Aircraft Fluid Delivery System for High-Temperature Payload Capacity
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Solution Overview
Problem
Aircraft payload capacity is reduced in high temperature environments due to engine material temperature thresholds limiting thrust generation, which restricts takeoff capabilities.
Innovation Solution
A fluid delivery system controlled by a fluid management system is used to cool engine heat sources during takeoff, increasing payload capacity by managing fluid flow from a tank to the engines using pumps and valves, and purging the fluid during flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If engine material temperature thresholds are used to limit thrust generation in high temperature environments, then engine reliability is maintained, but payload capacity is reduced
Solution Approach 1:
The fluid delivery system is activated before takeoff to pre-cool the engine heat sources, allowing the engines to operate at higher thrust levels during takeoff without exceeding material temperature thresholds. This preliminary cooling action enables increased payload capacity while maintaining engine reliability.
Solution Approach 2:
A fluid (water) is introduced as an intermediary cooling medium between the engine heat sources and the environment. The fluid absorbs excess heat from the engines during takeoff, enabling higher thrust generation without compromising engine material temperature limits, thus resolving the contradiction between payload capacity and engine reliability.
2Quantity of substance
If a fluid delivery system is activated to cool engine heat sources during takeoff, then payload capacity is increased, but device complexity is increased
Solution Approach 1:
The fluid delivery system is designed to serve multiple functions: cooling engine heat sources during takeoff, maintaining engine temperatures during high-performance operations, and potentially serving as a weight compensation system. This multi-functionality justifies the added device complexity by providing comprehensive thermal management capabilities that enable increased payload capacity.
Solution Approach 2:
The system includes automatic activation and purging capabilities that reduce the need for manual intervention. The fluid management system automatically activates cooling when needed and can purge the system of fluid during flight, reducing operational complexity and maintenance requirements despite the added hardware.
3Power
If fluid is used to cool engines during takeoff, then thrust generation is increased, but weight of the aircraft is increased
Solution Approach 1:
The fluid delivery system is designed for periodic or temporary use during critical phases such as takeoff and high-performance operations, rather than continuous operation. The system can be activated only when maximum thrust is needed and purged during cruise flight, minimizing the weight penalty of carrying fluid while maximizing thrust generation when required.
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 cooling of engine heat sources during takeoff allows for increased thrust and payload capacity in high temperature environments, extending engine life and enabling safe takeoff with full passenger and cargo loads.
Implementation Method 1
The fluid delivery system is to cool an engine heat source
Data Source
AI summary
Methods and apparatus to increase a payload capacity of an aircraft are disclosed herein. An example method includes receiving a selection via a control display unit to employ a fluid delivery system during takeoff of an aircraft. The fluid delivery system includes a tank disposed on the aircraft. The example method also includes automatically controlling, via a fluid management system including a processor, a flow of the water from the tank during takeoff in response to the selection. The water is to cool an engine heat source of the aircraft.