JP4672566B2 - Temperature measuring device, combustion monitoring device, and gas turbine - Google Patents

Description

  The present invention relates to a temperature measuring device for detecting a combustion state in a combustor of a gas turbine, and to a combustion monitoring device for monitoring the combustion state in the combustor based on a signal from the temperature measuring device, and The present invention relates to a gas turbine equipped with this combustion monitoring device.

  The gas turbine is rotationally driven by using a combustion gas obtained by a combustion operation in an installed combustor as a drive source. That is, the combustion gas from the combustor is supplied to the space formed by the moving blades disposed on the rotor and the stationary blades disposed in the passenger compartment, so that the rotor on which the moving blades are disposed. Rotate. In such a gas turbine, a plurality of combustors are annularly arranged on the outer periphery of the rotor, and all of the plurality of combustors must operate normally during operation of the gas turbine.

  For this reason, during operation of the gas turbine, whether or not an abnormality such as misfire or clogging of the fuel injection nozzle has occurred is constantly monitored for each combustor. When it is determined that an abnormality has occurred in at least one of the combustors, the gas turbine is immediately stopped automatically or emergencyly stopped to protect the gas turbine (see Patent Document 1). In order to protect the gas turbine in this way, the combustion state of the combustor is monitored. In order to monitor the combustion state of the combustor, the turbine blade outlet (downstream in the flow direction of the combustion gas) is monitored. , The same number or more thermocouples as the number of combustors are arranged in an annular shape.

  The combustion state of the combustor is monitored based on the temperature of the combustion gas (blade path temperature) at the turbine blade outlet measured by the thermocouple. That is, if an abnormality occurs in any one combustor, only the blade path temperature corresponding to this abnormal combustor is compared with the blade path temperature corresponding to the other combustor, and the deviation (average value and Difference) or the amount of change (rate of change) increases. Thereby, the abnormality of the abnormal combustor can be detected. Therefore, the gas turbine can be protected by outputting the gas turbine automatic stop signal or the gas turbine emergency stop signal as the gas turbine protection signal based on the measured value of the blade path temperature of these thermocouples.

  In order to protect such a gas turbine, a thermocouple used for monitoring the combustion state of the combustor is covered with a protective tube so as to be protected from a high temperature atmosphere. The thermocouple covered with the protective tube is configured as a temperature measuring device for measuring the blade path temperature, and is installed at the turbine blade outlet. That is, as shown in the cross-sectional view of FIG. 6, the temperature measuring device 100 is installed inside the diffuser 2 on the downstream side of the moving blade 11 that is the final stage installed on the outer periphery of the rotor 1. The temperature measuring device 100 is protected from being exposed to a high temperature environment by being formed through a thermocouple 101 in a protective tube 102 made of a heat-resistant material.

As shown in FIG. 6, the temperature measuring device 100 is inserted from the outer casing 3 that covers the outer periphery of the diffuser 2, and between the moving blade 11 that is the final stage and the strut cover 24 installed in the diffuser 2. The thermocouple 101 is installed so that the tip of the thermocouple 101 is positioned at the top. As a result, the exhaust gas from the moving blade 11 at the final stage flows to the tip of the thermocouple 101, whereby the blade path temperature, which is the temperature of the exhaust gas, is measured.
JP 2000-163606 A

  Thus, the exhaust gas flowing inside the diffuser 2 in which the temperature measuring device 100 is installed has a high temperature, and the temperature difference between the diffuser 2 and the outside becomes large, and the diffuser 2 is thermally expanded. Therefore, the relative position of the outer casing 3 and the diffuser 2 changes depending on when the gas turbine is stopped and when it is driven. Then, displacement of each position of the diffuser 2 due to this temperature difference appears as vibration. Therefore, in order to absorb the position displacement due to the vibration, a seal member (not shown) such as a bellows is used to seal the atmosphere inside and outside the diffuser 2 at a portion where the temperature measuring device 100 is inserted into the diffuser 2. ) Is installed.

