Aircraft Water Augmentation Tank Selection for Thrust and Durability
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Solution Overview
Problem
Gas turbine engines face challenges in optimizing water augmentation for performance and durability, as the location and type of water injection vary with operating parameters, and the water tank is heavy and occupies significant space on aircraft.
Innovation Solution
Aircraft propulsion system with a selectively usable water tank and augmentation system, including a controller to operate based on selected modes, allowing water injection into the compressor and combustor sections for intercooling and thrust augmentation, and a removable tank for flexible storage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a water tank is installed on the aircraft to enable water augmentation, then engine performance and durability are improved, but the aircraft experiences increased weight and occupied volume
Solution Approach 1:
The system dynamically adapts the water storage configuration based on flight conditions. The controller determines whether to install a full-size tank, a reduced-size tank, or no tank at all, depending on whether water augmentation is needed for durability enhancement or performance improvement. This dynamic reconfiguration allows the aircraft to carry water only when necessary, reducing unnecessary weight and volume.
Solution Approach 2:
The water storage system is segmented into multiple tank size options (full-size tank, reduced-size tank, or no tank). This segmentation allows the aircraft to select the appropriate tank configuration based on specific mission requirements, enabling flexible weight and volume management while maintaining the capability for both durability enhancement and performance improvement modes.
2Adaptability or versatility
If a large water tank is installed to provide sufficient water for all operating conditions, then both durability enhancement and performance improvement modes are supported, but the aircraft experiences increased weight and occupied volume
Solution Approach 1:
The system dynamically selects between different tank configurations based on the selected mode of operation. When durability enhancement mode is selected, a full-size tank is installed to provide sufficient water for extended periods. When performance improvement mode is selected, a reduced-size tank is installed to minimize weight and volume. This dynamic adaptation maintains versatility while optimizing weight for each specific mission.
Solution Approach 2:
The tank size parameter is changed based on the operating mode. The system can configure the aircraft with different water storage capacities depending on whether the mission requires durability enhancement (full-size tank) or performance improvement (reduced-size tank). This parameter change allows the aircraft to optimize its weight and volume characteristics for each specific operational requirement.
3Power
If water is injected into the core flow to improve engine power, then thrust is increased, but the system complexity increases due to mode selection and tank management
Solution Approach 1:
The controller automatically determines the appropriate tank configuration and water injection parameters based on the selected mode of operation. The system self-manages the complexity of mode selection and tank management by automatically configuring itself, reducing the burden on operators and simplifying the user interface while maintaining the capability for both durability enhancement and performance improvement modes.
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
Enhances engine performance by providing flexible water injection based on operating conditions, reducing weight and space requirements, and improving durability and emissions.
Implementation Method 1
water is injected into the compressor section for cooling a portion of an airflow through the compressor section
Implementation Method 2
water is injected into the combustor to increase a mass flow of the exhaust gas expanded through the main turbine section
Data Source
AI summary
An aircraft propulsion system includes a core engine with a core flow path through a main compressor where an inlet airflow is compressed and communicated to a combustor to generate an exhaust gas flow that is expanded through a main turbine section to generate power used to drive the main compressor and a propulsive fan. A water augmentation system includes at least one location where water is communicated into the core flow path, an aircraft structure that includes a water storage space, and a water storage system that is operable for storing and supplying water to the water augmentation system. The water storage system includes a portion that corresponds to the water storage space, and a controller that is programmed to operate the water augmentation system according to a selected mode of operation.