Combustion pressure measurement device and combustion engine including the same gas turbine

Abstract

The present invention provides a combustion dynamic pressure measuring device for measuring the combustion dynamic pressure inside a combustor of a gas turbine, comprising: a measuring tip portion disposed in the combustion space of the combustor and having a combustion air passage formed therein; and a measuring portion for measuring the combustion dynamic pressure of combustion air supplied through the combustion air passage of the measuring tip portion, wherein a plurality of cooling lines are formed in the measuring tip portion to reduce thermal damage to the measuring tip portion, and a combustor and a gas turbine including the same.

Description

Technology Field

[0001] The present invention relates to a combustion dynamic pressure measuring device, a combustor equipped with the same, and a gas turbine. More specifically, it relates to a combustion dynamic pressure measuring device installed in a combustor of a gas turbine to measure the combustion dynamic pressure inside the combustor, and a combustor equipped with the same and a gas turbine. Background Technology

[0002] Generally, a gas turbine is a rotary power engine that extracts energy from the flow of combustion air, and consists of a compressor, a turbine, and a combustor.

[0003] In other words, the gas turbine is configured to drive the turbine by utilizing the force generated when air compressed by a compressor is mixed with fuel and combusted in the combustion chamber, thereby expanding the high-temperature, high-pressure gas; among these components, monitoring the combustion state in the combustion chamber is crucial for ensuring the stability and reliability of the equipment.

[0004] If the combustion state becomes unstable due to reasons such as poor fuel supply to the combustion chamber, and the dynamic pressure inside the combustor increases or resonates with the combustor components, it is dangerous as it can not only shorten the lifespan of the combustor but also cause significant mechanical damage.

[0005] Furthermore, since combustion instability negatively impacts the reliability of the combustion system along with issues such as noise and vibration, and can also cause structural problems due to excessive heat transfer and high combustion dynamic pressure, it is crucial to prevent combustion instability.

[0006] Continuously measuring the dynamic combustion pressure in a combustion chamber not only allows for the early detection and response to signs of combustion instability but is also useful in the tuning process to find optimal operating conditions. Consequently, devices and methods utilizing sensors such as piezoelectric elements to measure the dynamic pressure generated inside a combustion chamber have been in use for some time; an example of this is a method of measuring pressure by attaching a dynamic pressure sensor to the combustion chamber.

[0007] However, the above-mentioned conventional technology had a problem in that the operating conditions became high temperature and high pressure due to the heat transferred from the combustion chamber during operation, which made it easy for the sensor to be damaged, resulting in a short replacement cycle for the expensive high-temperature sensor and high maintenance costs, and the reliability of dynamic pressure measurement was reduced because replacement during operation was impossible in the event of sensor failure.

[0008] To solve the aforementioned problems, a device is used that manufactures a dynamic pressure measuring probe and additionally installs a sensing line to measure the dynamic pressure of a combustion chamber. This device is configured to insert a tube-shaped measuring tip into the combustion chamber casing to extract and measure the internal dynamic pressure of the combustion chamber.

[0009] As prior art, Korean Registered Patent Publication No. 10-1219243 discloses a combustion dynamic pressure measuring device, the technical configuration of which is characterized by comprising a wave guide connected to a combustor to extract combustion dynamic pressure, a measuring unit including a dynamic pressure sensor connected to the wave guide to measure combustion dynamic pressure and then convert it into an electrical signal and transmit it to a data storage unit, a damping coil connected to the wave guide to attenuate combustion dynamic pressure, and a purging unit for periodically purging condensation generated in the wave guide and the damping coil.

[0010] In other words, the aforementioned prior art is characterized by being configured to measure combustion dynamic pressure using a low-temperature dynamic pressure sensor by periodically purging the condensate generated by combustion and compensating the measured combustion dynamic pressure value in correspondence with the length of the wave guide and the frequency of the combustion dynamic pressure; however, since the end of the wave guide connected to the combustion unit to extract the combustion dynamic pressure is similarly exposed to the high-temperature part of the combustion unit, there is a high risk of failure or deformation, and consequently, there is a problem in that the reliability of the dynamic pressure measurement is reduced. The problem to be solved

[0011] The present invention was created to solve the above-mentioned problems and aims to provide a combustion dynamic pressure measuring device installed in a combustor of a gas turbine that can measure the combustion dynamic pressure inside the combustor using a measuring tip and a measuring part, and in which a plurality of cooling lines are formed in the measuring tip to prevent one end of the measuring tip from melting due to the high temperature of the combustor, as well as a combustor and a gas turbine equipped with the same. means of solving the problem

