METHOD AND APPARATUS FOR OPERATING A GAS TURBINE ENGINE

• US 20070250245A1
• Filed: 04/21/2006
• Published: 10/25/2007
• Est. Priority Date: 04/21/2006
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: van der Merwe, Gert, Bradford, David
• Granted Patent: US 8,818,683 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• 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: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: G01H 1/006 of the rotor of turbo machines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A method for operating a gas turbine engine includes coupling at least one sensor within the gas turbine engine to transmit a signal indicative of a vibration level of a rotor assembly within the gas turbine engine, detecting the vibration level of the rotor assembly based on the signal transmitted from the at least one sensor, comparing the detected vibration level to a predetermined vibration threshold, and generating an output if the detected vibration amplitude exceeds the threshold amplitude for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

Claims

1. A method for operating a gas turbine engine, said method comprising:

coupling at least one sensor within the gas turbine engine to transmit a signal indicative of a vibration level of a rotor assembly within the gas turbine engine;

detecting the vibration level of the rotor assembly based on the signal transmitted from the at least one sensor;

comparing the detected vibration level to a predetermined vibration threshold; and

generating an output if the detected vibration amplitude exceeds the threshold amplitude for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

2. A method in accordance with claim 1 wherein the gas turbine engine comprises a fan assembly and the accelerometer is configured to detect fan imbalance, said method further comprising coupling at least one accelerometer within the gas turbine engine to transmit a signal indicative of a vibration level of a fan rotor assembly within the gas turbine engine.

3. A method in accordance with claim 1 further comprising:

coupling at least one speed sensor within the gas turbine engine to transmit a signal indicative of a rotational speed of a fan rotor assembly within the gas turbine engine;

detecting the rotational speed of the fan rotor assembly based on the signal transmitted from the speed sensor; and

comparing the detected rotational speed to the detected vibration level

generating an output if the detected rotational speed exceeds a threshold speed for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

4. A method in accordance with claim 2 further comprising:

coupling at least one speed sensor within the gas turbine engine to transmit a signal indicative of a rotational speed of a fan rotor assembly within the gas turbine engine;

detecting the rotational speed of the fan rotor assembly based on the signal transmitted from the speed sensor; and

comparing the detected rotational speed to a predetermined speed threshold to facilitate identifying a gas turbine engine impulse event.

5. A method in accordance with claim 1 further comprising:

determining a vector change in the vibration level of the rotor assembly based on the signal transmitted from the at least one sensor; and

generating an output if the detected vector change exceeds a predetermined threshold to facilitate identifying a gas turbine engine impulse event.

6. A method in accordance with claim 1 further comprising transmitting the generated output to a ground station to facilitate scheduling a maintenance event.

7. A method in accordance with claim 1 wherein the gas turbine engine includes a engine monitoring unit coupled to the gas turbine engine;

said method further comprising;

coupling a plurality of sensors within the gas turbine engine, each sensor configured to transmit a respective signal indicative of a vibration level and rotational speed of a rotor assembly to the engine monitoring unit;

detecting the vibration level and rotational speed of the rotor assembly based on the signals transmitted from the plurality of sensors;

utilizing an algorithm stored within the engine monitoring unit to compare the detected vibration level to a predetermined vibration threshold;

utilizing the algorithm stored within the engine monitoring unit to compare the detected vibration level to the detected rotational speed; and

programming the engine monitoring unit to generate an output if the detected vibration amplitude exceeds the threshold amplitude for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

8. A monitoring system for a turbine engine including a combustor, said system comprising:

at least one sensor configured to transmit a signal indicative of a vibration level of a rotor assembly within the gas turbine engine; and

an engine monitoring unit (EMU) coupled to said at least one sensor for receiving the signal transmitted therefrom, said EMU configured to detect the vibration level of the rotor assembly based on the signal transmitted from the at least one sensor and generate an output if the detected vibration level exceeds a threshold level for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

9. A monitoring system in accordance with claim 8 wherein said at least one sensor comprises an accelerometer that is configured detect fan imbalance, said accelerometer configured to transmit a signal indicative of a vibration level of a fan rotor assembly within the gas turbine engine to said EMU.

