Method and apparatus for operating a gas turbine engine

• US 8,818,683 B2
• Filed: 04/21/2006
• Issued: 08/26/2014
• Est. Priority Date: 04/21/2006
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: van der Merwe, Gert Johannes, Bradford, David Allen
• Primary Examiner(s): Holwerda, Stephen
• Application Number:
  US11/379,669
• Publication Number:
  US 20070250245A1
• Time in Patent Office: 3,049 Days
• Field of Search: 701/100, 701/99, 701/1, 701/3, 607/73, 415/1, 736/60, 73/66, 734/322, 734/55, 734/57, 734/60, 734/62, 735/70, 735/77, 738/658, 738/659, 702/1, 702/33, 702/34, 702/35, 702/39, 702/56, 702/127, 702/182, 702/183, 702/187, 702/189
• 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:

detecting a change in a rotational speed of a rotor assembly based on a signal transmitted from at least one speed sensor, wherein the change in rotational speed persists for at least a specified period;

comparing the detected change in rotational speed to a threshold speed range;

generating a first output when the detected change in rotational speed exceeds the threshold speed range for a first predetermined duration, wherein the first output is at least one of an audio and a visual indication alerting a user;

identifying, based on the first output, the occurrence of an engine impulse event;

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

comparing the detected vibration level to a predetermined amplitude vibration threshold range and a predetermined vibration duration threshold range, wherein the predetermined vibration duration threshold range is determined using vibration data collected from at least one gas turbine engine during a plurality of flights; and

generating a second output when the detected vibration level exceeds the predetermined vibration amplitude threshold range for a period of time that exceeds the predetermined vibration duration threshold range to identify a gas turbine engine impulse event.

2. 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 a third output when the detected vector change exceeds a predetermined threshold range to identify a gas turbine engine impulse event.

3. A method in accordance with claim 1 further comprising transmitting the generated indication to a ground station.

11. A method in accordance with claim 1, wherein the gas turbine engine includes an engine monitoring unit physically coupled to the gas turbine engine;

said method further comprising;

generating, via the engine monitoring unit, an indication of the engine impulse event based on at least one of the first and second generated outputs.

4. A monitoring system for a gas 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;

at least one speed sensor configured to transmit a speed signal indicative of a rotational speed of the rotor 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 the rotor assembly based on the signal transmitted from the at least one sensor;

detect a change in the rotational speed of the rotor assembly based on the speed signal from the at least one speed sensor, wherein the change in rotational speed persists for at least a specified period;

generate a first output when the change in rotational speed exceeds a threshold speed range for a first predetermined duration, wherein the first output is at least one of an audio and a visual indication alerting a user;

identify the occurrence of an engine impulse event based on the first output;

generate a second output when the detected vibration level exceeds a predetermined vibration amplitude threshold range for a period of time that exceeds a predetermined vibration duration threshold range; and

generate an indication of a gas turbine engine impulse event based on the first and second generated outputs;

wherein the first and second predetermined durations are stored in the EMU.

5. A monitoring system in accordance with claim 4 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 a third output if the detected vector change exceeds a predetermined threshold range to identify a gas turbine engine impulse event.

6. A monitoring system in accordance with claim 4 wherein said EMU is further configured to transmit the indication of the engine impulse event to a ground station.

7. 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;

at least one speed sensor positioned within the gas turbine engine, said speed sensor configured to transmit a signal indicative of a rotational speed of 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 a change in rotational speed of the fan assembly, wherein the change in rotational speed persists for at least a specified period;

generate a first output when the detected change in rotational speed exceeds a threshold speed range for a first predetermined duration, wherein the first output is at least one of an audio and a visual indication alerting a user;

identify the occurrence of an engine impulse event based on the first output;

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;

generate a second output when the detected vibration level exceeds a predetermined vibration amplitude threshold range for a period of time that exceeds a predetermined vibration duration threshold range; and

generate an indicator of a gas turbine engine impulse event based on the first and second generated outputs;

wherein the first and second predetermined durations are stored in the EMU.

8. A gas turbine engine assembly in accordance with claim 7 wherein said at least one sensor comprises an accelerometer that is configured to detect fan imbalance, said accelerometer configured to transmit a signal indicative of the vibration level of said fan assembly to said EMU.

9. A gas turbine engine assembly in accordance with claim 7 wherein said EMU is further configured to determine a vector change in the vibration level of the fan assembly based on the signal transmitted from the at least one sensor, and generate a third output if the detected vector change exceeds a predetermined threshold range to identify a gas turbine engine impulse event.

10. A gas turbine engine assembly in accordance with claim 7 wherein said EMU is further configured to transmit the indicator of the engine impulse event to a ground station.