[0012] To achieve the above objective, the present invention provides a combustion dynamic pressure measuring device for measuring the combustion dynamic pressure inside a combustor of a gas turbine, comprising: a measuring tip portion disposed in the combustion space of the combustor and having a combustion air passage formed therein; and a measuring portion for measuring the combustion dynamic pressure of combustion air supplied through the combustion air passage of the measuring tip portion, wherein a plurality of cooling lines are formed in the measuring tip portion to reduce thermal damage to the measuring tip portion.

[0013] In a combustion dynamic pressure measuring device according to the present invention, the measuring tip portion may include a measuring tip tube having one end disposed in the combustion space and the other end disposed outside the nozzle casing of the combustion device and having a combustion air passage formed inside; a positioning member provided outside the end of the measuring tip tube to limit the position of the end of the measuring tip tube that is introduced into the interior of the combustion device; and a support member coupled to the outside of the measuring tip tube spaced apart from the positioning member, in close contact with the combustion device casing, and supporting the measuring tip tube, and the plurality of cooling lines may be formed in the positioning member.

[0014] The above measuring tip may be a hollow tube, and the above positioned member may have a cylindrical shape, and at one end of the above positioned member that is in close contact with the liner of the combustion device, an inclined end may be formed at an angle toward the measuring tip tube side from the circumferential surface of the above positioned member, and a plurality of cooling lines may be formed concavely inwardly on the circumferential surface of the above positioned member and the inclined end.

[0015] The periphery of the above-mentioned fixed member may include a first section formed on the upstream side of the combustion air and a second section formed on the downstream side of the combustion air, and a plurality of cooling lines may be formed in the second section.

[0016] The first section above may have a central angle of 31 to 95 degrees with respect to the center of the positioned member.

[0017] Six cooling lines may be formed in the second section above, and each cooling line may have a semicircular shape, and the radius of the cooling line may be 2.0 mm or more and 3.0 mm or less.

[0018] The above cooling line may be formed by extending from the above-located fixed member to the above-located inclined section, and the cooling line formed on the above-located inclined section may be 6 to 22 degrees from the axial direction.

[0019] The angle between one of the six cooling lines formed in the second section and an adjacent cooling line may have one angle selected from 35° to 40°.

[0020] The above cooling line may be coated with chromium carbide, a compound composed of chromium and carbon, and the above-mentioned fixed member may be a heat-resistant material.

[0021] The combustion dynamic pressure measuring device according to the present invention may further include a damping unit that connects the measuring tip unit and the measuring unit and attenuates the combustion dynamic pressure of combustion air supplied to the measuring unit, and a data processing unit that is connected to the measuring unit and analyzes the data of the combustion dynamic pressure measured by the measuring unit to evaluate the operating state of the combustor and identify an abnormal state.

[0022] In addition, the present invention provides a combustor that mixes compressed air supplied from a compressor of a gas turbine with fuel and combusts it, and supplies the generated combustion air to the turbine of the gas turbine, comprising: a nozzle casing; a liner connected to the turbine-side end of the nozzle casing and having a combustion space formed therein in which a mixture of fuel and compressed air is combusted; a transition piece connected to the turbine-side end of the liner and supplying the combustion air generated in the combustion space to the turbine; and a nozzle assembly installed inside the nozzle casing and injecting fuel and compressed air into the combustion space, wherein the combustor is equipped with a combustion dynamic pressure measuring device for measuring the combustion dynamic pressure inside the combustor, and the combustion dynamic pressure measuring device comprises a measuring tip portion disposed in the combustion space of the combustor and having a combustion air passage formed therein, and a measuring portion for measuring the combustion dynamic pressure of the combustion air supplied through the combustion air passage of the measuring tip portion, wherein a plurality of cooling lines are formed in the measuring tip portion to reduce thermal damage to the measuring tip portion.

