FAN BLADE MONITORING AND CONTROL SYSTEM

• US 20160319845A1
• Filed: 04/28/2016
• Published: 11/03/2016
• Est. Priority Date: 05/01/2015
• Status: Abandoned Application

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Molnar, Daniel E.
• Application Number:
  US15/140,526
• Publication Number:
  US 20160319845A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 17/02 Arrangement of sensing elements
• CPC Class Codes: F01D 17/24 electrical
• CPC Class Codes: F01D 25/06 for preventing blade vibration means on blade-carrying members or blades F01D5/00
• CPC Class Codes: F01D 5/26 Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F04D 25/066 Linear Motors
• CPC Class Codes: F04D 27/001 Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/526 Details of the casing section radially opposing blade tips ducts F04D29/545
• CPC Class Codes: F04D 29/668 damping or preventing mechanical vibrations
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2240/307 related to the tip of a rotor blade
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2260/941 particularly aimed at mechanical or thermal stress reduction
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F05D 2270/114 by limiting mechanical stresses
• CPC Class Codes: F05D 2270/334 Vibration measurements
• CPC Class Codes: F05D 2270/708 with comparison tables
• CPC Class Codes: F05D 2270/821 Displacement measuring means, e.g. inductive
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine includes a fan positioned in a containment case. The fan includes a fan hub with a number of fan blades extending from the fan hub. A blade motion control system is coupled to the gas turbine engine to detect and control fan blade motion caused by harmonic modes. One or more magnetic materials are coupled to one or more of the fan blades of the gas turbine engine. One or more blade motion sensors are coupled to the containment case and are configured to detect the motion of the magnetic materials coupled to the fan blades. A control unit can adjust one or more operational parameters of the gas turbine engine to disrupt the fan blade motion caused by the detected harmonic modes.

Claims

1. A method for controlling motion caused by harmonic modes in a gas turbine engine fan blade, the method performed by a turbine engine control unit, the method comprising:

receiving a sensor signal that includes motion data indicative of fan blade motion of a fan of a gas turbine engine;

determining whether the fan blade motion is caused by a harmonic mode by comparing the motion data to reference data indicative of an expected fan blade motion during normal operation of the gas turbine engine; and

adjusting an operational parameter of the gas turbine engine in response to determining that the fan blade motion is caused by a harmonic mode.

2. The method of claim 1, wherein receiving a sensor signal comprises receiving timing data indicative of fan blade motion of the gas turbine engine fan.

3. The method of claim 2, wherein determining whether the fan blade motion is caused by harmonic modes comprises comparing the timing data to reference timing data.

4. The method of any of claim 1, comprising obtaining the reference data by detecting the fan blade motion of the gas turbine engine fan in a test environment.

5. The method of any of claim 1, wherein determining whether the fan blade motion is caused by harmonic modes comprises determining that the motion data is different than the reference data.

6. The method of any of claim 1, wherein adjusting an operational parameter of the gas turbine engine comprises applying a magnetic force to the fan blade.

7. The method of any of claim 1, wherein adjusting an operational parameter of the gas turbine engine comprises adjusting the rotation speed of the gas turbine engine fan blade.

8. The method of any of claim 1, wherein adjusting an operational parameter of the gas turbine engine comprises adjusting a pitch of the fan blade.

9. A system for controlling harmonic modes in a gas turbine engine, the system comprising:

a gas turbine engine comprising;

a turbo fan that includes a rotor and a plurality of fan blades, each fan blade extending radially outward from the rotor having a blade root coupled to the rotor and a blade tip opposite the blade root, wherein a permanent magnet is coupled to one or more fan blades near the blade tip;

a fan casing surrounding the turbo fan;

one or more sensors coupled to the fan casing configured to detect the motion of the permanent magnet coupled to the one or more fan blades and output motion data; and

a control unit in communication with the one or more sensors to receive motion data from the one or more sensors.

10. The system of claim 9, wherein each fan blade includes a leading edge and a trailing edge, and the permanent magnet is coupled to the fan blade near the leading edge of the fan blade and near the blade tip of the one or more fan blades.

11. The system of claim 10, wherein the fan casing includes a containment case and a fan track liner and wherein the sensor is coupled to the fan track liner of the fan casing.

12. The system of claim 9, wherein the sensor comprises an induction loop configured to detect a time-varying magnetic field caused by the motion of the permanent magnet coupled to the one or more fan blades.

13. The system of claim 9, wherein the sensor sends sensor signals to the control unit, and the sensor signals include motion data indicative of the motion of the fan blades.

14. The system of claim 9, wherein the control unit is configured to determine whether the motion of one or more fan blades is caused by a harmonic mode by comparing the motion data to reference data.

15. The system of claim 9, wherein the sensor is configured to produce a magnetic field that can affect the motion of the one or more fan blades by exerting a magnetic force on the permanent magnet coupled to the one or more fan blades.

16. The system of claim 9, comprising one or more electromagnets coupled to the fan casing.

17. A system for controlling harmonic modes in a gas turbine engine, the system comprising:

a gas turbine engine comprising;

a turbo fan that includes a rotor and a plurality of fan blades, each fan blade extending radially outwardly from the rotor, each fan blade having a blade root coupled to the rotor and a blade tip opposite the blade root, wherein a permanent magnet is coupled to one or more of the fan blades near the blade tip; and

a fan casing surrounding the turbo fan;

one or more sensors coupled to the fan casing and configured to detect a change in a magnetic field caused by the permanent magnet;

a controller coupled to the gas turbine engine and configured to determine, based on sensor signals produced by the one or more sensors, whether the motion of the one or more fan blades is caused by harmonic modes; and

one or more electromagnets coupled to the fan casing and configured to exert an electromechanical force on the permanent magnet.

18. The system of claim 17, further comprising a power source coupled to the one or more electromagnets and the control unit, wherein the power source is configured to provide power to the one or more electromagnets when the controller detects that the motion of one or more fan blades includes motion caused by harmonic modes.

19. The system of claim 17, wherein the number of sensors coupled to the fan casing is different than the number of electromagnets coupled to the fan casing.

20. The system of claim 19, wherein the number of sensors coupled to the fan casing is greater than the number of electromagnets coupled to the fan casing.