System and method for controlling ice formation on gas turbine inlet guide vanes

Patent metadata

Field	Value
Publication number	US-9874109-B2
Application number	US-201313904066-A
Country	US
Kind code	B2
Filing date	May 29, 2013
Priority date	May 29, 2013
Publication date	Jan 23, 2018
Grant date	Jan 23, 2018

Abstract

Gas turbine inlet guide vane ice detection and control systems and methods that utilize active infra-red monitoring of inlet guide vanes, detection of ice formation on the guide vanes and elimination of the ice by altering properties of the gas turbine inlet intake airflow, such as by introducing compressed and/or heated air bled from the turbine. Ice has lower detectable emissivity intensity in the infra-red spectrum than ice-free inlet guide vane surfaces. Ice formation is inhibited by direct monitoring of inlet guide vane icing conditions, rather than by indirect empirical assumptions of ice formation based on atmospheric condition monitoring. Direct monitoring mitigates ice formation in real time without reliance on excessive use of gas turbine compressed or heated air bleed, which enhances turbine operational efficiency.

First claim

What is claimed is:

1. A method for detecting and alleviating ice formation on inlet guide vanes of a gas turbine, comprising:
viewing a gas turbine inlet guide vane with an infra-red camera, wherein the infra-red camera is placed external the gas turbine and the inlet guide vane is viewed through a viewing window within a housing of the gas turbine;
actively monitoring emissivity intensity of the inlet guide vane with the infra-red camera in a wavelength range indicative of ice formation;
detecting when monitored emissivity is indicative of ice formation on the inlet guide vane wherein ice formation is indicated when a viewed inlet guide vane emissivity intensity drops below a threshold amount indicating ice formation;
alleviating the detected ice formation by altering intake airflow properties into the gas turbine; and wherein the alleviating step comprising bleeding compressor pressurized air and combustor heated air into the gas turbine intake airflow in a feedback loop with the detecting step.

2. The method of claim 1 , the infra-red camera comprising a micro bolometer detector in which detector electrical conductivity changes in response to temperature changes.

3. The method of claim 1 , the monitored emissivity ice formation indication comprising viewed inlet guide vane aggregate emissivity intensity dropping below a defined threshold.

4. The method of claim 1 , the monitored emissivity ice formation indication comprising a defined percentage of viewed inlet guide vane having emissivity intensity dropping below a defined threshold.

5. The method of claim 4 the defined percentage determined by comparing percentage of camera detector pixels indicating intensity above and below the defined threshold.

6. The method of claim 1 , the monitored emissivity ice formation indication comprising mapping of viewed inlet guide vane emissivity intensity and identification of mapping patterns.

7. The method of claim 1 further comprising performing the viewing, actively monitoring and detecting steps on a plurality of inlet guide vanes simultaneously.

8. The method of claim 1 , the infra-red camera actively monitoring emissivity intensity of the inlet guide vane in a wavelength range of 3-13 μm.

9. A method for detecting and alleviating ice formation on inlet guide vanes of a gas turbine, comprising:
viewing a gas turbine inlet guide vane with an infra-red camera having a micro bolometer detector in which detector electrical conductivity changes in response to temperature changes, wherein the infra-red camera is placed external the gas turbine and the inlet guide vane is viewed through a viewing window within a housing of the gas turbine;
actively monitoring emissivity intensity of the inlet guide vane with the infra-red camera in a wavelength range of 3-13 μm;
detecting when monitored emissivity is indicative of ice formation on the inlet guide vane wherein ice formation is indicated when a viewed inlet guide vane emissivity intensity drops below a threshold amount indicating ice formation; and
alleviating the detected ice formation by altering intake airflow properties into the gas turbine comprising bleeding compressor pressurized air and combustor heated air into the gas turbine intake airflow in a feedback loop with the detecting step.

10. The method of claim 9 , the monitored emissivity ice formation indication selected from the group consisting of: viewed inlet guide vane aggregate emissivity intensity dropping below a defined threshold; defined percentage of viewed inlet guide vane having emissivity intensity dropping below a defined threshold; and mapping of viewed inlet guide vane emissivity intensity and identification of mapping patterns.

11. The method of claim 9 , further comprising performing the viewing, actively monitoring and detecting steps on a plurality of inlet guide vanes simultaneously.

12. A system for detecting and alleviating ice formation on inlet guide vanes of a gas turbine, comprising:
an infra-red camera viewing a gas turbine inlet guide vane and capturing emissivity intensity images of the inlet guide vane, wherein the infra-red camera is placed external the gas turbine and the inlet guide vane is viewed through a viewing window within a housing of the gas turbine;
a controller coupled to the infra-red camera that actively monitors the infra-red camera emissivity intensity images in a wavelength range indicative of ice formation, detects when monitored emissivity is indicative of ice formation on the inlet guide vane and sends output commands to the gas turbine to alter intake airflow properties into the gas turbine in response to detected ice formation, so as to alleviate ice formation on the inlet guide vane wherein ice formation is indicated when a viewed inlet guide vane emissivity intensity drops below a threshold amount indicating ice formation; and wherein the controller alters intake air flow properties by bleeding compressor pressurized air and combustor heated air into the gas turbine intake airflow in a feedback loop.

13. The system of claim 12 , the infra-red camera comprising a micro bolometer detector in which detector electrical conductivity changes in response to temperature changes.

14. The system of claim 12 , the infra-red camera actively monitoring emissivity intensity of the inlet guide vane in a wavelength range of 3-13 μm.

15. The system of claim 12 actively monitoring a plurality of inlet guide vanes simultaneously by at least one infra-red camera.

16. The system of claim 12 , the controller monitored emissivity ice formation indication selected from the group consisting of: viewed inlet guide vane aggregate emissivity intensity dropping below a defined threshold; defined percentage of viewed inlet guide vane having emissivity intensity dropping below a defined threshold; and mapping of viewed inlet guide vane emissivity intensity and identification of mapping patterns.

Assignees

• Hatcher Jr Clifford
• Ruhge Forrest R
• Siemens Energy Inc

Inventors

• Hatcher Jr Clifford
• Ruhge Forrest R

Classifications

• F01D25/02 Primary

  De-icing means for engines having icing phenomena · CPC title

• F05D2270/44

  active, predictive, or anticipative · CPC title

• G01M15/14

  Testing gas-turbine engines or jet-propulsion engines · CPC title

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• F05D2270/804

  Optical devices · CPC title