  However, even if the seal member is installed in this manner, damage is generated in the temperature measurement device 100 itself or the seal member at the installation position of the temperature measurement device 100 on the diffuser 2 based on the combustion vibration approaching the diffuser 2. To do. Therefore, damage such as the protective tube 102 being cut, insulation failure between the strands of the thermocouple 101 occurs, or the mounting point of the temperature measuring device 100 is loosened and the measurement point is shifted from the normal position. As a result, the blade path temperature measurement value by the temperature measurement device 100 may become abnormal.

  In view of such a problem, an object of the present invention is to provide a temperature measurement device having a structure capable of preventing damage due to thermal vibration. Moreover, it aims at providing the combustion monitoring apparatus provided with such a temperature measuring device, and the gas turbine by which the combustion state of a combustor is monitored by this combustion monitoring apparatus.

In order to achieve the above object, a temperature measuring device according to the present invention is installed in a diffuser for exhausting combustion gas flowing through the turbine body in a gas turbine having a turbine body rotated by combustion gas of a combustor. A temperature measuring device for measuring a temperature of combustion gas discharged from the turbine body, wherein the thermocouple is inserted into the diffuser from outside the casing covering the turbine body and the diffuser, and the casing of the diffuser. A thermotube that is supported and fixed to the outer wall surface of the thermocouple and covers the portion of the thermocouple inserted into the diffuser to protect the thermocouple from heat, and the thermocouple is inserted through the vehicle compartment. And a terminal head which is installed outside the vehicle compartment and presses the tip of the protective tube so as to contact the tip of the thermocouple , Wherein the protective tube, both ends and the opening, a tube body extending within said diffuser while being supported and fixed to the outer wall surface of the casing side of the diffuser, the tip of the diffuser inside the tube body A well that is installed and abutted against the tip of the thermocouple; and a fixing member that fixes the well to the tube body, and the fixing member has a ring shape in which an L-shaped cross section is continuous in a circumferential shape. A tip end surface of the tube body inside the diffuser and a first end surface of the well contacting the thermocouple are in contact with each other, and a side surface of each of the tube body and the well and a side opposite to the first end surface of the well The well is fixed to the distal end of the tube body by contacting the second end surface of the tube and the inner wall surface of the fixing member .

Further, in such a temperature measuring device, the tip of the pre-Symbol thermocouple by the wells in contact with fixed to the tube body, to fix the tip position of the thermocouples inside the diffuser.

  Then, the pipe body penetrates the outer wall of the diffuser on the passenger compartment side and is fixed at a contact portion with the outer wall surface of the diffuser on the passenger compartment side, so that the inside of the diffuser and the outer portion of the diffuser are fixed. It does not matter as a seal.

  Further, at the tip end portion on the outer wall surface side of the diffuser of the tube body, the inner wall surface has a shape in which the opening area increases toward the tip, thereby preventing the thermocouple from coming into contact with the tube body and being damaged. It does n’t matter. At this time, the inner wall surface may have a curved surface shape that smoothly changes toward the distal end at the distal end portion on the outer wall surface side of the diffuser of the pipe body.

  In the thermocouple, a portion of the pipe body corresponding to the position near the tip end on the outer wall surface side of the diffuser may be coated with a curable material.

  Further, the combustion monitoring device of the present invention detects the combustion state of the combustor based on the temperature measurement value of the combustion gas that has passed through the turbine body and is obtained by measurement by any one of the temperature measurement devices described above. It is characterized by that.

  Furthermore, the gas turbine of the present invention includes the above-described combustion monitoring device, control of the flow rate of fuel supplied to the combustor based on the combustion state of the combustor confirmed by the combustion monitoring device, and the gas turbine main body. And a controller that performs emergency stop control.

  According to the present invention, by providing the protective tube only inside the diffuser, the influence of thermal vibration caused by the diffuser can be absorbed by the portion in the space between the diffuser of the thermocouple and the passenger compartment. Displacement of the temperature measurement position can be prevented. Compared to the case where all the thermocouples are covered with a protective tube as in the prior art, the thermocouple can flexibly cope with the bending due to the thermal vibration of the diffuser, so that the thermocouple can be prevented from being damaged. Further, in the tube main body, the inner wall surface of the tube main body has a shape in which the opening area increases toward the tip, so that the thermocouple can be prevented from coming into contact with the tube main body and being damaged. Furthermore, since the inner wall surface of the tube body has a curved shape, damage damage when the thermocouple contacts the tube body can be suppressed.

  Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings. FIG. 1 is a schematic diagram showing a configuration of a gas turbine in the present embodiment. FIG. 2 is a schematic cross-sectional view around the diffuser showing the configuration of the temperature measuring device installed in the gas turbine of FIG.

(Configuration of gas turbine)
As shown in FIG. 1, the gas turbine of this embodiment is provided with a plurality of combustors 6 on the turbine inlet side (upstream side in the combustion gas flow direction) of the turbine body 10, The rotor blades 11 installed on the outer wall of the rotor 1 (see FIG. 2) and the stationary blades 41 installed on the inner wall of the inner casing 4 (see FIG. 2) covering the outer periphery of the rotor 1 are alternately arranged. Yes. A plurality of temperature measuring devices 5 (which are the same as the number of the combustors 6 in the present embodiment) are installed on the turbine outlet side (downstream side in the combustion gas flow direction) of the turbine body 10.

  Further, the combustor 6 and the temperature measuring device 5 are arranged in an annular shape at equal intervals on the outer periphery of the rotor 1. At this time, the temperature measuring device 5 is installed so as to correspond to the circumferential installation position of the combustor 6. The blade path temperature (hereinafter referred to as “BPT temperature”) of the combustion gas of each combustor 6 is not measured at the turbine outlet position corresponding to each combustor 6, but from each combustor 6 to the turbine body. It is measured at the turbine outlet position at an angle shifted in the circumferential direction by several combustors in the 10 rotation directions. Such a deviation in blade path temperature is called a swirl angle and is expressed in units of the number of combustors, and varies depending on the magnitude of the load.

Therefore, for example, when the temperature measuring device 5 is installed at a position overlapping with the combustor 6 in the axial direction and the swirl angle is 2.7 degrees , the blade path of the combustion gas of the combustor 6 as the measurement target The temperature is not at the temperature measuring device 5 arranged at the turbine outlet position corresponding to the combustor 6 but at the turbine outlet position shifted in the circumferential direction by two or three from the temperature measuring device 5. It is measured by the temperature measuring device 5. Further, each temperature measuring device 5 may be installed at a position shifted in the circumferential direction by the swirl angle from each combustor 6 so that the relationship between the combustor 6 and the temperature measuring device 5 is 1: 1. I do not care.

  Further, the gas turbine shown in FIG. 1 is provided with a combustion monitoring device 7 for monitoring the combustion state of each combustor 6 given a measurement value of the BPT temperature at the turbine outlet position measured by the temperature measuring device 5, and combustion monitoring. A control device 8 that confirms an abnormality or the like according to the combustion state of each combustor 6 confirmed by the device 7 and instructs a fuel supply control to each combustor 6 or an emergency stop of the gas turbine, and the control device 8 And a fuel supply device 9 that is controlled to set the fuel supply amount to each combustor 6.

  In the gas turbine configured as described above, the fuel supplied from the fuel supply device 9 is mixed with the compressed air supplied from a compressor (not shown) and burned to generate combustion gas. When the combustion gas of each combustor 6 is introduced from the turbine inlet side of the turbine body 10, the combustion gas flows toward the moving blades 11 and the stationary blades 41 installed in the turbine body 10. The rotor 1 at 10 rotates. And the combustion gas which rotationally driven the rotor 1 is discharged | emitted as exhaust gas from the turbine exit of the turbine main body 10, The temperature of the exhaust gas in the turbine exit at this time is measured by each temperature measurement apparatus 5 as BPT temperature. .

  In the combustion monitoring device 7 to which the BPT temperature measurement value obtained by measurement by each temperature measurement device 5 is given, each combustor 6 corresponding to each temperature measurement device 5 is determined by the BPT temperature measurement value from each temperature measurement device 5. The combustion state of is monitored. At this time, when the temperature deviation obtained from the BPT temperature measurement value of any one of the temperature measurement devices 5 exceeds a preset BPT temperature deviation large set value, an abnormality has occurred in the combustor 6 for the temperature measurement device 5. This is notified to the control device 8. A combustor for the temperature measuring device 5 also when the amount of change in the temperature deviation obtained from the measured BPT temperature of any temperature measuring device 5 exceeds a preset large value of BPT temperature deviation changing amount. 6 notifies the control device 8 that an abnormality has occurred.

