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 aero damping measurement system, comprising:
a shroud;
a hub disposed within the shroud;
a plurality of blades coupled to the hub and configured to rotate about the hub;
a pressure sensor; and
a gas pressure probe further comprising:
a valve having an electronically controlled switching mechanism,
a tip extending
through the shroud to deliver a pressurized burst of gas into the plurality of blades,
a probe body, and
a base of the probe body;
wherein the base of the probe body is configured to receive the pressure sensor, and wherein the electronically controlled switching mechanism is coupled proximate the base.
2. The aero damping measurement system of claim 1 , wherein the gas pressure probe comprises a valve configured to control a pressure within the gas pressure probe.
3. The aero damping measurement system of claim 2 , further comprising a transducer coupled to the gas pressure probe to measure the pressure within the gas pressure probe.
4. The aero damping measurement system of claim 2 , wherein the valve is operable at a frequency between 0.5 Hz and 260 Hz.
5. The aero damping measurement system of claim 1 , wherein the gas pressure probe comprises an outlet oriented towards the plurality of blades.
6. The aero damping measurement system of claim 1 , wherein the shroud defines a cylindrical opening extending through the shroud in a radial direction with the gas pressure probe extending through the cylindrical opening.
7. The aero damping measurement system of claim 6 , wherein the tip of the gas pressure probe protrudes from the cylindrical opening proximate the plurality of blades.
8. The aero damping measurement system of claim 1 , further comprising a sensor probe that detects a deflection of the plurality of blades.