[0023] In addition, the present invention comprises a compressor that compresses air introduced from the outside; a combustor that mixes compressed air supplied from the compressor with fuel and burns it; and a turbine that passes combustion air supplied from the combustor through its interior to generate power for electricity generation, wherein the combustor comprises a nozzle casing; a liner connected to the turbine-side end of the nozzle casing and having a combustion space formed therein where a mixture of fuel and compressed air is burned; and a transition piece connected to the turbine-side end of the liner and supplying combustion air generated in the combustion space to the turbine. The present invention provides a gas turbine comprising a nozzle assembly installed inside the nozzle casing and injecting fuel and compressed air into the combustion space, wherein the combustion chamber is equipped with a combustion dynamic pressure measuring device for measuring the combustion dynamic pressure inside the combustion chamber, and the combustion dynamic pressure measuring device is disposed in the combustion space of the combustion chamber and includes a measuring tip portion having a combustion air passage formed therein and a measuring portion for measuring the combustion dynamic pressure of the combustion air supplied through the combustion air passage of the measuring tip portion, wherein a plurality of cooling lines are formed in the measuring tip portion to reduce thermal damage to the measuring tip portion. Effects of the invention

[0024] According to the combustion dynamic pressure measuring device of the present invention and the combustor and gas turbine equipped therewith, the combustion dynamic pressure inside the combustor can be measured using a measuring tip portion and a measuring portion, and a plurality of cooling lines are formed in the measuring tip portion to prevent one end of the measuring tip portion from melting due to the high temperature of the combustor. Brief explanation of the drawing

[0025] FIG. 1 is a schematic diagram illustrating a gas turbine according to the present invention. Figure 2 is a cutaway perspective view of the combustion device shown in Figure 1. FIG. 3 is a schematic diagram illustrating a combustion dynamic pressure measuring device installed in the combustion device shown in FIG. 2 to measure the combustion dynamic pressure inside the combustion device. Figure 4 is a schematic diagram showing the state in which the combustion dynamic pressure measuring device illustrated in Figure 3 is installed in a combustion chamber. Figure 5 is an enlarged view of the measuring tip portion shown in Figure 4. Figure 6 is a side view of the measuring tip portion shown in Figure 5. FIG. 7 is a schematic diagram illustrating a combustion dynamic pressure measuring device with an example of deformation of the damping section. Specific details for implementing the invention

[0026] Hereinafter, preferred embodiments according to the present invention will be described in detail with reference to the attached drawings. Prior to this, terms and words used in this specification and claims should not be interpreted as being limited to their ordinary or dictionary meanings, and should be interpreted in a meaning and concept consistent with the technical spirit of the present invention, based on the principle that the inventor can appropriately define the concept of the terms to best describe his invention.

[0027] Referring to FIG. 1, the gas turbine (100) includes a compressor (110), a combustor (1000), and a turbine (120). Based on the flow direction of the gas (compressed air or combustion air), the compressor (110) is positioned on the upstream side of the gas turbine (100) and the turbine (120) is positioned on the downstream side, and the combustor (1000) is positioned between the compressor (110) and the turbine (120).

[0028] The compressor (110) accommodates compressor vanes and a compressor rotor inside a compressor casing, and the turbine (120) accommodates turbine vanes and a turbine rotor inside a turbine casing. These compressor vanes and a compressor rotor are arranged in a multi-stage configuration along the direction of compressed air flow, and the turbine vanes and a turbine rotor are also arranged in a multi-stage configuration along the direction of combustion air flow. At this time, the internal space of the compressor (110) decreases from the front stage to the rear stage so that the sucked air can be compressed, while conversely, the internal space of the turbine (120) increases from the front stage to the rear stage so that the combustion air supplied from the combustor (1000) can be expanded.

[0029] Meanwhile, between the compressor rotor located at the rear end of the compressor (110) and the turbine rotor located at the front end of the turbine (120), a torque member is disposed as a torque transmission member that transmits rotational torque generated in the turbine (120) to the compressor (110). The torque member may be composed of a plurality of torque tube discs consisting of a total of three stages, but is not limited thereto, and the torque tube may be composed of a plurality of torque tube discs consisting of four or more stages or two or fewer stages.

[0030] The compressor rotor comprises a compressor disc and a compressor blade. A plurality of compressor discs (e.g., 14 discs) are provided inside the compressor casing, and each of the compressor discs is connected by a tie rod so as not to be separated in the axial direction. More specifically, each of the compressor discs is aligned along the axial direction with its center penetrated by the tie rod. Adjacent compressor discs are positioned so that their opposing surfaces are compressed by the tie rod, thereby preventing relative rotation between them.

