Turbojet Bleeding System Dynamic Air Intake Control
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Solution Overview
Problem
The existing air bleeding systems in aircraft turbojets are not energy-efficient, leading to high fuel consumption, particularly during take-off, ascent, and cruising phases.
Innovation Solution
A revised air bleeding system that includes a low-pressure air intake, a high-pressure air intake, a compressor, check valves, a high-pressure valve, a cooler, and a control system with pressure sensors to dynamically adjust air flow based on pressure thresholds, allowing for efficient air distribution to the aircraft cabin while minimizing energy consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stress or pressure
If air is bled at intermediate pressure from the high-pressure compressor, then the air pressure for the cabin is sufficient, but fuel consumption increases significantly
Solution Approach 1:
The system changes the pressure parameter at which air is bled from the compressor. Instead of bleeding at intermediate pressure (40 psia), the system bleeds at low pressure (30 psia or lower) during take-off and ascent phases, and at high pressure (above 30 psia) during cruising phase. This dynamic parameter adjustment optimizes the balance between providing sufficient cabin pressure and minimizing fuel consumption.
Solution Approach 2:
The system dynamically adjusts the air bleeding strategy based on the operational phase and pressure conditions. A pressure sensor continuously monitors the pressure at the first air intake, and the controller dynamically switches between different air intake sources (first air intake for low pressure, second air intake for high pressure) to optimize fuel consumption while maintaining cabin pressure requirements.
2Use of energy by moving object
If air is bled at high pressure from the high-pressure compressor, then fuel consumption is reduced, but the air pressure for the cabin becomes insufficient
Solution Approach 1:
The system segments the air intake into two separate sources: a first air intake for bleeding air at low pressure and a second air intake for bleeding air at high pressure. This segmentation allows the system to selectively use each source based on operational requirements, enabling low-pressure bleeding during take-off/ascent and high-pressure bleeding during cruising to optimize both fuel consumption and cabin pressure.
Solution Approach 2:
The controller acts as an intermediary that receives pressure information from the pressure sensor and dynamically directs air flow to the appropriate air intake source. The controller mediates between the conflicting requirements of fuel savings and adequate cabin pressure by making real-time decisions based on monitored pressure conditions.
3Device complexity
If a single air intake is used for all operating conditions, then the system is simple, but it cannot optimize fuel consumption across different phases
Solution Approach 1:
The system segments the air intake function into two separate air intakes (first air intake and second air intake) with distinct functions. The first air intake is used for low-pressure bleeding during take-off and ascent, while the second air intake is used for high-pressure bleeding during cruising. This segmentation enables phase-specific optimization of fuel consumption.
Solution Approach 2:
The system introduces dynamic control through a pressure sensor and controller that monitor pressure conditions and automatically switch between different air intake sources. This dynamic architecture allows the system to adapt to changing operational phases and optimize fuel consumption without requiring manual intervention.
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 system reduces fuel consumption by optimizing air flow and pressure management, achieving savings of 0.7% to 1.7% depending on the turbojet's structure, and ensures compatible air pressure for the aircraft cabin.
Implementation Method 1
a compressor (218) of which the inlet is fluidically connected to the outlet of the second valve (216), and which compresses the air passing therethrough
Implementation Method 2
a check valve (206) of which the inlet is fluidically connected to the outlet of the first valve (215) and to the outlet of the compressor (218), and which prevents the air from moving toward the compressor (218) and the first valve (215)
Implementation Method 3
a cooler (212) intended to cool the air passing therethrough
Data Source
AI summary
A turbojet comprising a low-pressure compressor, a high-pressure compressor and a bleeding system configured to bleed air in the turbojet and to deliver the air to an air system. The bleeding system comprises a first air intake configured to bleed air at low pressure, a second air intake configured to bleed air at high pressure, a first valve and a second valve having inlets connected to the first air intake, a compressor having an inlet connected to an outlet of the second valve, a high-pressure valve connected to the second air intake, a control valve connected to the air system, and a controller to control opening and closing of the valves depending on a pressure at the first air intake.