Method and system for piping failure detection in a gas turbine bleeding air system

Patent metadata

Field	Value
Publication number	US-10196928-B2
Application number	US-201615059116-A
Country	US
Kind code	B2
Filing date	Mar 2, 2016
Priority date	Mar 2, 2016
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

A pipe fault detection system is provided for a gas turbine engine having a compressor and a turbine. The pipe fault detection system includes a cooling manifold configured to direct cooling air from the compressor to the turbine. The cooling manifold includes at least two cooling pipes, a sensor configured to detect an operating condition indicative of a pipe break, and a controller configured to control the amount of cooling air through the cooling manifold in response to the operating condition detected by the sensor.

First claim

What is claimed is:

1. A pipe fault detection system for a gas turbine engine having a compressor and a turbine, said pipe fault detection system comprising:
a cooling manifold configured to direct cooling air from the compressor to the turbine, said cooling manifold comprising at least two cooling pipes;
a sensor configured to detect an operating condition indicative of a pipe break;
a controller configured to control the amount of cooling air through said cooling manifold in response to the operating condition detected by said sensor; and
wherein the operating condition is a detected difference between a first operational parameter at a first location and a second operational parameter at a second location different from the first location and wherein said sensor is a first pressure sensor, and wherein said first and second operational parameters are measured pressures at said first location and said second location, respectively and wherein said first pressure sensor is a single pressure switch coupled to both of said first and second locations by respective pressure tubes disposed outside of the compressor and the turbine.

2. The pipe fault detection system as claimed in claim 1 , wherein said first pressure sensor is configured to communicate the detected pressure difference between said first and second locations to said controller.

3. The pipe fault detection system as claimed in claim 2 , wherein said first location is an opening in said cooling manifold proximate the compressor, and wherein said second location is one of an opening in said cooling manifold proximate the turbine and an opening in said cooling manifold upstream of the turbine.

4. The pipe fault detection system as claimed in claim 2 , wherein said first location is an opening in a first one of said at least two cooling pipes upstream of the turbine, and wherein said second location is an opening in a second one of said at least two cooling pipes upstream of the turbine.

5. The pipe fault detection system as claimed in claim 1 , further comprising a second pressure sensor comprising a second pressure switch coupled between a third location and a fourth location by respective pressure tubes disposed outside of the compressor and the turbine, wherein said third and fourth locations are different from said first location.

6. The pipe fault detection system as claimed in claim 5 , wherein said controller is further configured to control the amount of cooling air through said cooling manifold based on a comparison of said first pressure sensor and said second pressure sensor.

7. A pipe fault detection system for a gas turbine engine having a compressor and a turbine, said pipe fault detection system comprising:
a cooling manifold configured to direct cooling air from the compressor to the turbine, said cooling manifold comprising at least two cooling pipes;
a sensor configured to detect an operating condition indicative of a pipe break;
a controller configured to control the amount of cooling air through said cooling manifold in response to the operating condition detected by said sensor; and
wherein the operating condition is a detected difference between a first operational parameter at a first location and a second operational parameter at a second location different from the first location and wherein said sensor is a first pressure sensor, and wherein said first and second operational parameters are measured pressures at said first location and said second location, respectively wherein said pressure sensor comprises a first pressure switch disposed proximate said first location and a second pressure switch disposed proximate said second location, and wherein said first and second pressure switches are configured to transmit measured pressure data electronically to said controller by one of direct wiring and wireless transmission.

Assignees

• Gen Electric

Inventors

• Adibhatla Sridhar
• Nolte Steven Edward
• Litzler Jeffrey Wayne

Classifications

• F01D21/003 Primary

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

• F05D2260/80

  Diagnostics · CPC title

• F01D21/14

  responsive to other specific conditions · CPC title

• F05D2270/09

  to cope with emergencies · CPC title

• F02C6/08 Primary

  the gas being bled from the gas-turbine compressor · CPC title