KR102580414B1 - Test rig and test system and method for heat resistant test of high-temperature component - Google Patents

Abstract

The present invention provides a test rig for testing the thermal durability of high-temperature components and a test system and method using the same.
The test rig for testing the thermal durability of the high-temperature components is connected to a combustor and has an inlet through which combustion gas flows in, an outlet through which the combustion gas is discharged, and a flow path through which the combustion gas flows in a receiving space provided therein. A housing provided, a test specimen mounting unit provided in the housing, and a test specimen including a vane and a blade installed in a gas turbine are mounted to be disposed on the flow path, and the temperature distribution of the combustion gas inside the housing is adjusted to control the gas Connected to an air compressor that compresses air to simulate the operating environment of a turbine, coupled to the inlet side of the housing, and injecting cooling air, which is unheated compressed air supplied from the air compressor, into the flow path, Includes an air inlet for pattern control.

Description

Test rig for testing thermal durability of high-temperature components and test system and method using the same {TEST RIG AND TEST SYSTEM AND METHOD FOR HEAT RESISTANT TEST OF HIGH-TEMPERATURE COMPONENT}

The present invention relates to a test rig for testing the thermal durability of high-temperature components and a test system and method using the same. More specifically, it relates to a high-temperature test rig for testing the thermal durability of high-temperature components used in gas turbines in an environment similar to the operating environment of an actual gas turbine. This relates to a test rig for testing the thermal durability of components and a test system and method using it.

Combined cycle power generation, which can produce electricity and heat sources simultaneously, consists of a gas turbine, a steam turbine, and a heat recovery array boiler.

A gas turbine is a rotating power machine that burns natural gas in a high-temperature, high-pressure environment to generate combustion gas, and extracts energy by the flow of this combustion gas. A gas turbine includes a compressor, turbine, and combustion chamber. When the air compressed in the compressor mixes with fuel and burns, the high-temperature, high-pressure gas expands, and this power is used to drive the turbine.

The turbine is located after the combustor and includes vanes and blades. Since these vanes and blades are exposed to high-temperature exhaust gases, thermal stress is evaluated before operation to ensure stability during operation. When evaluating the thermal stress of vanes and blades, the reliability of the results can be ensured by exposing the actually used parts to high temperature gas in the same environment.

However, because testing actual components in the same environment is subject to practical limitations, conventionally, test pieces are manufactured separately and the thermal durability of the test pieces is evaluated. In other words, in order to evaluate the component characteristics of gas turbine blades and vanes, small test pieces are separately produced and tested by simulating only temperature conditions similar to the gas turbine environment. According to the conventional method, the evaluation is performed in an environment designed differently from the actual combustion environment of the gas turbine, resulting in difficulties in applying the evaluation results to the field.

The present invention was developed to solve the above-mentioned problems, and is a test rig for thermal durability testing of high-temperature components that improves the reliability of thermal durability testing by installing and testing vanes and blades used in actual gas turbines according to the operating environment of the turbine. The purpose is to provide a test system and method using the same.

In addition, the purpose is to provide a test rig for testing the thermal durability of high-temperature components that can monitor, control, and record test conditions and results in real time, and a test system and method using the same.

In order to achieve the above object, the test rig for testing the thermal durability of high-temperature components according to the present invention is connected to a combustor and has an inlet through which combustion gas flows in, an outlet through which the combustion gas is discharged, and a receiving space provided therein. A housing in which a passage through which the combustion gas flows is provided, a test specimen mounting portion provided in the housing and including a vane and a blade installed in a gas turbine, and mounted to be disposed on the passage, and an interior of the housing. It is connected to an air compressor that compresses air to simulate the operating environment of a gas turbine by controlling the combustion gas temperature distribution, is coupled to the inlet side of the housing, and is unheated compressed air supplied from the air compressor. It includes an air inlet for pattern adjustment that injects cooling air into the flow path.

The thermal durability test system for high-temperature components according to another aspect of the present invention includes an air compressor that compresses air to generate compressed air, the compressed air supplied from the air compressor is heated by an air heater and supplied as fuel, There is a combustor that burns the fuel supplied from the supply unit and generates high-temperature combustion gas, and a flow path connected to a rear end of the combustor and a passage through which the combustion gas flowing in from the combustor flows. On the flow path, A test specimen including vanes and blades installed in a gas turbine is mounted, and cooling air, which is unheated compressed air supplied from the air compressor, is introduced into the flow path to test the thermal durability of the vanes and blades. A test rig, a cooling unit connected to the test rig to cool the air discharged from the test rig, and a combustion temperature distribution inside the test rig to simulate the operating environment of a gas turbine. It may include a control unit that adjusts the pressure and temperature of the incoming combustion gas and cooling air.