  And in the control apparatus 8, if the combustor 6 with respect to the temperature measurement apparatus 5 with which the temperature deviation obtained from a BPT temperature measurement value exceeded BPT temperature deviation large setting value is alert | reported, the gas turbine for automatically stopping a gas turbine An automatic stop signal is generated and sent to the fuel supply device 9. Further, when the combustor 6 for the temperature measuring device 5 in which the change amount in the temperature deviation obtained from the measured BPT temperature value exceeds the BPT temperature deviation change amount large set value is notified, the gas turbine for emergency stop of the gas turbine An emergency stop signal is generated and sent to the fuel supply device 9.

  When a gas turbine automatic stop signal is output from the control device 8 operating in this way, the fuel supply device 9 automatically reduces the fuel supplied to the combustor 6 and reduces the load, thereby automatically Stop. Further, when a gas turbine emergency stop signal is output from the control device 8, the fuel supply device 9 instantaneously stops the gas turbine by shutting off the fuel supply to the combustor 6.

(Configuration of temperature measuring device)
Below, the temperature measuring device 5 used for the gas turbine of a structure like FIG. 1 is demonstrated with reference to FIGS.

  As shown in FIG. 2, the turbine body 10 is configured so that a rotor 1 serving as a rotation shaft, a rotor blade 11 installed on an outer wall of the rotor 1, and a space for flowing combustion gas between the rotor 1 are configured. A space through which cooling air flows between the inner casing 4 that covers the outer periphery of the inner casing 4, the stationary blade 41 that is installed on the inner wall of the inner casing 4, and the inner casing 4 that covers the outer peripheral side of the inner casing 4 And an outer casing 3 constituting the. The inner casing 4 is fixed by being connected to the outer casing 3. The rear end (downstream side) of the rotor 1 is supported by a bearing (journal bearing) 12 housed in a bearing housing 13.

  And the diffuser 2 comprised by the double ring | wheel for exhausting the combustion gas which flowed through the moving blade 11 and the stationary blade 41 is installed in the downstream of this turbine main body 10. FIG. The diffuser 2 has an inner cylinder 21 whose outer wall surface forms the same surface as the shroud surface of the rotor blade 11 at the final stage, and an outer cylinder 22 whose inner wall surface forms the same surface as the inner wall surface of the inner casing 4. The struts 23 arranged radially to support the bearing housing 13 installed inside the inner cylinder 21 and the inner cylinder 21 are fixed by covering the struts 23 and connecting the inner cylinder 21 and the outer cylinder 22. A strut cover 24 that is connected to each of the outer cylinder 22 and the outer casing 3, and a fixing ring 25 that fixes the outer cylinder 22 to each other. The strut cover 24 has a structure that reduces resistance to exhaust gas from the turbine body 10.

  In the diffuser 2, the inner cylinder 21 and the outer cylinder 22 are arranged concentrically, so that an annular flow path is formed between the inner cylinder 21 and the outer cylinder 22. At this time, the inner cylinder 21 has a cylindrical shape, but the outer cylinder 22 has a truncated cone shape whose diameter increases toward the downstream side. Therefore, the diffuser 2 has a cross-sectional area of the flow path from upstream to downstream. It is a so-called conical diffuser that grows gradually. The strut cover 24 maintains the space between the inner cylinder 21 and the outer cylinder 22 to maintain the shape of the annular flow path.

  Thus, when the diffuser 2 is configured, the temperature measuring device 5 for measuring the BPT temperature, which is the temperature of the exhaust gas flowing into the space configured between the inner cylinder 21 and the outer cylinder 22 of the diffuser 2, It is installed so as to be inserted from the outside of the outer casing 3. The temperature measuring device 5 includes a thermocouple 51 having a tip installed in the diffuser 2, a protective tube 52 that covers the thermocouple 51 inserted in the diffuser 2, protects the heat, and seals the diffuser 2. A through-hole 53 provided in the outer casing 3 into which the thermocouple 51 is inserted, a terminal head 55 provided at a front end of the outer casing 3 outside and leading to a lead wire 56 connected to the thermocouple 51; Is provided.

