Aircraft Bleed Air Compressor Control for Stable Supply Pressure
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The conventional bleed air system for aircraft environmental control systems suffers from energy loss due to the proportional relationship between the auxiliary compressor's rotational frequency and engine rotational frequency, leading to inaccurate pressure supply, and pressure fluctuations in the passage to the air cycle machine.
Innovation Solution
A compressed air supply system with a sensor-controlled driver, such as a continuously variable transmission or electric motor, adjusts the auxiliary compressor's rotational frequency based on pressure and temperature feedback, using circuitry to manage energy loss and pressure fluctuations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the auxiliary compressor's rotational frequency is determined in proportion to the engine's rotational frequency, then the system structure is simple, but energy loss increases and pressure supply accuracy deteriorates
Solution Approach 1:
The patent applies dynamics by making the auxiliary compressor's rotational frequency adjustable rather than fixed proportional to engine speed. The driver (23) enables continuous variation of the compressor speed to match actual air supply demands, transforming a static proportional relationship into a dynamic controlled one that optimizes energy efficiency while maintaining simple system structure.
Solution Approach 2:
The patent changes the rotational frequency parameter of the auxiliary compressor independently from the engine's rotational frequency. By controlling the driver (23) to adjust the compressor speed based on actual pressure and temperature conditions in the air system, the system achieves energy efficiency without increasing structural complexity.
2Device complexity
If the auxiliary compressor's rotational frequency is determined in proportion to the engine's rotational frequency, then the system structure is simple, but pressure supply accuracy deteriorates
Solution Approach 1:
The patent implements feedback control by using sensors to detect pressure and temperature in the air system, then using this information to adjust the driver (23) control signals. This closed-loop feedback mechanism enables accurate pressure supply while maintaining simple system structure, as the feedback automatically compensates for variations without adding complex manual control systems.
3Measurement precision
If the auxiliary compressor's rotational frequency is increased to maintain pressure, then pressure supply accuracy improves, but energy loss increases
Solution Approach 1:
The patent applies dynamics by enabling the auxiliary compressor's rotational frequency to dynamically adjust to actual system needs rather than running at high constant speed. The driver (23) modulates the compressor speed based on real-time pressure and temperature conditions, achieving accurate pressure supply only when necessary and reducing energy consumption during normal operation.
Solution Approach 2:
The patent changes the rotational frequency parameter of the auxiliary compressor based on actual system conditions rather than maintaining a constantly high value. By adjusting this parameter dynamically through the driver (23) control system, the patent achieves both accurate pressure supply and energy efficiency.
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 system prevents energy waste and ensures accurate pressure supply to aircraft air systems by controlling the auxiliary compressor's rotational frequency, maintaining stable pressure despite fluctuations.
Implementation Method 1
a sensor that detects pressure and temperature of the supply passage
Implementation Method 2
an auxiliary compressor including a compressor inlet and a compressor outlet, the compressor inlet being fluidly connected to the bleed air passage
Data Source
AI summary
A compressed air supply system of an aircraft includes: a bleed air passage through which bleed air from a gas turbine engine flows; an auxiliary compressor including a compressor inlet and a compressor outlet, the compressor inlet being fluidly connected to the bleed air passage; a supply passage which is fluidly connected to the compressor outlet and through which compressed air from the auxiliary compressor is supplied to an air system of the aircraft; a driver that rotates the auxiliary compressor; a sensor that detects pressure or temperature of the supply passage; and circuitry that controls an output rotational frequency of the driver in accordance with a detection signal of the sensor.