[0031] A plurality of compressor blades are radially coupled to the outer surface of the compressor disk. Additionally, between the compressor blades, a plurality of compressor vanes are arranged in an annular manner on the inner surface of the compressor casing based on the same stage. Unlike the compressor disk, the compressor vanes remain in a fixed state so as not to rotate and serve to align the flow of compressed air passing through the compressor blades and guide the compressed air to the compressor blades located downstream. At this time, the compressor casing and the compressor vanes may be defined by the comprehensive name "compressor stator" to distinguish them from the compressor rotor.

[0032] The compressor stator further includes a compressor inlet scroll strut in addition to the compressor casing and compressor vanes. The compressor inlet scroll strut is connected to the front end of the compressor casing and guides external air to the inlet of the compressor casing. Meanwhile, among the compressor vanes, the one located at the front end is called an inlet guide vane. The inlet guide vane serves to guide the air flowing into the compressor casing to the compressor blades and compressor vanes located at the rear end.

[0033] The tie rod is positioned to penetrate the center of the plurality of compressor discs and the turbine disc to be described later, and one end is fastened within the compressor disc located at the foremost end of the compressor (110), and the other end is fastened by a fixing nut.

[0034] Since the shape of the tie rod above can be formed in various structures depending on the gas turbine, it is not necessarily limited to the shape shown in FIG. 1. That is, as illustrated, it may have a shape in which a single tie rod penetrates the central part of the compressor disk and the turbine disk, or a shape in which multiple tie rods are arranged circumferentially, and a combination of these is also possible.

[0035] Although not shown, a deswirler acting as a guide vane may be installed in the compressor (110) of the gas turbine (100) to adjust the flow angle of the fluid entering the combustor (1000) inlet to the design flow angle after increasing the fluid pressure.

[0036] The high-temperature, high-pressure combustion air from the above-described combustor (1000) is supplied to the turbine (120) described above. The high-temperature, high-pressure combustion air supplied to the turbine (120) expands as it passes through the interior of the turbine (120), thereby applying impulse and reaction forces to the turbine blades described later, causing rotational torque to be generated. The rotational torque obtained in this way is transmitted to the compressor (110) via the torque tube described above, and any portion exceeding the power required to drive the compressor (110) is used to drive a generator, etc.

[0037] The turbine (120) is basically similar in structure to the compressor (110). That is, the turbine (120) is also equipped with a plurality of turbine rotors similar to the compressor rotors of the compressor (110). Accordingly, the turbine rotor also includes a turbine disk and a plurality of turbine blades arranged radially therefrom. Between the turbine blades, a plurality of turbine vanes are provided, which are installed in an annular manner on the turbine casing based on the same stage, and the turbine vanes guide the flow direction of the combustion air passing through the turbine blades. At this time, the turbine casing and the turbine vanes may also be defined by the comprehensive name of a turbine stator to distinguish them from the turbine rotor.

[0038] Referring to FIGS. 1 and 2, a combustor (1000) according to the present invention comprises a nozzle casing (1100), a liner (1200), a transition piece (1300), and a nozzle assembly (1400). The nozzle casing (1100) is formed in a hollow cylindrical shape, and fuel is introduced from the outside. The nozzle casing (1100) is provided with a casing head (not shown), and the casing head (not shown) covers the nozzle casing (1100) at the front of the nozzle casing (1100). The liner (1200) is disposed inside the nozzle casing (1100) and is formed in a hollow cylindrical shape. Compressed air moves from the rear to the front between the liner (1200) and the nozzle casing (1100), and fuel and compressed air are injected into the interior through the front.

[0039] And as the mixture of fuel and compressed air injected into the interior of the liner (1200) burns, high-temperature, high-pressure flames and combustion air are generated. Here, the space where combustion takes place inside the liner (1200) is called the combustion space (1210). A liner head (not shown) is installed at the front of the liner (1200), and the liner head (not shown) mixes the supplied fuel and compressed air and supplies them into the interior of the liner (1200).

[0040] A transition piece (1300) is connected to the turbine (120) side end of the liner (1200), and the transition piece (1300) supplies combustion air generated in the combustion chamber (1210) to the turbine (120). The transition piece (1300) has an annular flow path formed that surrounds the internal space of the transition piece (1300), and the outer wall is cooled by compressed air flowing along the annular flow path of the transition piece to prevent damage caused by the high temperature of the combustion air.

[0041] A nozzle assembly (1400) is installed inside the nozzle casing (1100), more specifically in the liner head (not shown), and the nozzle assembly (1400) mixes fuel and compressed air and injects them into the combustion space (1210).