  As shown in the schematic configuration diagram of FIG. 3, each of the thermocouple 51 includes a thermocouple element 51a made of a pair of dissimilar metals capable of generating a large thermoelectromotive force such as chromel and alumel, and a thermocouple element 51a. Insulating tube 51b that insulates each thermocouple element 51a by covering the surface, and thermocouple element 51a covered with insulating tube 51b is further covered to protect from a high temperature atmosphere and flexibly acts on bending. And a sheath 51c that can be used.

  As shown in the schematic block diagram of FIG. 3, the terminal head 55 into which the thermocouple 51 is inserted and connected to the lead wire 56 are a protective tube 55a that covers the outer periphery of the thermocouple 51, and a distal end side of the protective tube 55a. A fixing member 55b, which is fixed to the outer casing 3 by being screwed into the through-hole 53, and a base end portion inside the protective tube 55a to press the thermocouple 51 into the diffuser 2. A spring 55c, a terminal plate 55d for electrically connecting the thermocouple element 51a of the thermocouple 51 and the lead wire 56, and a head portion connected to the base end side of the protective tube 55a having the terminal plate 55d therein 55e.

  The configuration of the protective tube 52 into which the thermocouple 51 is inserted and installed in the diffuser 2 is configured as shown in the schematic cross-sectional view of FIG. That is, a well 52a that is in contact with the tip of the thermocouple 51 and forms the tip of the protective tube 52, a tube body 52b that covers the thermocouple 51 and is installed so as to penetrate the outer cylinder 22 of the diffuser 2, A flange 52c that is provided on the proximal end side of the tube main body 52b and supports the tube main body 52b by being in contact with and fixed to the outer wall of the outer cylinder 22, and a ring-shaped member that fixes the well 52a to the distal end of the tube main body 52b. A fixing member 52d.

  The outer diameter of the well 52a is equal to the outer diameter of the tube main body 52b so that the outer peripheral side of the end surface of the well 52a that contacts the thermocouple 51 is in contact with the tip end surface of the tube main body 52b. . Further, the end surface of the well 52a opposite to the contact end surface with the thermocouple 51 has a shape in which the central portion protrudes. Furthermore, the fixing member 52d has a configuration in which an L-shaped cross section is formed in a ring shape, the end surface of the well 52a opposite to the contact end surface with the thermocouple 51, the outer wall surface of the well 52a, and the outside of the tube body 52b. Abuts against the wall. At this time, the outer wall surface of the well 52a and the tube body 52b and the inner wall surface of the fixing member 52d are threaded, and the well 52a and the tube body 52b are male screws, and the fixing member 52d is a female screw.

  By configuring the distal end side of the protective tube 52 in this way, the thermocouple 51 is inserted from the distal end side of the tube body 52b, and the distal end of the tube body 52b is covered with the well 52a to which the distal end of the thermocouple 51 is fixed in contact. The tip of the thermocouple 51 is fixed to the end surface of the well 52a, for example, by welding. Then, the fixing member 52d is screwed from the distal end side of the protective tube 52 and is fitted until the fixing member 52d comes into contact with the end surface of the well 52a, whereby the well 52a is supported and fixed to the distal end of the tube main body 52b.

  The tube main body 52b is configured to protrude to the outside of the outer cylinder 22 of the diffuser 2, and an end 52e that is outside the outer cylinder 22 is opened, and the end 52e at the opening 52e is open. The inner wall has a truncated cone shape whose opening area increases toward the tip of the end 52e. By comprising in this way, the contact of the thermocouple 51 in the edge part 52e outside the outer cylinder 22 in the pipe | tube main body 52b can be prevented.

  At this time, the outer wall of the sheath 51c is shaved when the thermocouple 51 comes into contact with the end 52e so that the inner wall surface of the tube body 52b is smoothly curved toward the outer side of the outer cylinder 22 and the thermocouple 51 comes into contact. It is possible to prevent the pair 51 from being damaged. Further, in the vicinity of the end 52e of the tube main body 52b, the outer wall of the sheath 51c of the thermocouple 51 is coated with a coating material such as chrome carbide with a coating, and the outer wall of the sheath 51c is shaved to remove the thermocouple 51. It is also possible to prevent damage.

