JP2018100627A - Tail pipe for combustor, combustor and manufacturing method of tail pipe for combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve lifetime prediction accuracy of a tail pipe for combustor.SOLUTION: The present invention relates to a combustor tail pipe 18 that is provided in a combustor 3 and connected to a downstream side of an inner cylinder 17 and further extends to the downstream side, the combustor comprising: a pilot nozzle 33 extending in an axial line; multiple main nozzles 34 provided at an outer peripheral side of the pilot nozzle 33 while being spaced apart from each other in a circumferential direction and extending in an axial direction Dac; and the inner cylinder 17 enclosing the pilot nozzle 33 and the main nozzles 34 from the outer peripheral side. The tail pipe 18 for combustor comprises: a tail pipe body 36 which is formed cylindrical along an axial line Ac; and a temperature sensor 40 including multiple measuring points 41 that are provided at intervals on a measurement line extending in the axial direction Dac on an outer surface of the tail pipe body 36.SELECTED DRAWING: Figure 2

Description

  The present invention relates to a combustor transition, a combustor, and a method for manufacturing a combustor transition.

  The gas turbine includes a gas turbine rotor that rotates about a gas turbine axis, a casing that covers the gas turbine rotor, and a plurality of combustors attached to the casing. The plurality of combustors are attached to the vehicle compartment side by side in the circumferential direction with respect to the gas turbine axis.

  A combustor of a gas turbine includes a tail cylinder (or a combustion cylinder) that forms a flow path for combustion gas, and a fuel injector that injects fuel together with air into the tail cylinder. In the transition piece, the fuel burns and the combustion gas generated by the combustion of the fuel flows. That is, the inner peripheral surface of the transition piece is exposed to extremely high temperature combustion gas. For this reason, it is common to form a thermal barrier coating layer on the transition piece of the combustor (see, for example, Patent Document 1).

  The life of each component of the gas turbine is managed by various methods, but for the tail tube, the life is generally predicted based on data generated in a laboratory.

JP 2009-209440 A

  However, the life prediction based on the data generated in the laboratory has a problem that the life prediction accuracy is limited, and replacement is required earlier.

  An object of the present invention is to provide a combustor tail cylinder capable of improving life prediction accuracy by detailed temperature monitoring, a combustor including the combustor tail cylinder, and a method for manufacturing the combustor tail cylinder. .

  According to the first aspect of the present invention, the combustor tail tube includes a pilot nozzle extending along the axis, and a plurality of nozzles provided in the circumferential direction on the outer peripheral side of the pilot nozzle so as to extend in the axial direction. A combustor tail cylinder provided in a combustor including a nozzle, an inner cylinder surrounding the pilot nozzle and the main nozzle from an outer peripheral side, connected to a downstream side of the inner cylinder and extending further downstream; And a temperature sensor having a plurality of measurement points provided at intervals on a measurement line extending in the axial direction on the outer surface of the tail cylinder main body.

  According to such a configuration, detailed temperature monitoring of the combustor tail tube is possible. Specifically, the temperature distribution as a surface can be grasped by a plurality of measurement points. As a result, it is possible to grasp the loss of function due to deterioration of the material of the transition piece and the progress of peeling of the coating, cracking, or breakage, and the life prediction accuracy can be improved.

  In the combustor transition piece, the circumferential position of the measurement line may correspond to the circumferential position of the main nozzle.

  According to such a configuration, it is possible to measure the temperature of a higher temperature portion. That is, the temperature of a part that is exposed to a higher temperature and affects the life can be managed.

  According to the second aspect of the present invention, the combustor includes a pilot nozzle extending along the axis, and a main nozzle extending in the axial direction, the plurality of which is provided in the circumferential direction on the outer peripheral side of the pilot nozzle. And an inner cylinder that surrounds the pilot nozzle and the main nozzle from the outer periphery side, and the combustor tail cylinder.

  According to a third aspect of the present invention, a combustor tail cylinder manufacturing method is the above-described combustor tail cylinder manufacturing method, in which the temperature sensor is directly drawn on the tail cylinder using a drawing device.

  According to such a configuration, the combustor tail cylinder having the temperature sensor can be thinned. In addition, a plurality of temperature sensors can be easily formed.