[0042] The nozzle assembly (1400) is installed in a structure in which one nozzle group is positioned at the center of the nozzle casing (1100), and the remaining multiple nozzle groups surround the nozzle group at the center from the radial outer side.

[0043] Referring to FIGS. 2 to 6, the combustion device (1000) is equipped with a combustion dynamic pressure measuring device (2000) for measuring the combustion dynamic pressure inside the combustion device (1000), and the combustion dynamic pressure measuring device (2000) includes a measuring tip part (2100) and a measuring part (2200), and may further include a damping part (2300) and a data processing part (2400).

[0044] Referring to FIGS. 2, 3, and 5, one end of the measuring tip portion (2100) is positioned in the combustion space (1210) of the combustor (1000), and a combustion air passage (2110a) through which combustion air within the combustion space (1210) moves is formed inside the measuring tip portion (2100). The measuring portion (2200) is connected to the measuring tip portion (2100), and the measuring portion (2200) serves to measure the combustion dynamic pressure of the combustion air supplied through the combustion air passage (2110a) of the measuring tip portion (2100).

[0045] The measuring tip portion (2100), which is positioned at one end in the combustion space (1210), includes a measuring tip tube (2110), a positioning member (2120), and a supporting member (2130), and a plurality of cooling lines (CL) are formed in the measuring tip portion (2100) to reduce heat damage to the measuring tip portion (2100) caused by the high temperature of the combustion device (1000).

[0046] The above measuring tip tube (2110) is a hollow tube, one end of the measuring tip tube (2110) is placed in the combustion space (1210) and the other end is placed outside the nozzle casing (1100), and the combustion air passage (2110a) is formed inside the measuring tip tube (2110).

[0047] A positioning member (2120) is provided on the outer side of one end of the above measuring tip tube (2110), and the positioning member (2120) serves to limit the position of one end of the above measuring tip tube (2110) that is introduced into the interior of the combustion device (1000), and the positioning member (2120) has a cylindrical shape, and the plurality of cooling lines (CL) are formed in the positioning member (2120).

[0048] Referring to FIGS. 2 and 4, a support member (2130) is provided on the outer side of the measuring tip tube (2110) so as to be spaced apart from the positioned member (2120), and the support member (2130) is coupled to the outer side of the measuring tip tube (2110) and is in close contact with the nozzle casing (1100) to support the measuring tip tube (2110).

[0049] Referring to FIGS. 4 to 6, an inclined section (2121) is formed at one end of the positioned member (2120) that is in close contact with the liner (1200) of the combustion device (1000). The inclined section (2121) is formed at an angle toward the measuring tip tube (2110) from the circumferential surface of the positioned member (2120), and a plurality of cooling lines (CL) are formed inwardly concavely on the circumferential surface of the positioned member (2120) and the inclined section (2121).

[0050] The periphery of the above-mentioned positional member (2120) includes a first section (2120a) and a second section (2120b), wherein the first section (2120a) is formed on the periphery of the above-mentioned positional member (2120) which is positioned upstream of the combustion air when the above-mentioned positional member (2120) is in close contact with the liner (1200), and the second section (2120b) is formed on the periphery of the above-mentioned positional member (2120) which is positioned downstream of the combustion air, and it is preferable that the plurality of cooling lines (CL) are formed in the second section (2120b).

[0051] The first section (2120a) formed on the circumferential surface of the above-mentioned fixed member (2120) has a central angle of 31 to 95 degrees with respect to the center of the above-mentioned fixed member (2120), and six cooling lines (CL) are formed in the second section (2120b).

[0052] If the center angle of the first section (2120a) is 31 degrees or less relative to the center of the positioned member (2120), there is a problem such as an increased possibility of acquiring error data due to interference with the cooling air, and if the center angle of the first section (2120a) is 95 degrees or more relative to the center of the positioned member (2120), there is a problem of insufficient cooling.

[0053] Each of the six cooling lines (CL) formed in the second section (2120b) has a semicircular shape, and it is preferable that the radius of the cooling line (CL) is 2.0 mm or more and 3.0 mm or less.

[0054] The above cooling line (CL) is coated with chromium carbide, a compound composed of chromium and carbon, and the above positioning member (2120) is preferably made of a heat-resistant material. As the chromium carbide is coated on the cooling line (CL), the durability of the cooling line (CL) can be improved in high-temperature, high-wear, and high-corrosion environments.

