Aeromechanical identification systems and methods
An aero damping measurement system is provided. The system includes a shroud defining a tunnel, a hub disposed within the tunnel, and a plurality of blades coupled to the hub. The blades may rotate about the hub. A gas pressure probe may have a tip extending to the tunnel to deliver a pressurized burst into the tunnel. An aeromechanical identification system may include a pressurized gas source, a valve in fluid communication with the pressurized gas source, and the gas pressure probe may be in fluid communication with the valve. The valve may control a flow of a pressurized gas from the pressurized gas source into the gas pressure probe. A pressure sensor may be coupled to the gas pressure probe and configured to measure a pressure within the gas pressure probe.
1. An aeromechanical identification system, comprising:
a pressurized gas source;
a valve in fluid communication with the pressurized gas source;
a first pressure regulator fluidly coupled between the valve and the pressurized gas source configured to receive a pressure command;
a manifold fluidly coupled between the first pressure regulator and the valve;
a gas pressure probe in fluid communication with the valve, wherein the valve is configured to control a flow of a pressurized gas from the pressurized gas source into the gas pressure probe,
wherein the gas pressure probe comprises a probe body having a base configured to receive a pressure sensor, and wherein an electronically controlled switching mechanism of the valve is coupled proximate the base;
the pressure sensor coupled to the gas pressure probe at the base and configured to measure a pressure within the gas pressure probe;
a controller in electronic communication with the valve to command the valve to operate at a frequency, wherein the controller is in electronic communication with the pressure sensor, wherein the controller is in electronic communication with the first pressure regulator and configured to control a gas pressure of the pressurized gas source via the pressure command.
2. The aeromechanical identification system of claim 1 , further comprising a second pressure regulator controlled by the controller and fluidly coupled between the valve and the pressurized gas source, wherein the second pressure regulator is configured to be redundant to the first pressure regulator.
3. The aeromechanical identification system of claim 1 , wherein the aeromechanical identification system is integrated into an aero damping measurement system.
4. The aeromechanical identification system of claim 3 , wherein the aero damping measurement system further comprises:
a shroud defining a passage;
a hub disposed within the passage;
a plurality of blades coupled to the hub and configured to rotate about the hub, wherein the gas pressure probe extends to the passage to deliver a pressurized burst of air into the passage.
5. The aeromechanical identification system of claim 1 , wherein the frequency is between 0.5 Hz and 260 Hz.