  According to the present invention, detailed temperature monitoring of the combustor tail tube is possible. Specifically, the temperature distribution as a surface can be grasped by a plurality of measurement points. As a result, it is possible to grasp the loss of function due to deterioration of the material of the transition piece and the progress of peeling of the coating, cracking, or breakage, and the life prediction accuracy can be improved.

It is a typical whole side view of a gas turbine of an embodiment of the present invention. It is an expanded sectional view around a combustor of a gas turbine of an embodiment of the present invention. It is a perspective view of the transition piece of the combustor of the embodiment of the present invention. It is sectional drawing seen from the combustor axial direction of the transition piece of the combustor of embodiment of this invention. It is the schematic of the temperature sensor of embodiment of this invention. It is the schematic explaining the arrangement | positioning of the temperature sensor provided in the transition piece of embodiment of this invention. It is a graph which shows the metal temperature of the circumferential direction of the transition piece of embodiment of this invention.

Hereinafter, a gas turbine (rotary machine) including a combustor according to an embodiment of the present invention will be described in detail with reference to the drawings.
As shown in FIG. 1, the gas turbine 1 of the present embodiment generates a combustion gas G by combusting a fuel F in the compressed air A and a compressor 2 that compresses the outside air Ao to generate the compressed air A. A plurality of combustors 3 and a turbine 4 driven by combustion gas G are provided.

The compressor 2 includes a compressor rotor 6 that rotates about a gas turbine axis Ar, a compressor casing 7 that rotatably covers the compressor rotor 6, and a plurality of compressor vane rows 8. .
Hereinafter, a direction in which the gas turbine axis Ar extends is referred to as a gas turbine axis direction Da. Further, a circumferential direction centered on the gas turbine axis Ar is simply referred to as a circumferential direction Dc, and a direction perpendicular to the gas turbine axis Ar is referred to as a radial direction Dr. In the radial direction Dr, the side away from the gas turbine axis Ar is defined as the radially outer side, and the side approaching the gas turbine axis Ar is defined as the radially inner side.

  The compressor rotor 6 includes a compressor rotor shaft 9 extending in the gas turbine axial direction Da along the gas turbine axis Ar, and a plurality of compressor rotor blade rows 10 attached to the compressor rotor shaft 9. Yes. The plurality of compressor rotor cascades 10 are arranged in the gas turbine axial direction Da. Each compressor moving blade row 10 is composed of a plurality of moving blades arranged in the circumferential direction Dc. A compressor stationary blade row 8 is disposed on each downstream side of the plurality of compressor moving blade rows 10. Each of the compressor vane rows 8 is fixed inside the compressor casing 7. Each compressor stationary blade row 8 is composed of a plurality of stationary blades arranged in the circumferential direction Dc.

  The turbine 4 includes a turbine rotor 11 that rotates about a gas turbine axis Ar, a turbine casing 12 that rotatably covers the turbine rotor 11, and a plurality of turbine stationary blade rows 13. The turbine rotor 11 includes a turbine rotor shaft 14 extending in the gas turbine axial direction Da along the gas turbine axis Ar, and a plurality of turbine rotor blade rows 15 attached to the turbine rotor shaft 14.

  The plurality of turbine rotor blade rows 15 are arranged in the gas turbine axial direction Da. Each of the turbine rotor blade rows 15 includes a plurality of rotor blades arranged in the circumferential direction Dc. A turbine stationary blade row 13 is arranged on each upstream side of the plurality of turbine blade rows 15. Each turbine stationary blade row 13 is fixed inside the turbine casing 12. Each turbine stationary blade row 13 is composed of a plurality of turbine stationary blades 5 arranged in the circumferential direction Dc.

  The gas turbine 1 further includes a cylindrical intermediate casing 16 centered on the gas turbine axis Ar. The intermediate casing 16 is disposed between the compressor casing 7 and the turbine casing 12 in the gas turbine axial direction Da. The compressor casing 7, the intermediate casing 16, and the turbine casing 12 are connected to each other to form a gas turbine casing 21. The compressor rotor 6 and the turbine rotor 11 are located on the same gas turbine axis Ar, and are connected to each other to form a gas turbine rotor 20. For example, a rotor of a generator GEN is connected to the gas turbine rotor 20.

