manages the complexity of auto-ignition processes at supersonic speeds.
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
This design enhances thrust capability and operational efficiency by adapting airflow and combustion processes, providing effective power generation below and above sonic speeds without the cycle penalties associated with conventional augmenter designs.
Implementation Method 1
The sensor 54 measures aircraft flight condition such as speed and altitude, to set forth just two non-limiting examples, and may output any variety of data whether sensed or calculated
Implementation Method 2
The gas turbine engine 62 includes a compressor 72, a core combustor 74, and a turbine 76
Implementation Method 3
The gas turbine engine 62 includes a compressor 72, a core combustor 74, and a turbine 76
Implementation Method 4
The gas turbine engine 62 includes a compressor 72, a core combustor 74, and a turbine 76
Implementation Method 5
The inlet valve 60 can be positioned to permit the core flow 68 to enter the gas turbine engine 62
Implementation Method 6
a second thrust producing mode including an auto-ignition combustor operable to support an auto-ignition process
Implementation Method 7
the bypass valve operable to be positioned to cocoon the gas turbine engine during high temperature conditions
Data Source
AI summary
An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression combustor engine such as a ramjet and/or scramjet. An airflow valve is provided to direct air to a downstream portion of the aircraft engine and can be positioned as a function of the aircraft operating modes. The valve can be used to cocoon the gas turbine engine.