Emergency Shut-Down Detection System For A Gas Turbine

• US 20160363001A1
• Filed: 05/09/2016
• Published: 12/15/2016
• Est. Priority Date: 06/10/2015
• Status: Active Grant

• 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: Argote, Christopher, Harvell, John K.
• Granted Patent: US 10,190,440 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 21/04 responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• CPC Class Codes: F01D 21/06 Shutting-down
• CPC Class Codes: F01D 21/14 responsive to other specific conditions
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F02C 9/46 Emergency fuel control
• CPC Class Codes: F02C 9/48 Control of fuel supply conjointly with another control of the plant with nozzle section control F02K1/17
• 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 27/0292 Stop safety or alarm devices, e.g. stop-and-go control; Disposition of check-valves
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/09 to cope with emergencies
• CPC Class Codes: F05D 2270/101 Compressor surge or stall
• CPC Class Codes: F05D 2270/301 Pressure
• CPC Class Codes: F05D 2270/304 Spool rotational speed
• CPC Class Codes: F05D 2270/807 Accelerometers

Abstract

A gas turbine engine is provided with a controller configured to detect a spool shaft failure and to initiate an engine shut-down in response to the shaft failure. The controller evaluates the compressor speed probe, the speed probe continuity, P30 pressure and compressor surge to determine whether a shaft failure has occurred.

Claims

1. A gas turbine engine comprising:

a compressor;

a combustor;

a turbine coupled to said compressor by a spool;

at least one electrical speed sensor disposed in said compressor upstream of the spool and operable to provide a compressor speed signal, said at least one speed sensor including an electrical continuity circuit operable to generate a continuity signal for the electrical speed sensor;

a controller having a number of inputs for receiving at least one measured engine parameter and a number of outputs for transmitting control signals for controlling engine operation variables, said controller including an input for receiving the speed signal and the continuity signal, said controller configured to generate a speed probe fault in response to a loss of the speed signal and a continuity fault signal in response to a loss of the continuity signal, said controller further configured to generate a signal to shut down engine operation in response to detection of both the speed probe fault signal and the continuity fault signal.

2. The gas turbine engine of claim 1, wherein:

said at least one electrical speed sensor includes two speed sensors disposed in said compressor upstream of the spool, each of said two speed sensors operable to provide a compressor speed signal and including an electrical continuity circuit operable to generate a continuity signal; and

said controller includes an input for receiving the speed signal and the continuity signal of each of said two speed sensors and is configured to generate a speed probe fault signal in response to a loss of the speed signal and a continuity fault signal in response to a loss of the continuity signal for each of said two speed sensors, said controller further configured to generate a signal to shut down engine operation in response to detection of both the speed probe fault signal and the continuity fault signal for both of said two speed sensors.

3. The gas turbine engine of claim 1, further comprising:

a pressure sensor operable to generate a pressure signal in response to a fluid pressure within the compressor;

said controller receiving said pressure signal as an input and configured to generate the signal to shut down the engine operation only when the pressure signal exceeds a pressure threshold related to disc burst for the turbine.

4. The gas turbine engine of claim 3, wherein the pressure sensor senses the P30 pressure of the engine.

5. The gas turbine of claim 1, wherein said controller is configured to detect compressor surge from the at least one measured engine parameter, to generate a surge signal indicative of a compressor surge condition, and to generate the signal to shut down the engine operation only when the surge signal is received.

6. The gas turbine of claim 3 wherein said controller is configured to detect compressor surge from the at least one measured engine parameter, to generate a surge signal indicative of a compressor surge condition, and to generate the signal to shut down the engine operation only when the surge signal is received.

7. A method for shutting down a gas turbine engine comprising:

detecting a fault in a signal from a compressor speed probe upstream of the spool connecting a compressor to a turbine;

detecting a fault in a continuity signal for the compressor speed probe; and

commanding an engine shut down in response to the detection of a fault in both the speed probe signal and the continuity signal.

8. The method for shutting down a gas turbine engine of claim 7, further comprising:

detecting a fault in a signal from a second compressor speed probe upstream of the spool connecting a compressor to a turbine;

detecting a fault in a continuity signal for the second compressor speed probe; and

commanding an engine shut down in response to the detection of a fault in both the speed probe signal and the continuity signal for both speed probes.

9. The method for shutting down a gas turbine engine of claim 7, further comprising:

detecting the P30 pressure of the engine; and

commanding the engine shut down only when the P30 pressure signal exceeds a predetermined threshold value related to disc burst for the turbine.

10. The method for shutting down a gas turbine engine of claim 9, further comprising commanding the engine shut down only when a compressor surge condition is detected.

11. The method for shutting down a gas turbine engine of claim 7, further comprising commanding the engine shut down only when a compressor surge condition is detected.