Emergency shut-down detection system for a gas turbine

Patent metadata

Field	Value
Publication number	US-10190440-B2
Application number	US-201615149263-A
Country	US
Kind code	B2
Filing date	May 9, 2016
Priority date	Jun 10, 2015
Publication date	Jan 29, 2019
Grant date	Jan 29, 2019

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.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a fan;
an IP compressor arranged aft of the fan:
an HP compressor arranged aft of the IP compressor;
a combustor arranged aft of the HP compressor;
an HP turbine arranged aft of the combustor and coupled to said HP compressor by an HP spool;
a bearing assembly comprising a bearing mounted on the HP Spool, the bearing assembly supporting an inner housing, an outer housing and a spring bar assembly arranged between the inner housing and the outer housing, the spring bar assembly having a plurality of circumferentially disposed spring bars configured to flex, the outer housing having a protrusion;
at least one electrical speed sensor arranged fore of said HP compressor and near the protrusion, the at least one electrical speed sensor 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;
wherein when the HP spool fractures, the HP compressor generates a forward axial force to fracture the spring bars causing the protrusion to sever the at least one speed probe resulting in a simultaneous termination of the compressor speed signal and continuity signal.

2. The gas turbine engine of claim 1 wherein said controller is 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.

3. The gas turbine engine of claim 2 , further comprising:
a pressure sensor operable to generate a pressure signal in response to a fluid pressure within the HP 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 HP turbine.

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

5. 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.

6. The gas turbine engine of claim 1 , wherein said at least one electrical speed sensor includes two speed sensors disposed in said HP compressor upstream of the HP 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.

7. The gas turbine of claim 2 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.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Argote Christopher
• Harvell John K

Classifications

• F01D21/14 Primary

  responsive to other specific conditions · CPC title

• F05D2270/807

  Accelerometers · CPC title

• F01D21/003

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2270/09

  to cope with emergencies · CPC title