  And the flange 52c contact | abutted with the outer wall surface of the outer side cylinder 22 of the diffuser 2 is installed in the outer wall surface of the pipe main body 52b at the edge part 52e side of the pipe main body 52b. The flange 52c is brought into contact with the outer wall surface of the outer cylinder 22 and is fixed to the outer cylinder 22 with a bolt or the like, whereby the protective tube 52 is supported and fixed to the outer cylinder 22 of the diffuser 2. The pipe body 52b may be supported and fixed to the outer cylinder 22 of the diffuser 2 by welding the end 52e side to the outer cylinder 22 of the diffuser 2.

  The protective tube 52 configured in this manner is installed at a position between the last stage moving blade 11 and the strut cover 24. Further, by installing the protective tube 52 so that the well 52a installed at the tip of the protective tube 52 is positioned at the center position of the space formed by the inner cylinder 21 and the outer cylinder 22 of the diffuser 2, the turbine body 10 The BPT temperature in the vicinity of the turbine outlet can be measured. Further, the protective tube 52 is made of a heat-resistant material, and the thermocouple 51 is prevented from being exposed to the high temperature atmosphere inside the diffuser 2. Since the space between the diffuser 2 and the outer casing 3 has a sufficiently low temperature atmosphere as compared with the temperature atmosphere inside the diffuser 2, the thermocouple 51 can be sufficiently protected by the sheath 51c.

  Further, the configuration of the through hole 53 in which the thermocouple 51 is similarly inserted and installed in the outer casing 3 is as shown in the schematic cross-sectional view of FIG. That is, the through hole 53 configured to penetrate the outer casing 3 includes a thick screw-in part 53 a formed on the outer wall side of the outer casing 3 and a narrow hole formed on the inner wall side of the outer casing 3. Part 53b. In the through hole 53 configured as described above, the fixing member 55b of the terminal head 55 is inserted into the screw-in portion 53a, and the thermocouple 51 is inserted into the hole 53b.

  That is, the hole 53b is formed as a hole having an inner diameter slightly thicker than the outer diameter of the sheath 51c of the thermocouple 51, and the screw-in part 53a and the fixing member 55b are formed as a female screw and a male screw, respectively. As a result, the thermocouple 51 whose tip is fixed to the protective tube 52 is inserted through the hole 53 b, thereby penetrating the through hole 53 of the outer casing 3. Then, the thermocouple 51 is inserted into the protective tube 55 a of the terminal head 55 so as to cover the end portion of the thermocouple 51 protruding outside the outer casing 3 through the through hole 53. Further, the terminal head 55 is supported and fixed in the through hole 53 of the outer casing 3 by screwing the fixing member 55 b of the terminal head 55 into the screwed portion 53 a of the through hole 53.

  As shown in FIGS. 2 to 5, by configuring the temperature measurement device 5, the thermocouple 51 is covered only by the sheath 51 c in the space between the outer cylinder 22 of the diffuser 2 and the outer casing 3. It becomes. As a result, when the gas turbine is driven, the exhaust gas discharged from the turbine body 10 to the diffuser 2 is deformed by exposure of the interior of the diffuser 2 to a high temperature. Vibration can be absorbed by flexibility. At this time, since the thermocouple 51 is pressed by the spring 55c of the terminal head 55, the tip of the thermocouple 51 can be kept in contact with the well 52a.

  In the gas turbine according to the present embodiment, the thermocouple 51 is supported in the temperature measuring device 5 by fixing the tip of the thermocouple 51 at the tip of the protective tube 52 installed in the diffuser 2. Therefore, the relative position of the thermocouple 51 with respect to the diffuser 2 can be kept constant without being displaced even if thermal vibration occurs in the diffuser 2. Thereby, the influence by the thermal vibration of the diffuser 2 can be reduced with respect to the BPT temperature measured by the temperature measuring device 5.