[0055] The above-mentioned positional member (2120) is formed of a heat-resistant material, and a plurality of cooling lines (CL) are formed in the second section (2120b) of the above-mentioned positional member (2120). Since the plurality of cooling lines (CL) are formed only on the downstream side of the combustion air, the formation of vortices is suppressed to improve the reliability of dynamic pressure, and the air moving through the plurality of cooling lines (CL) is used to cool one end of the measuring tip tube (2110) inserted into the above-mentioned positional member (2120) and the liner (1200), thereby preventing the phenomenon of melting due to the high temperature of the combustion device.

[0056] The cooling line (CL) is formed by extending from the positioned member (2120) to the inclined section (2121), and the cooling line (CL) formed on the inclined section (2121) is preferably 6 to 22 degrees from the axial direction.

[0057] If the above cooling line (CL) is 6 degrees or less from the axial direction, it has problems such as the possibility of obtaining incorrect information, and if the above cooling line (CL) is 22 degrees or more, it has problems such as a decrease in cooling flow rate.

[0058] It is preferable that the angle between one of the six cooling lines (CL) formed in the second section (2120) of the above-mentioned fixed member (2120) and the adjacent cooling line (CL) be one angle selected from 35° to 40°.

[0059] The angle between one of the six cooling lines (CL) formed in the second section (2120) and the adjacent cooling line (CL) is 35° to 40°, so that the six cooling lines (CL) in the second section (2120) are spaced apart at a uniform angle.

[0060] Referring to FIGS. 2 to 4, the measuring tip portion (2100) and the measuring portion (2200) are connected by a damping portion (2300), and the damping portion (2300) serves to dampen the combustion dynamic pressure of the combustion air supplied to the measuring portion (2200).

[0061] The above measuring unit (2200) is connected to the data processing unit (2400), and the data processing unit (2400) analyzes the combustion dynamic pressure data measured by the measuring unit (2200) to evaluate the operating state of the combustor (1000) and check for abnormal conditions.

[0062] Referring to FIG. 7, the measuring tip portion (2100) and the measuring portion (2200) can be connected by a damping portion (2300') having a coil shape, and because the damping portion (2300') has a coil shape, internal moisture contained in the combustion air supplied to the measuring portion (2200) can be smoothly removed. Since internal moisture can be smoothly removed by the damping portion (2300'), the combustion dynamic pressure can be accurately measured.

[0063] Accordingly, the combustion dynamic pressure inside the combustion chamber (1000) can be measured using a measuring tip portion (2100) and a measuring portion (2200), and a plurality of cooling lines (CL) are formed in the measuring tip portion (2100) to prevent one end of the measuring tip portion (2100) from melting due to the high temperature of the combustion chamber (1000).

[0064] The present invention has been described with reference to embodiments illustrated in the drawings, but this is merely illustrative, and those skilled in the art will understand that various modifications and equivalent alternative embodiments are possible therefrom. Accordingly, the true technical scope of protection of the present invention should be determined by the technical spirit of the appended claims. Explanation of the symbols

[0065] 100 : Gas turbine 110 : Compressor 120 : Turbine 1000 : Combustion device 1100 : Nozzle casing 1200 : Liner 1210 : Combustion space 1300 : Transition Piece 1400: Nozzle assembly 2000 : Combustion dynamic pressure measuring device 2100 : Measuring tip section 2110 : Measuring tip tube 2120 : Located government property 2130 : Support member 2200 : Measurement section 2300 : Attenuation section 2400 : Data processing unit

