Aircraft Cabin Blower Active Flow Control
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Solution Overview
Problem
Conventional active flow control systems for aircraft are unsuitable for civil transport aircraft due to their weight and complexity, which erodes the benefits of enhanced aerodynamic performance, as they require additional components and a source of fluid from the auxiliary power unit or engine core bleed.
Innovation Solution
A system that integrates a cabin blower system with a variable geometry compressor and an active flow control system, where the compressor generates pressurized fluid for both environmental control and active flow control, using a fluid supply line to direct the fluid to the active flow control system, and an auxiliary power unit to provide fluid when the cabin blower is inactive, minimizing weight and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a conventional active flow control system is implemented using auxiliary power unit or engine core bleed, then aerodynamic performance is enhanced, but weight and system complexity increase significantly
Solution Approach 1:
The cabin blower system is designed to serve dual purposes: providing pressurized air for environmental control (cabin pressurization and air conditioning) and supplying pressurized fluid for active flow control. This multi-functionality eliminates the need for separate dedicated systems, reducing overall system complexity while maintaining aerodynamic performance benefits.
Solution Approach 2:
The system utilizes existing aircraft infrastructure (cabin blower system with variable geometry compressor) to provide pressurized fluid for active flow control without requiring additional power units or complex fluid management systems. The cabin blower system essentially serves itself by allocating its output to multiple functions including flow control.
2Force
If a conventional active flow control system is implemented using auxiliary power unit or engine core bleed, then aerodynamic performance is enhanced, but aircraft weight increases
Solution Approach 1:
By making the cabin blower system multi-functional (serving both environmental control and active flow control), the patent eliminates the need for additional dedicated components such as separate fluid storage tanks, pumps, and distribution systems that would add significant weight to the aircraft.
Solution Approach 2:
The patent merges the environmental control system and active flow control system into a unified architecture where the cabin blower system provides pressurized fluid to both functions. This consolidation integrates previously separate systems, reducing redundant components and overall aircraft weight.
3Quantity of substance
If engine core bleed is used for active flow control, then pressurized fluid is available, but additional components and fluid distribution infrastructure are required
Solution Approach 1:
The cabin blower system inherently generates pressurized fluid as part of its normal environmental control operation. This pressurized output is then directly utilized by the active flow control system without requiring additional fluid generation equipment, storage infrastructure, or complex distribution networks.
Solution Approach 2:
The cabin blower system acts as an intermediary that bridges environmental control and active flow control functions. It receives ambient air, compresses it to the required pressure, and distributes it to both the environmental control system and the active flow control system through existing infrastructure.
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 solution allows for efficient active flow control without the added weight and energy expenditure of conventional systems, using existing aircraft components to enhance aerodynamic performance while maintaining the benefits of active flow control.
Implementation Method 1
a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate pressurised fluid
Implementation Method 2
ejecting pressurised fluid out of the aircraft across an exterior surface of a movable control element to impart momentum into an air stream flow over the surfaces
Implementation Method 3
flow separation that occurs on the suction side of the element, i.e. where a boundary layer of fluid (gas) on the suction side surface travels against an adverse pressure gradient
Data Source
AI summary
A system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.