System and method to prevent bleed air over-extraction in aircraft
A pneumatic flow control system for an aircraft includes a control system operating and implementing a software program through a digital environment, the software program having one or more rules; a sensor in digital communication with the control system, the sensor to relay engine power data to the control system; an electronically controlled valve in digital communication with the control system, the electronically controlled valve to control an amount of bleed air flowing therethrough; a first rule defining an engine power parameter and a valve position for the electronically controlled valve and using the engine power data relayed from the sensor, receiving data equating to the engine power parameter activates transmitting a command to the electronically controlled valve to adjust to the valve position; and the valve position is set to restrict flow through the valve to below a threshold limit.
1. A pneumatic flow control system for an aircraft, comprising:
a control system operating a software program, the control system and software program being implemented through a digital environment, the software program having one or more rules associated with preventing an amount of bleed air from over-extraction into an aircraft environment of the aircraft;
at least one sensor in digital communication with the control system, the at least one sensor configured to relay engine power data to the control system;
at least one electronically controlled valve in digital communication with the control system, the at least one electronically controlled valve configured to control the amount of the bleed air flowing therethrough;
the one or more rules include a first rule defining an engine power parameter and a corresponding pre-set valve position, each being user-defined, for triggering a valve adjustment of the at least one electronically controlled valve;
wherein upon detecting a rapid increase in engine power that meets or exceeds the engine power parameter, the control system transmits a command to the at least one electronically controlled valve based on the first rule triggering the valve adjustment, such that the at least one electronically controlled valve dynamically adjusts to the pre-set valve position to restrict flow to within a predetermined range.
2. The system of claim 1 , wherein the control system further comprises a non-transitory memory for storing the software program thereon and a processor for executing the software program.
3. The system of claim 2 , wherein the control system performs the steps of:
receiving the engine power data from the at least one sensor;
monitoring the engine power data to determine when engine power equates to the engine power parameter; and
sending the command to implement the valve position when the engine power data equates to the engine power parameter.
4. The system of claim 3 , wherein the control system performs the steps of:
monitoring the engine power data to determine when the engine power no longer equates to the engine power parameter; and
sending a second command to adjust the at least one electronically controlled valve to a second position.
5. The system of claim 4 , wherein the second position is a fully open position.
6. The system of claim 1 , wherein the engine power parameter is a measured rate of increase in engine power.
7. The system of claim 1 , wherein the engine power parameter is a percent shaft horsepower parameter.
8. The system of claim 1 , wherein the predetermined range includes a limit based on an engine core flow extraction certification limit.
9. The system of claim 1 , wherein the bleed air is high pressure bleed air generated from an aircraft engine.
10. The system of claim 1 , further comprising a flowrate sensor configured to monitor an amount of bleed air flowing through at least one electronically controlled valve.
11. The system of claim 1 , further comprising an Environmental Control System (ECS) configured to receive the amount of bleed air flowing through the at least one electronically controlled valve, the ECS regulating an air supply provided to an aircraft environment.
12. A pneumatic flow control method for an aircraft, comprising:
providing a control system with a software program thereon;
installing at least one electronically controlled valve to control an amount of bleed air flowing from an engine to an aircraft environment, the at least one electronically controlled valve in digital communication with the control system;
receiving user input to define a valve position for the at least one electronically controlled valve and an engine power parameter, the valve position being configured to restrict flow through the at least one valve to within a predetermined range that prevents the amount of the bleed air from over-extraction into the aircraft environment;
monitoring power of an engine via at least one engine sensor in digital communication with the control system;
detecting, based on a rate of change of the monitored engine power, whether the engine power is predicted to reach or exceed the user-defined engine power parameter;
determining, via the control system, when the engine power parameter is met based on the monitoring of power via the at least one engine sensor; and
sending a command to the at least one valve to adjust to the valve position when the engine power parameter is met.
13. The method of claim 12 , further comprising:
determining, via the control system, when the engine power does not equate to the engine power parameter based on the monitoring of power by the at least one engine sensor; and
sending a second command to adjust to a second valve position.
14. The method of claim 13 , wherein the second valve position is a fully open position.
15. The method of claim 12 , wherein the control system comprises a non-transitory memory for storing the software program thereon and a processor for executing the software program.
16. The method of claim 12 , wherein the engine power parameter is a measured rate of increase in engine power.
17. The method of claim 12 , wherein the engine power parameter is a percent shaft horsepower parameter.
18. The method of claim 12 , wherein the predetermined range includes a limit based on an engine core flow extraction certification limit.
19. The method of claim 12 , further comprising monitoring a flowrate of the amount of bleed air via a flowrate sensor.
20. The method of claim 12 , further comprising:
receiving the amount of bleed air into an Environmental Control System (ECS); and
regulating and providing an air supply to one or more aircraft environments from the ECS.