ELECTRIC MOTOR DRIVEN LUBRICATION PUMP AND LUBRICATION SYSTEM PROGNOSTIC AND HEALTH MANAGEMENT SYSTEM AND METHOD

• US 20090299535A1
• Filed: 08/08/2007
• Published: 12/03/2009
• Est. Priority Date: 08/08/2007
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Delaloye, Jim E.
• Application Number:
  US11/835,540
• Publication Number:
  US 20090299535A1
• Time in Patent Office: Days
• US Class Current: 700/282
• CPC Class Codes: F01D 25/20 using lubrication pumps
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M

Abstract

An aircraft lubrication supply system health and prognostic system and method includes supplying a pressure signal representative of lubricant pressure, a temperature signal representative of lubricant temperature, a speed signal representative of motor rotational speed, and one or more aircraft condition signals representative of one or more aircraft operating conditions to a system characterization model of at least portions of the lubrication supply system. Simulation response data representative of at least the pressure signal, the temperature signal, and the speed signal are generated, and lubrication supply system health is determined based, at least in part, on the simulation response data.

Claims

1. An aircraft lubrication supply system, comprising:

a motor operable, upon being energized from a power source, to rotate and supply a drive force;

a pump coupled to receive the drive force from the motor and operable, upon receipt thereof, to supply lubricant;

a controller coupled to receive a pressure signal representative of lubricant pressure, a temperature signal representative of lubricant temperature, a speed signal representative of motor rotational speed, and one or more aircraft condition signals representative of one or more aircraft operating conditions, the controller operable, in response to each of the received signals, to (i) at least selectively energize the motor from the power source and (ii) determine lubrication supply system health status.

2. The system of claim 1, wherein the controller is further adapted to receive a motor current signal representative of current being drawn by the motor and a motor voltage signal representative of motor supply voltage, and is further responsive to these signals to determine lubrication supply system health status.

3. The system of claim 1, wherein the controller is further operable, in response to each of the received signals, to at least selectively generate data representative of operator maintenance directions.

4. The system of claim 1, wherein the controller includes a system characterization model representative of at least portions of the lubrication supply system, the system control model responsive to one or more of the pressure signal, the temperature signal, the speed signal, and the one or more aircraft condition signals to generate simulation response data representative of at least the pressure signal, the temperature signal, and the speed signal.

5. The system of claim 4, wherein the controller determines lubrication supply system health based, at least in part, on the simulation response data.

6. The system of claim 1, further comprising:

a lubricant filter having a filter inlet and a filter outlet, the filter inlet coupled to receive at least a portion of the lubricant supplied by the pump, the lubricant filter configured to filter the lubricant received thereby and discharge filtered lubricant via the filter outlet; and

a filter outlet pressure sensor disposed downstream of the filter outlet, the filter outlet pressure sensor configured to sense filter outlet pressure and supply a filter outlet pressure signal representative thereof to the controller,

wherein the pressure signal received by the controller is the filter outlet pressure signal.

7. The system of claim 6, further comprising:

a filter inlet pressure sensor disposed upstream of the filter inlet, the filter inlet pressure sensor configured to sense filter inlet pressure and supply a filter inlet pressure signal representative thereof to the controller,

wherein the controller is further responsive the filter inlet pressure signal to determine lubrication supply system health status.

8. The system of claim 1, further comprising:

a rotational speed sensor configured to sense motor rotational speed and supply the speed signal to the controller.

9. The system of claim 1, further comprising:

a temperature sensor configured to sense lubricant temperature and supply the temperature signal to the controller.

10. The system of claim 1, wherein the one or more aircraft condition signals representative of aircraft operating conditions include:

an altitude signal representative of aircraft altitude; and

an attitude signal representative of aircraft attitude.

11. The system of claim 1, further comprising:

an altitude sensor configured to sense aircraft altitude and supply the altitude signal representative thereof to the controller; and

an attitude sensor configured to sense aircraft attitude and supply the attitude signal representative thereof to the controller.

12. The system of claim 1, further comprising:

a bearing sump exit temperature sensor configured to sense bearing sump lubricant exit temperature and supply the temperature signal to the controller.

13. An aircraft lubrication supply system, comprising:

a motor coupled to receive motor speed commands representative of a commanded motor speed and operable, in response thereto, to rotate at the commanded motor speed and supply a drive force;

a pump having at least a fluid inlet and a fluid outlet, the fluid inlet adapted to couple to a lubricant source, the pump coupled to receive the drive force from the motor and configured, in response thereto, to draw lubricant from the lubricant source into the fluid inlet and supply lubricant, via the fluid outlet, to a rotating machine;

a pressure sensor operable to supply a pressure signal representative of lubricant pressure;

a temperature sensor operable to supply a temperature signal representative of lubricant temperature;

a rotational speed sensor operable to supply a speed signal representative of motor rotational speed;

one or more aircraft condition sensors operable to supply one or more aircraft condition signals representative of aircraft operating conditions; and

a controller coupled to receive the pressure signal, the temperature signal, the speed signal, and the one or more aircraft condition signals, the controller operable, in response to each of the received signals, to (i) at least selectively energize the motor from the power source and (ii) determine lubrication supply system health status.

14. The system of claim 13, wherein the controller is further adapted to receive a motor current signal representative of current being drawn by the motor and a motor voltage signal representative of motor supply voltage, and is further responsive to these signals to determine lubrication supply system health status.

15. The system of claim 13, wherein the controller is further operable, in response to each of the received signals, to at least selectively generate data representative of operator maintenance directions.

16. The system of claim 13, wherein the controller includes a system characterization model representative of at least portions of the lubrication supply system, the system control model responsive to one or more of the pressure signal, the temperature signal, the speed signal, and the one or more aircraft condition signals to generate simulation response data representative of at least the pressure signal, the temperature signal, and the speed signal.

17. The system of claim 16, wherein the controller determines lubrication supply system health based, at least in part, on the simulation response data.

18. A method of determining aircraft lubrication supply system health, the method comprising the steps of:

supply a pressure signal representative of lubricant pressure, a temperature signal representative of lubricant temperature, a speed signal representative of drive motor rotational speed, and one or more aircraft condition signals representative of one or more aircraft operating conditions to an embedded system characterization model of at least portions of the lubrication supply system;

generating simulation response data representative of at least the pressure signal, the temperature signal, and the speed signal; and

determining lubrication supply system health based, at least in part, on the simulation response data.

19. The method of claim 18, further comprising:

selectively generating data representative of operator maintenance directions