The combustor 3 generates high-temperature and high-pressure combustion gas G by supplying fuel F to the compressed air A compressed by the compressor 2. The plurality of combustors 3 are fixed to the intermediate casing 16 at intervals in the circumferential direction Dc.
As shown in FIG. 2, the combustor 3 is connected to the fuel injector 26 that injects the fuel F together with the compressed air A, the inner cylinder 17 that surrounds the fuel injector 26 from the outer peripheral side, and the downstream side of the inner cylinder 17. And a transition piece 18 (combustor transition piece) extending further downstream. The transition piece 18 sends the high-temperature and high-pressure combustion gas G to the combustion gas passage 22 in the turbine casing 12.

  The fuel injectors 26 are disposed at equal intervals in a pilot burner 27 disposed on the combustor axis Ac and in a circumferential direction around the combustor axis Ac (hereinafter referred to as a combustor circumferential direction Dcc). A plurality of main burners 28, a cylindrical burner holding cylinder 29, a combustor top flange 30 attached to the intermediate casing 16, and a nozzle base 31 fixed to the combustor top flange 30. ing. Hereinafter, the direction in which the combustor axis Ac extends is referred to as a combustor axis direction Dac.

The pilot burner 27 has a pilot nozzle 33 extending in the combustor axial direction Dac. The base end of the pilot nozzle 33 is fixed to the nozzle base 31. The main burner 28 has a main nozzle 34 extending in the combustor axial direction Dac. The base end of the main nozzle 34 is fixed to the nozzle base 31.
The burner holding cylinder 29 covers the outer peripheral sides of the pilot burner 27 and the plurality of main burners 28. The burner holding cylinder 29 is fixed to the nozzle base 31.
The combustor top flange 30 protrudes from the nozzle base 31 in a radial direction with respect to the combustor axis Ac. The combustor top flange 30 has an annular shape around the combustor axis Ac.

  A plurality of fuel pipes for supplying fuel F to the plurality of combustors 3 and a cooling medium are not shown in the region along the outer peripheral surface of the intermediate casing 16 on the outer peripheral side of the intermediate casing 16. Are provided with a plurality of cooling medium pipes or the like for supplying high-temperature components in contact with the high-temperature combustion gas G in the gas turbine 1.

  As shown in FIG. 3, the transition piece 18 includes a transition piece main body 36 having a cylindrical shape that gradually decreases in diameter toward the downstream side in the combustor axial direction Dac, and a plurality of transition pieces provided on the transition piece main body 36. And a temperature sensor 40. The temperature sensor 40 is a thermocouple that makes a circuit by bringing the tips of two kinds of metal wires into contact with each other and measures a temperature difference through a thermoelectromotive force generated at a junction (measurement point).

Each temperature sensor 40 includes a measurement point 41 that is a location for measuring temperature, a first metal wire portion 42, and a second metal wire portion 43 (see FIG. 5). The measurement point 41 is a joint point between the first metal wire portion 42 and the second metal wire portion 43.
The plurality of measurement points 41 are provided on the plurality of measurement lines L provided on the transition piece main body 36 at intervals in the combustor axial direction Dac. The measurement line L is a virtual line extending in the combustor axial direction Dac on the outer surface of the transition piece main body 36. The measurement lines L are set to be equally spaced in the combustor circumferential direction Dcc with the combustor axis Ac as the center. The number of measurement lines L corresponds to the number of main nozzles 34.

  It is preferable that the interval between the measurement points 41 in the combustor axial direction Dac is approximately the same as the interval between the measurement lines L adjacent in the combustor circumferential direction Dcc. Thereby, the space | interval of the measurement points 41 adjacent to the combustor circumferential direction Dcc and the space | interval of the measurement points 41 adjacent to the combustor axial direction Dac become comparable. As a result, the measurement points 41 are evenly arranged on the outer surface of the transition piece main body 36.

  As shown in FIG. 4, the inner surface of the transition piece main body 36 is provided with a thermal barrier coating (TBC, Thermal Barrier Coating). Specifically, the transition piece main body 36 is formed of a base material 37 formed of a heat resistant alloy and a thermal barrier coating layer 38. The thermal barrier coating layer 38 is formed of a metal bond coat layer for improving adhesion to the base material 37 and oxidation resistance, and a ceramic top coat layer for improving thermal barrier properties.

  The measurement point 41 of the temperature sensor 40 is formed on the surface of the thermal barrier coating layer 38. The formation position of the measurement point 41 is not limited to this, and may be, for example, the inside of the thermal barrier coating layer 38 or the back surface (surface opposite to the front surface) of the thermal barrier coating layer 38.

