An aircraft system includes a fan, a differential pressure sensor, a temperature sensor, and a system controller. The fan provides airflow for at least one heat exchanger. The differential pressure sensor senses a pressure difference between an inlet of the fan and a diffuser exit of the fan. The te
An aircraft system includes a fan, a differential pressure sensor, a temperature sensor, and a system controller. The fan provides airflow for at least one heat exchanger. The differential pressure sensor senses a pressure difference between an inlet of the fan and a diffuser exit of the fan. The temperature sensor senses a temperature at the inlet of the fan. The system controller is configured to receive the sensed pressure difference, the sensed temperature, and a speed of the fan, and determines an operating point of the fan based upon the sensed pressure difference, the speed of the fan, and the sensed temperature. The operating point is indicative of contamination of the at least one heat exchanger.
대표청구항▼
1. An aircraft system comprising: a fan that provides airflow for at least one heat exchanger;a differential pressure sensor that senses a pressure difference between an inlet of the fan and a diffuser exit of the fan;a temperature sensor that senses a temperature at the inlet of the fan; anda syste
1. An aircraft system comprising: a fan that provides airflow for at least one heat exchanger;a differential pressure sensor that senses a pressure difference between an inlet of the fan and a diffuser exit of the fan;a temperature sensor that senses a temperature at the inlet of the fan; anda system controller configured to receive the sensed pressure difference, the sensed temperature, and a speed of the fan, wherein the system controller determines an operating point of the fan, wherein the operating point of the fan is the sensed pressure difference at a respective corrected speed of the fan, and wherein the respective corrected speed of the fan is the speed of the fan compensated by the sensed temperature, and wherein the operating point is indicative of contamination of the at least one heat exchanger;wherein the system controller is further configured to compare the operating point of the fan to a threshold indicative of an unstable operating condition of the fan, wherein the threshold is a threshold pressure difference at the respective corrected speed of the fan; andwherein the system controller is further configured to reduce the speed of the fan if the operating point of the fan is greater than the threshold, wherein the speed of the fan is reduced to a corrected speed of the fan below which the fan operates in a stable operating condition. 2. The aircraft system of claim 1, further comprising an exit duct connected between an outlet of the fan and ambient air, wherein the system controller determines a flow through the fan based upon the sensed pressure difference, and wherein the system controller determines a pressure loss for the exit duct based upon the determined flow. 3. The aircraft system of claim 2, wherein the system controller determines an outlet pressure of the fan based upon the determined pressure loss for the exit duct, and wherein the system controller determines an inlet pressure of the fan based upon the determined outlet pressure and the sensed pressure differential. 4. The aircraft system of claim 3, wherein the system controller determines the operating point of the fan based further upon the determined inlet pressure of the fan. 5. The aircraft system of claim 1, further comprising a pressure sensor that measures an inlet pressure of the fan, wherein the system controller determines the operating point of the fan based further upon the measured inlet pressure of the fan. 6. The aircraft system of claim 1, wherein the system controller further provides a maintenance indication on a communication bus upon the determined operating point of the fan reaching the threshold. 7. The aircraft system of claim 1, further comprising a motor controller that drives the fan, wherein the speed of the fan is provided to the system controller from the motor controller. 8. The aircraft system of claim 1, further comprising a speed sensor, wherein the fan is turbine driven and the speed sensor provides the speed of the fan to the system controller. 9. A method of detecting contamination of at least one heat exchanger in an aircraft system, the method comprising: sensing, by a differential pressure sensor, a pressure differential between an inlet of a fan and a diffuser exit of the fan;sensing, by a temperature sensor, an inlet temperature at the inlet of the fan;providing the sensed pressure differential and sensed inlet temperature to a system controller;determining, by the system controller, an operating point of the fan, wherein the operating point of the fan is the sensed pressure difference at a respective corrected speed of the fan, and wherein the respective corrected speed of the fan is the speed of the fan compensated by the sensed temperature, wherein the operating point of the fan is indicative of contamination of the at least one heat exchanger;comparing the operating point of the fan to a threshold indicative of an unstable operating condition of the fan, wherein the threshold is a threshold pressure difference at the respective corrected speed of the fan; andreducing the speed of the fan using the system controller if the operating point of the fan exceeds the threshold, wherein the speed of the fan is reduced to a corrected speed of the fan below which the fan operates in a stable operating condition. 10. The method of claim 9, further comprising: determining, by the system controller, a flow through the fan based upon the sensed pressure differential;determining, by the system controller, a duct pressure loss of an outlet duct, wherein the outlet duct is connected between an outlet of the fan and ambient air;determining, by the system controller, an outlet pressure at the outlet of the fan based upon the duct pressure loss and an ambient pressure of the ambient air; anddetermining, by the system controller, an inlet pressure at the inlet of the fan based upon the determined outlet pressure and the sensed pressure differential, wherein determining the operating point of the fan is further based upon the determined inlet pressure. 11. The method of claim 9, further comprising measuring an inlet pressure at the inlet of the fan using an inlet pressure sensor, wherein determining the operating point of the fan is further based upon the measured inlet pressure. 12. The method of claim 9, further comprising: providing a maintenance indication using the system controller if the determined operating point of the fan exceeds the threshold. 13. The method of claim 9, further comprising providing the speed of the fan to the system controller from a motor controller, wherein the motor controller controls the speed of the fan. 14. The method of claim 9, further comprising providing the speed of the fan to the system controller from a speed sensor, wherein the fan is turbine driven and the system controller controls the speed of the fan.
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Sauterleute Alfred,DEX, Air-conditioning system for airplane cabin.
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