Systems and methods for variable alignment aerodynamic probes

1. A variable alignment aerodynamic probe comprising:

a probe body having a leading edge and extending radially into a vane case;

a sensor element proximate the leading edge; and

a bearing coupled to the probe body and the vane case;

wherein the probe body is configured to rotate in response to a turned flow within the vane case,

wherein the rotation of the probe body is configured to maintain an angle of attack of the leading edge with respect to the turned flow between 0° and 15°.

2. The variable alignment aerodynamic probe of claim 1 , wherein the sensor element is at least one of a Pitot tube or Kiel probe.

3. The variable alignment aerodynamic probe of claim 2 , wherein the probe body further comprises a first shaft coupled to the probe body and rigidly coupled to a first control arm.

4. The variable alignment aerodynamic probe of claim 3 , wherein the first control arm is coupled to a first end of a control linkage, wherein the control linkage is coupled at a second end to a second control arm.

5. The variable alignment aerodynamic probe of claim 4 , wherein the second control arm is rigidly coupled to one of a second shaft or a synchronization ring, wherein the second control arm is configured to deflect in response to rotation of a variable vane.

6. The variable alignment aerodynamic probe of claim 2 , further comprising:

a controller;

a first sensor in electronic communication with the controller;

a second sensor in electronic communication with the controller;

a first servomotor in electronic communication with the controller;

a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising:

receiving, by the controller, a first data from the first sensor and a second data from the second sensor;

determining, by the controller, a first angle of attack difference based on the first data and the second data;

calculating, by the controller, a first angle of attack response based on the angle of attack difference, wherein the angle of attack response is configured to null the angle of attack difference; and

controlling, by the controller, the first servomotor and, in response, rotating the probe body about a first axis.

7. The variable alignment aerodynamic probe of claim 6 , further comprising a second servomotor in electronic communication with the controller, wherein the operations further comprise:

determining, by the controller, a second angle of attack difference based on the first data and the second data;

calculating, by the controller, a second angle of attack response based on the second angle of attack difference, wherein the second angle of attack response is configured to null the second angle of attack difference; and

controlling, by the controller, the second servomotor and, in response, rotating the probe body about a second axis.

8. The variable alignment aerodynamic probe of claim 6 , wherein the first sensor is at least one of a Pitot tube, a Kiel probe, a rotary encoder, a yaw sensor, a pitch sensor, or a Rotary Variable Differential Transformer (RVDT).

9. The variable alignment aerodynamic probe of claim 7 , wherein the probe body comprises one of a yaw sensor, a pitch sensor, or an RVDT.

10. A gas turbine engine comprising:

a fan section having a fan case;

a compressor section having a compressor case;

a turbine section having a turbine case; and

a variable alignment aerodynamic probe comprising:

a probe body having a leading edge and extending radially into a vane case;

a sensor element proximate the leading edge; and

a bearing coupled to the probe body and the vane case;

wherein the probe body is configured to rotate in response to a turned flow within the vane case,

wherein the rotation of the probe body is configured to maintain an angle of attack of the leading edge with respect to the turned flow between 0° and 15°.

11. The gas turbine engine of claim 10 , wherein the sensor element is at least one of a Pitot tube or Kiel probe.

12. The gas turbine engine of claim 11 , wherein the probe body further comprises a first shaft coupled to the probe body and rigidly coupled to a first control arm.

13. The gas turbine engine of claim 12 , wherein the first control arm is coupled to a first end of a control linkage, wherein the control linkage is coupled at a second end to a second control arm.

14. The gas turbine engine of claim 13 , wherein the second control arm is rigidly coupled to one of a second shaft or a synchronization ring, wherein the second control arm is configured to deflect in response to rotation of a variable vane.

15. The gas turbine engine of claim 11 , further comprising:

a controller;

a first sensor in electronic communication with the controller;

a second sensor in electronic communication with the controller;

a first servomotor in electronic communication with the controller;

a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising:

receiving, by the controller, a first data from the first sensor and a second data from the second sensor;

determining, by the controller, a first angle of attack difference based on the first data and the second data;

calculating, by the controller, a first angle of attack response based on the angle of attack difference, wherein the angle of attack response is configured to null the angle of attack difference; and

controlling, by the controller, the first servomotor and, in response, rotating the probe body about a first axis.

16. The gas turbine engine of claim 15 , further comprising a second servomotor in electronic communication with the controller, wherein the operations further comprise:

determining, by the controller, a second angle of attack difference based on the first data and the second data;

calculating, by the controller, a second angle of attack response based on the second angle of attack difference, wherein the second angle of attack response is configured to null the second angle of attack difference; and

controlling, by the controller, the second servomotor and, in response, rotating the probe body about a second axis.

17. The gas turbine engine of claim 15 , wherein the first sensor is at least one of a Pitot tube, a Kiel probe, a rotary encoder, a yaw sensor, a pitch sensor, or a Rotary Variable Differential Transformer (RVDT).

18. The gas turbine engine of claim 16 , wherein the probe body comprises one of a yaw sensor, a pitch sensor, or an RVDT.

19. An article of manufacture including a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising:

receiving, by the processor, a first data from a first sensor and a second data from a second sensor;

determining, by the processor, a first angle of attack difference based on the first data and the second data;

calculating, by the processor, a first angle of attack response based on the angle of attack difference, wherein the angle of attack response is configured to null the angle of attack difference; and

controlling, by the processor, a first servomotor and, in response, rotating a probe body about a first axis.

20. The article of manufacture of claim 19 , further comprising the operations of:

determining, by the processor, a second angle of attack difference based on the first data and the second data;

calculating, by the processor, a second angle of attack response based on the second angle of attack difference, wherein the second angle of attack response is configured to null the second angle of attack difference; and

controlling, by the processor, a second servomotor and, in response, rotating the probe body about a second axis.