These are the schematic which shows the structure of the gas turbine in this embodiment. FIG. 2 is a schematic cross-sectional view of the periphery of a diffuser showing a configuration of a temperature measuring device installed in the gas turbine of FIG. 1. These are schematic block diagrams which show the structure of the thermocouple in the temperature measuring device shown in FIG. These are schematic sectional drawings which show the structure of the protective tube part in the temperature measuring device shown in FIG. These are schematic sectional drawings which show the structure of the through-hole part in the temperature measuring device shown in FIG. These are schematic sectional drawing of the periphery of a diffuser which shows the structure of the temperature measuring apparatus installed in the conventional gas turbine.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Rotor 2 Diffuser 3 Outer casing 4 Inner casing 5 Temperature measuring device 6 Combustor 7 Combustion monitoring device 8 Control device 9 Fuel supply device 10 Turbine body 11 Rotor blade 12 Bearing 13 Bearing housing 21 Inner cylinder 22 Outer cylinder 23 Strut 24 Strut Cover 25 Fixing ring 41 Stator blade 51 Thermocouple 52 Protective tube 53 Through hole 55 Terminal head 56 Lead wire

Claims (8)

In a gas turbine having a turbine body that is rotated by combustion gas of a combustor, the temperature measurement is performed in a diffuser that exhausts the combustion gas that has flowed through the turbine body, and measures the temperature of the combustion gas discharged from the turbine body. A device,
A thermocouple inserted into the diffuser from the outside of the passenger compartment covering the turbine body and the diffuser;
A protective tube that is supported and fixed to the outer wall surface of the diffuser on the passenger compartment side and that heat-protects the thermocouple by covering a portion of the thermocouple inserted into the diffuser;
A through hole through which the thermocouple is inserted through the vehicle compartment;
A terminal head that is installed outside the passenger compartment and presses the thermocouple tip to contact the tip of the protective tube;
Equipped with a,
The protective tube is
Both ends are openings, and a pipe body that is supported and fixed to the outer wall surface of the diffuser on the passenger compartment side and extends into the diffuser,
A well that is installed at the tip of the diffuser inside the tube body and is in contact with the tip of the thermocouple;
A fixing member for fixing the well to the tube body;
With
The fixing member has a ring shape in which an L-shaped cross section is continuous in a circumferential shape,
The tip end surface of the tube body inside the diffuser is in contact with the first end surface of the well that is in contact with the thermocouple, and the side surfaces of the tube body and the well and the first end surface opposite to the first end surface of the well. The temperature measuring device is characterized in that the well is fixed to the tip of the tube main body by contacting two end surfaces with the inner wall surface of the fixing member . Before Symbol By the tip of the thermocouple is fixed to the well in contact with the said tube body, the temperature measuring device according to claim 1, characterized in that to fix the position of the tip of the thermocouple inside the diffuser . The pipe body penetrates the outer wall on the passenger compartment side of the diffuser and is fixed at a contact portion with the outer wall surface on the passenger compartment side of the diffuser, thereby connecting the diffuser inside and the diffuser outside. temperature measuring device according to claim 1 or claim 2, characterized in that sealing. At the tip end portion of the outer wall surface of the diffuser of the tube body, according to any one of claims 1 to 3 in which the inner wall surface and wherein the toward the tip a shape that the opening area becomes larger Temperature measuring device. The temperature measuring device according to claim 4 , wherein an inner wall surface of the tube body has a curved surface shape that smoothly changes toward the tip at a tip end portion of the diffuser on the outer wall surface side of the diffuser. In the thermocouple, any claims 1 to 3, characterized in that the coating by coating the curable material for the portion corresponding to the tip end position near the outer wall surface side of the diffuser of the tube body The temperature measuring device according to crab. Detecting a combustion state of the combustor based on a temperature measurement value of the combustion gas that has passed through the turbine main body and obtained by being measured by the temperature measuring device according to any one of claims 1 to 6. A characteristic combustion monitoring device. A combustion monitoring device according to claim 7 ;
Based on the combustion state of the combustor confirmed by the combustion monitoring device, a control unit that performs control of the flow rate of fuel supplied to the combustor and emergency stop control of the gas turbine main body,
A gas turbine comprising:

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