Next, details of the temperature sensor 40 will be described.
As shown in FIG. 5, the plurality of measurement points 41 of the temperature sensor 40 are arranged along the measurement line L. The first metal wire portion 42 extends on the measurement line L. The second metal line portion 43 extends along the measurement line L after extending from each measurement point 41 in a direction intersecting the measurement line L. That is, in the plurality of temperature sensors 40, the first metal wire portion 42 is common to the plurality of measurement points 41.

The line widths of the first metal line portion 42 and the second metal line portion 43 can be set to 250 μm, for example. Moreover, the thickness of the 1st metal wire part 42 and the 2nd metal wire part 43 can be 25 micrometers, for example.
As a metal constituting the first metal wire portion 42 and the second metal wire portion 43, it is preferable to use platinum or a platinum rhodium alloy suitable for high temperature measurement.

As shown in FIG. 6, the circumferential position around the combustor axis Ac of the measurement line L where the measurement point 41 of the temperature sensor 40 is arranged (triangle mark in FIG. 6) is the circumferential position of the main nozzle 34. Corresponds to the position. That is, the eight measurement lines L are set so that the positions of the eight main nozzles 34 and the combustor circumferential direction Dcc are the same.
FIG. 7 is a graph showing the metal temperature in the combustor circumferential direction Dcc of the tail cylinder 18 with the horizontal axis representing the angle in the combustor circumferential direction Dcc of the tail cylinder 18 and the vertical axis representing the metal temperature. The Roman numerals I to VIII in FIG. 7 correspond to the Roman numerals I to VIII in FIG.
Here, as shown in FIG. 7, the metal temperature in the combustor circumferential direction Dcc of the transition piece 18 changes corresponding to the position of the main nozzle 34 in the combustor circumferential direction Dcc. The metal temperature in the combustor circumferential direction Dcc of the transition piece 18 is higher at the position where the main nozzle 34 is disposed. The position where the metal temperature in the combustor circumferential direction Dcc of the transition piece 18 is high coincides with the position where the main nozzle 34 is installed.

Specifically, the metal temperature at the position corresponding to the main nozzle 34 (I) (the position of 22.5 ° when the top of the transition piece 18 is 0 °) is high, and similarly, the main nozzle 34 ( II), a position corresponding to the main nozzle 34 (III), a position corresponding to the main nozzle 34 (IV), a position corresponding to the main nozzle 34 (V), and a position corresponding to the main nozzle 34 (VII). The temperature at the position corresponding to the main nozzle 34 (VIII) is high.
The position of the measurement line L in the combustor circumferential direction Dcc, that is, the position in the combustor circumferential direction Dcc where the measurement point 41 of the temperature sensor 40 is disposed is the same as the position of the main nozzle 34 in the combustor circumferential direction Dcc. I'm doing it.

  The plurality of temperature sensors 40 are connected to a measuring instrument (not shown). The user can grasp the metal temperature of the transition piece 18 measured by the plurality of temperature sensors 40 via the measuring device.

Next, a method for manufacturing the transition piece 18 will be described.
The method for manufacturing the transition piece 18 of this embodiment includes a transition piece body manufacturing process for manufacturing the transition piece body 36 and a temperature sensor forming process for forming the temperature sensor 40.
In the temperature sensor forming step, the temperature sensor 40 can be formed by using a drawing apparatus that directly draws the first metal wire portion 42 and the second metal wire portion 43. As the drawing device, a device capable of continuously arranging linear metals, for example, a welding robot or a metal 3D (three-dimensional) printer can be employed. A welding apparatus such as an LMD (Laser Metal Deposition, Laser Metal Deposition, hereinafter referred to as LMD) apparatus can also be employed.
In the temperature sensor forming step, the first metal wire portion 42 and the second metal wire portion 43 constituting the temperature sensor 40 are directly drawn on the tail tube main body 36.