Claims

Claim 1 A combustion dynamic pressure measuring device for measuring the combustion dynamic pressure inside a combustor of a gas turbine, comprising: a measuring tip portion disposed in the combustion space of the combustor and having a combustion air passage formed therein; and a measuring portion for measuring the combustion dynamic pressure of combustion air supplied through the combustion air passage of the measuring tip portion, wherein a plurality of cooling lines are formed in the measuring tip portion to reduce heat damage to the measuring tip portion. Claim 2 A combustion dynamic pressure measuring device according to claim 1, wherein the measuring tip portion comprises: a measuring tip tube having one end disposed in the combustion space and the other end disposed outside the nozzle casing of the combustion device and having a combustion air passage formed inside; a positioning member provided outside the end of the measuring tip tube to limit the position of the end of the measuring tip tube that is introduced into the interior of the combustion device; and a support member coupled to the outside of the measuring tip tube spaced apart from the positioning member, in close contact with the nozzle casing, and supporting the measuring tip tube, wherein the plurality of cooling lines are formed in the positioning member. Claim 3 A combustion dynamic pressure measuring device according to claim 2, wherein the measuring tip tube is a hollow tube, the positioned member has a cylindrical shape, and at one end of the positioned member that is in close contact with the liner of the combustion device, an inclined end is formed inclined toward the measuring tip tube side from the circumferential surface of the positioned member, and a plurality of cooling lines are formed inwardly concavely on the circumferential surface of the positioned member and the inclined end. Claim 4 A combustion dynamic pressure measuring device according to claim 3, wherein the circumferential surface of the positioned member comprises a first section formed on the upstream side of the combustion air and a second section formed on the downstream side of the combustion air, and wherein a plurality of cooling lines are formed in the second section. Claim 5 A combustion dynamic pressure measuring device according to claim 4, wherein the first section has a central angle of 31 to 95 degrees with respect to the center of the positioned member. Claim 6 A combustion dynamic pressure measuring device according to claim 5, characterized in that six cooling lines are formed in the second section, each cooling line has a semicircular shape, and the radius of the cooling line is 2.0 mm or more and 3.0 mm or less. Claim 7 A combustion dynamic pressure measuring device according to claim 6, wherein the cooling line is formed by extending from the positioned fixed member to the inclined section, and the cooling line formed at the inclined section is 6 to 22 degrees from the axial direction. Claim 8 A combustion dynamic pressure measuring device according to claim 6, characterized in that the angle between one of the six cooling lines formed in the second section and an adjacent cooling line has one angle selected from 35° to 40°. Claim 9 A combustion dynamic pressure measuring device according to claim 8, characterized in that the cooling line is coated with chromium carbide, which is a compound composed of chromium and carbon, and the positioned member is made of a heat-resistant material. Claim 10 A combustion dynamic pressure measuring device according to claim 1, further comprising a damping part that connects the measuring tip part and the measuring part and dampens the combustion dynamic pressure of combustion air supplied to the measuring part. Claim 11 A combustion dynamic pressure measuring device according to claim 10, further comprising a data processing unit connected to the measuring unit, which analyzes data of the combustion dynamic pressure measured by the measuring unit to evaluate the operating state of the combustor and identify an abnormal state. Claim 12 A combustor that mixes compressed air supplied from a compressor of a gas turbine with fuel and combusts it, and supplies the generated combustion air to the turbine of a gas turbine, comprising: a nozzle casing; a liner connected to the turbine-side end of the nozzle casing and having a combustion space formed therein in which a mixture of fuel and compressed air is combusted; a transition piece connected to the turbine-side end of the liner and supplying the combustion air generated in the combustion space to the turbine; and a nozzle assembly installed inside the nozzle casing and injecting fuel and compressed air into the combustion space, wherein the combustor is provided with a combustion dynamic pressure measuring device for measuring the combustion dynamic pressure inside the combustor, and the combustion dynamic pressure measuring device comprises a measuring tip portion disposed in the combustion space of the combustor and having a combustion air passage formed therein, and a measuring portion for measuring the combustion dynamic pressure of the combustion air supplied through the combustion air passage of the measuring tip portion, wherein a plurality of cooling lines are formed in the measuring tip portion to reduce heat damage to the measuring tip portion. Claim 13 In claim 12, the measuring tip portion comprises: a measuring tip tube having one end disposed in the combustion space and the other end disposed outside the nozzle casing, with the combustion air passage formed inside; a positioning member provided outside the end of the measuring tip tube to limit the position of the end of the measuring tip tube that is introduced into the interior of the combustor; and a support member coupled to the outside of the measuring tip tube spaced apart from the positioning member, in close contact with the nozzle casing, and supporting the measuring tip tube; wherein the plurality of cooling lines are formed in the positioning member, the measuring tip tube is a hollow tube, the positioning member has a cylindrical shape, and at one end of the positioning member that is in close contact