10. A monitoring system in accordance with claim 8 further comprising:

at least one speed sensor coupled within the gas turbine engine, said speed sensor configured to transmit a signal indicative of a rotational speed of a fan rotor assembly to said EMU, said EMU further configured to generate an output if the detected rotational speed exceeds a threshold speed for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

11. A monitoring system in accordance with claim 9 further comprising:

at least one speed sensor coupled within the gas turbine engine, said speed sensor configured to transmit a signal indicative of a rotational speed of a fan rotor assembly to said EMU, said EMU further configured to compare the detected vibration level to the detected rotational speed to facilitate identifying a gas turbine engine impulse event.

12. A monitoring system in accordance with claim 8 wherein said EMU is further configured to determine a vector change in the vibration level of the rotor assembly based on the signal transmitted from the at least one sensor, and generate an output if the detected vector change exceeds a predetermined threshold to facilitate identifying a gas turbine engine impulse event.

13. A monitoring system in accordance with claim 8 wherein said EMU is further configured to transmit a signal indicative of an engine impulse event to a ground station to facilitate scheduling a maintenance event.

14. A monitoring system in accordance with claim 8 wherein said EMU is further configured to:

detect the vibration level and rotational speed of the rotor assembly based on the signals transmitted from the plurality of sensors;

utilize an algorithm stored within the engine monitoring unit to compare the detected vibration level to a predetermined vibration threshold;

utilize the algorithm stored within the engine monitoring unit to compare the detected vibration level to the detected rotational speed; and

generate an output if the detected vibration amplitude exceeds the threshold amplitude for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

15. A gas turbine engine assembly comprising:

a core gas turbine engine comprising a compressor, a combustor, and a turbine coupled to said compressor;

a fan assembly coupled to said core gas turbine engine;

at least one sensor configured to transmit a signal indicative of a vibration level of at least one of said compressor and said fan assembly; and

an engine monitoring unit (EMU) coupled to said at least one sensor for receiving the signal transmitted therefrom, said EMU configured to detect the vibration level of at least one of the compressor and the fan assembly based on the signal transmitted from the at least one sensor and generate an output if the detected vibration level exceeds a threshold level for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

16. A gas turbine engine assembly in accordance with claim 15 wherein said at least one sensor comprises an accelerometer that is configured detect fan imbalance, said accelerometer configured to transmit a signal indicative of a vibration level of said fan assembly to said EMU.

17. A gas turbine engine assembly in accordance with claim 15 further comprising:

at least one speed sensor coupled within the gas turbine engine, said speed sensor configured to transmit a signal indicative of a rotational speed of said fan assembly to said EMU, said EMU further configured to generate an output if the detected rotational speed exceeds a threshold speed for a predetermined duration to facilitate identifying a gas turbine engine impulse event.

18. A gas turbine engine assembly in accordance with claim 15 further comprising at least one speed sensor coupled within the gas turbine engine, said speed sensor configured to transmit a signal indicative of a rotational speed of said fan assembly to said EMU, said EMU further configured to compare the detected vibration level to the detected rotational speed to facilitate identifying a gas turbine engine impulse event.

19. A gas turbine engine assembly in accordance with claim 15 wherein said EMU is further configured to determine a vector change in the vibration level of the rotor assembly based on the signal transmitted from the at least one sensor, and generate an output if the detected vector change exceeds a predetermined threshold to facilitate identifying a gas turbine engine impulse event.

20. A gas turbine engine assembly in accordance with claim 15 wherein said EMU is further configured to transmit a signal indicative of an engine impulse event to a ground station to facilitate scheduling a maintenance event.