Next, the operation and action of the gas turbine 1 of the present embodiment will be described.
The compressor 2 sucks outside air Ao and compresses it. The air compressed by the compressor 2 is guided into the main burner 28 and the pilot burner 27 of the combustor 3. Fuel is supplied to the main burner 28 and the pilot burner 27 from a fuel supply source. The main burner 28 is a premixed gas premixed with fuel and air.
It ejects into the tail cylinder 18. The premixed gas is premixed and combusted in the transition piece 18. The pilot burner 27 ejects fuel and air into the tail cylinder 18. This fuel is subjected to diffusion combustion or premixed combustion in the transition piece 18. The high-temperature and high-pressure combustion gas G generated by the combustion of fuel in the tail cylinder 18 is guided into the combustion gas passage 22 of the turbine 4 to rotate the turbine rotor 11.

  According to the embodiment, by providing the plurality of temperature sensors 40 on the outer surface of the transition piece 18, detailed temperature monitoring of the transition piece 18 becomes possible. Specifically, the temperature distribution as a surface can be grasped by the plurality of measurement points 41. As a result, it is possible to grasp the progress of the loss of function due to material deterioration of the transition piece 18 and the peeling of the coating, cracks, or breakage, and the life prediction accuracy can be improved.

  Further, the position in the combustor circumferential direction Dcc of the measurement line L where the measurement point 41 of the temperature sensor 40 is arranged corresponds to the position of the main nozzle 34 in the combustor circumferential direction Dcc. Is possible. That is, the temperature of a part that is exposed to a higher temperature and affects the life can be managed.

In addition, by directly drawing the temperature sensor 40 on the transition piece 18 using a drawing apparatus, it is possible to reduce the thickness of the transition piece 18 having the temperature sensor 40. Moreover, the several temperature sensor 40 can be formed easily. Moreover, the width | variety of the 1st metal wire part 42 and the 2nd metal wire part 43 which comprises the temperature sensor 40 can be made thin.
Further, by making the first metal wire portion 42 common to the plurality of measurement points 41, the space required for the temperature sensor 40 can be reduced.

The embodiment of the present invention has been described in detail with reference to the drawings. However, the specific configuration is not limited to this embodiment, and includes design changes and the like within a scope not departing from the gist of the present invention. .
In the above-described embodiment, a thermocouple is used as the temperature sensor 40. However, the present invention is not limited to this, and any known device may be used as long as it can be disposed on the surface of the tail tube 18.

DESCRIPTION OF SYMBOLS 1 Gas turbine 2 Compressor 3 Combustor 4 Turbine 6 Compressor rotor 9 Compressor rotor shaft 11 Turbine rotor 14 Turbine rotor shaft 17 Inner cylinder 18 Tail cylinder 20 Gas turbine rotor 21 Gas turbine casing 26 Fuel injector 27 Pilot burner 28 Main burner 33 Pilot nozzle 34 Main nozzle 36 Cylinder body 37 Base material 38 Thermal barrier coating layer 40 Temperature sensor 41 Measurement point 42 First metal wire portion 43 Second metal wire portion A Compressed air Ac Combustor axis (axis)
Ar Gas turbine axis Da Gas turbine axis direction Dac Combustor axis direction (axis direction)
Dc circumferential direction Dcc combustor circumferential direction (circumferential direction)
Dr radial direction G combustion gas L measurement line

Claims (4)

A pilot nozzle extending along an axis;
A plurality of main nozzles that are provided in the circumferential direction on the outer circumferential side of the pilot nozzle and that extend in the axial direction.
A combustor tail cylinder that is provided in a combustor including an inner cylinder that surrounds the pilot nozzle and the main nozzle from the outer peripheral side, and that is connected to a downstream side of the inner cylinder and extends further downstream;
A tail tube main body having a cylindrical shape along the axis;
And a temperature sensor having a plurality of measurement points provided at intervals on a measurement line extending in the axial direction on the outer surface of the tail cylinder body.   The combustor tail cylinder according to claim 1, wherein a circumferential position of the measurement line corresponds to a circumferential position of the main nozzle. A pilot nozzle extending along an axis;
A plurality of nozzles provided in the circumferential direction on the outer peripheral side of the pilot nozzle, and a main nozzle extending in the axial direction;
An inner cylinder surrounding the pilot nozzle and the main nozzle from the outer peripheral side;
A combustor comprising the combustor tail cylinder according to claim 1 or 2. A method for manufacturing a combustor tail cylinder according to claim 1 or 2,
A method for manufacturing a combustor tail cylinder, in which the temperature sensor is directly depicted on the tail cylinder using a drawing apparatus.

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