with the liner of the combustor, an inclined end is formed inclined in the direction toward the measuring tip tube from the circumferential surface of the positioning member, and a plurality of cooling lines are formed concavely inwardly on the circumferential surface of the positioning member and the inclined end. Claim 14 A combustor according to claim 13, wherein the periphery surface of the positioned member comprises a first section formed on the upstream side of the combustion air and a second section formed on the downstream side of the combustion air, wherein a plurality of cooling lines are formed in the second section, wherein the first section has a central angle of 31 to 95 degrees with respect to the center of the positioned member, wherein six cooling lines are formed in the second section, wherein each cooling line has a semicircular shape, and the radius of the cooling line is 2.0 mm or more and 3.0 mm or less. Claim 15 A combustor according to claim 14, wherein the cooling line is formed by extending from the positioned member to the inclined section, the cooling line formed on the inclined section is 6 to 22 degrees from the axial direction, the angle between one of the six cooling lines formed in the second section and an adjacent cooling line is one angle selected from 35° to 40°, the cooling line is coated with chromium carbide, which is a compound composed of chromium and carbon, and the positioned member is a heat-resistant material. Claim 16 A combustor according to claim 12, further comprising: a damping unit connecting the measuring tip unit and the measuring unit and damping the combustion dynamic pressure of combustion air supplied to the measuring unit; and a data processing unit connected to the measuring unit and analyzing data of the combustion dynamic pressure measured by the measuring unit to evaluate the operating state of the combustor and identify an abnormal state. Claim 17 A compressor for compressing air introduced from the outside; a combustor for mixing compressed air supplied from the compressor with fuel and burning it; and a turbine for generating power for electricity generation by passing combustion air supplied from the combustor through its interior, wherein the combustor comprises: a nozzle casing; a liner connected to the turbine-side end of the nozzle casing, having a combustion space formed therein where a mixture of fuel and compressed air is burned; and a transition piece connected to the turbine-side end of the liner, supplying combustion air generated in the combustion space to the turbine. A gas turbine comprising a nozzle assembly installed inside the nozzle casing and injecting fuel and compressed air into the combustion space, wherein the combustion chamber is equipped with a combustion dynamic pressure measuring device for measuring the combustion dynamic pressure inside the combustion chamber, and the combustion dynamic pressure measuring device comprises a measuring tip portion disposed in the combustion space of the combustion chamber and having a combustion air passage formed therein, and a measuring portion for measuring the combustion dynamic pressure of the combustion air supplied through the combustion air passage of the measuring tip portion, wherein a plurality of cooling lines are formed in the measuring tip portion to reduce thermal damage to the measuring tip portion. Claim 18 In claim 17, the measuring tip portion comprises: a measuring tip tube having one end disposed in the combustion space and the other end disposed outside the nozzle casing, with the combustion air passage formed inside; a positioning member provided outside the end of the measuring tip tube to define the position of the end of the measuring tip tube that is introduced into the interior of the combustor; and a support member coupled to the outside of the measuring tip tube spaced apart from the positioning member, in close contact with the nozzle casing, and supporting the measuring tip tube; wherein the plurality of cooling lines are formed in the positioning member, the measuring tip tube is a hollow tube, the positioning member has a cylindrical shape, and at one end of the positioning member that is in close contact with the liner of the combustor, an inclined end is formed on the circumferential surface of the positioning member in a direction toward the measuring tip tube, and a plurality of cooling lines are formed concavely inwardly on the circumferential surface of the positioning member and the inclined end, and the circumferential surface of the positioning member comprises a first section formed upstream of the combustion air and the combustion air A gas turbine characterized by including a second section formed on the downstream side, wherein a plurality of cooling lines are formed in the second section, wherein the first section has a center angle of 31 to 95 degrees with respect to the center of the positioned member, wherein six cooling lines are formed in the second section, wherein each cooling line has a semicircular shape, and wherein the radius of the cooling line is 2.0 mm or more and 3.0 mm or less. Claim 19 A gas turbine according to claim 18, wherein the cooling line is formed by extending from the positioned upper member to the inclined section, the cooling line formed at the inclined section is 6° to 22° with respect to the axial direction, the angle between one of the six cooling lines formed in the second section and an adjacent cooling line is one angle selected from 35° to 40°, the cooling line is coated with chromium carbide, which is a compound composed of chromium and carbon, and the positioned upper member is made of a heat-resistant material. Claim 20 A gas turbine according to claim 17, further comprising: a damping unit connecting the measuring tip unit and the measuring unit and damping the combustion dynamic pressure of the combustion air supplied to the measuring unit; and a data processing unit connected to the measuring unit and analyzing data of the combustion dynamic pressure measured by the measuring unit to evaluate the operating state of the combustor and identify an abnormal state.

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