Optic pyrometer for gas turbines

• US 6,109,783 A
• Filed: 08/21/1998
• Issued: 08/29/2000
• Est. Priority Date: 08/21/1997
• Status: Expired due to Term

• Current Assignee: Ansaldo Energia IP UK Limited (Ansaldo Energia SPA)
• Original Assignee: ABB Research Ltd. (ABB Ltd.)
• Inventors: Dobler, Thomas, Haffner, Ken, Evers, Wolfgang
• Primary Examiner(s): Bennett, G. Bradley
• Assistant Examiner(s): VERBITSKY, GAIL KAPLAN
• Application Number:
  US09/137,681
• Time in Patent Office: 739 Days
• Field of Search: 374/131, 374/141, 374/144
• US Class Current: 374/131
• CPC Class Codes: G01J 5/0022 for sensing the radiation of moving bodies

Abstract

The present invention discloses a high temperature pyrometer 20 which is suitable, in particular, for temperature measurement in a gas turbine. The pyrometer comprises a flexible lightguiding measuring probe 21 with a microlens 22 resistant to high temperatures and with an optic fiber 24 composed of quartz or sapphire, said microlens and said fiber being provided with a gold sheathing 25, 26 and/or a protective capillary 27, 28. The heat radiation is evaluated in a remote detector 32 having measuring electronics 33 connected to it. The pyrometer 20 is distinguished by compactness, high temperature capability, flexibility, versatile installability and high measuring accuracy. The invention also relates to a development of the pyrometer 20 for gas turbines, to a gas turbine with a pyrometer 20 according to the invention, and to a method for monitoring a gas turbine with the aid of a pyrometer 20. Explanations are given of ways in which the measuring probe 21 can be fitted in guide blades 34, 48 and by means of which accurate temperature measurements are possible on moving and guide blades 34, 35, 48, 49 in low pressure and high pressure turbines. The operating safety and the efficiency of gas turbines can thereby be increased.

Claims

1. A high temperature pyrometer suitable for temperature measurement in a gas turbine, the pyrometer comprising a lightguiding measuring probe for detecting heat radiation and transmitting the latter to a detector, wherein

the measuring probe comprises an optic fiber with a microoptic sensor head;

the fiber and the sensor head are resistant to high temperatures; and

the fiber and the sensor head have a pliable sheathing resistant to high temperatures.

2. The high temperature pyrometer as claimed in claim 1, wherein

the sensor head comprises a cone or a microlens;

and

the sensor head and the fiber are designed in one piece or are optically connected to one another in a manner resistant to high temperatures.

3. The high temperature pyrometer as claimed in claim 1, wherein

the fiber and the sensor head each comprises an external element selected from the group consisting of a high temperature coating and a protective capillary.

4. The high temperature pyrometer as claimed in claim 3, wherein

the fiber and the sensor head comprise a material selected from the group consisting of quartz glass and sapphire crystal;

the high temperature coating comprises a metal selected from the group consisting of gold and aluminum; and

the protective capillary comprises Inconel.

5. The high temperature pyrometer as claimed in claim 1, further in combination with a gas turbine having structural parts subject to high thermal load, wherein the measuring probe is arranged in the interior of the gas turbine in order to detect the heat radiation from said structural parts, and further comprising:

a detector;

a fiber for transmitting the heat radiation to the detector;

measuring electronics, the detector being connected to the measuring electronics; and

the detector being positioned outside the gas turbine.

6. The high temperature pyrometer as claimed in claim 5, wherein

the turbine includes a cooling duct and a guide blade having a trailing edge, a foot with a rear wall, and a bore therein;

the measuring probe is seated in the bore in the guide blade;

the fiber is located at least partially in the cooling duct; and

further comprising a guide tube receiving an element of the pyrometer selected from the group consisting of the fiber and the measuring probe.

7. The high temperature pyrometer as claimed in claim 6, wherein the gas turbine includes a moving blade, and wherein

the bore has an orifice (42) on one of the guide blade trailing edge or the blade foot rear wall;

and

the sensor head is positioned in the orifice and includes a viewing direction toward the moving blade.

8. The high temperature pyrometer as claimed in claim 6, wherein

the bore is located in a wall of the guide blade proximate the surface and has a blind hole;

further comprising a spacer for the sensor head in the blind hole; and

the sensor head and the blind hole together form a cavity.

9. A gas turbine suitable for generating electric energy, in combination with a high temperature pyrometer as claimed in claim 1, wherein

the gas turbine includes structural parts subject to high thermal load;

the measuring probe is arranged in the interior of the gas turbine;

a detector;

measuring electronics in communication with the detector;

the optic fiber is in communication with the detector for transmitting the heat radiation to the detector; and

the detector is positioned outside the gas turbine.

10. The gas turbine as claimed in claim 9, wherein

the gas turbine further comprises

a guide blade including a bore for receiving the measuring probe;

a cooling duct at least partially receiving the optic fiber; and

a guide tube receiving an element selected from the group consisting of the optic fiber and the measuring probe.

11. The gas turbine as claimed in claim 10, wherein

the gas turbine further comprises a moving blade and guide blade having a trailing edge and a blade foot having a rear wall, and wherein

the bore has an orifice on at least one of the trailing edge and the blade foot rear wall;

and

the sensor head is positioned in the orifice and includes a viewing direction toward the moving blade.

12. The gas turbine as claimed in claim 10, wherein

the bore is located in a wall of the guide blade proximate the surface and has a blind hole;

further comprising a spacer for the sensor head in the blind hole; and

the sensor head and the blind hole together form a cavity.

13. A method for monitoring a gas turbine using a high temperature pyrometer as claimed in claim 5, wherein

calculating a characteristic temperature signal of at least one structural part subject to high thermal load is with the measuring electronics;

and

monitoring a temperature signal as a protective signal for monitoring the gas turbine.

14. A method for monitoring a gas turbine as claimed in claim 13, wherein

the step of calculating comprises calculating a characteristic temperature signal of a structural part comprising a row of moving blades or guide blades;

and

determining a mean temperature signal, individual temperature signals, or both from the moving blades or guide blades as characteristic temperature signal.