The thermal durability test method of high-temperature parts according to another aspect of the present invention includes a compressed air generation step of compressing air through an air compressor to generate compressed air, and the compressed air generated in the compressed air generation step is converted into air. A compressed air heating step of heating to a preset temperature through a heater, supplying the compressed air heated in the compressed air heating step, and fuel supplied from a fuel supply unit to a combustor, and burning the fuel to produce high temperature combustion gas. A combustion gas generation step that generates a combustion gas supply step of supplying the combustion gas generated in the combustion gas generation step to a test rig equipped with vanes and blades installed in a gas turbine, and a combustion gas supply step and Additionally, a cooling air supply step of supplying cooling air, which is unheated compressed air generated by the air compressor, to the test rig to adjust the temperature distribution of the air flowing inside the test rig may be further included.

In this way, the test rig for testing the thermal durability of high-temperature components according to the present invention, unlike the conventional method of separately producing test pieces and performing thermal durability testing, tests by installing and testing vanes and blades used in actual gas turbines according to the operating environment, The reliability of thermal durability tests can be improved.

In addition, according to the present invention, by evaluating vanes and blades by simulating the thermal stress state occurring in an actual gas turbine, limiting factors are minimized when analyzing test results, which has the effect of further improving the usability and reliability of the evaluation results. You can get it.

Additionally, according to the present invention, the flow of combustion gas in a gas turbine can be simulated by adjusting the arrangement of the vanes and blades to the operating environment of the gas turbine.

Additionally, according to the present invention, test conditions and results can be monitored, adjusted, and recorded in real time.

Figure 1 is a perspective view showing a thermal durability test system for high-temperature components according to an embodiment of the present invention.
Figure 2 is a perspective view showing a test rig for testing the thermal durability of high-temperature components according to an embodiment of the present invention.
Figure 3 is a perspective view of Figure 2 viewed from below.
Figure 4 is a side view of Figure 2.
Figure 5 is a diagram showing the shape of a flow path applied to one embodiment of the present invention.
Figure 6 is a perspective view with the top portion of the housing applied to one embodiment of the present invention removed.
Figure 7 is a top view of the lower surface of the housing of Figure 6 as seen from above.
Figure 8 is a side cross-sectional view of the air input portion for pattern adjustment applied to one embodiment of the present invention.
Figure 9 is a partial cross-sectional perspective view of Figure 8;
Figure 10 is a cross-sectional view taken along line II of Figure 8.
Figures 11 (a) to 11 (e) are views showing the assembly process of the vane mounting member applied to one embodiment of the present invention.
Figures 12(a) to 12(d) are views showing the assembly process of the blade mounting member applied to one embodiment of the present invention.
13 is a partially enlarged cross-sectional view showing a temperature sensor according to an embodiment of the present invention.
Figure 14 is a flow chart of a thermal durability test method for high-temperature components according to an embodiment of the present invention.
Figure 15 is a diagram capturing a thermal durability test operation program for high-temperature components according to an embodiment of the present invention.
Figure 16 is a flowchart of a procedure for executing the driving program shown in Figure 15.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings.

First, the examples described below are suitable for understanding the technical characteristics of the test rig for testing the thermal durability of high-temperature components of the present invention and the test system and method using the same. However, the technical features of the present invention are not limited to the embodiments described or applied to the embodiments described below, and various modifications and implementations are possible within the technical scope of the present invention.

First, the thermal durability test system 10 for high-temperature components according to the present invention will be described with reference to the embodiments shown in FIGS. 1 and 15.

1 and 15, the thermal durability test system 10 for high-temperature components according to an embodiment of the present invention includes an air compressor 20, a combustor 50, a test rig 100, and a cooling unit. It includes a unit 60 and a control unit.

The air compressor 20 compresses air and generates compressed air.

In the combustor 50, compressed air supplied from the air compressor 20 is heated and supplied by the air heater 30, and combusts the fuel supplied from the fuel supply unit 40 to generate high temperature combustion gas. do. Specifically, the combustor 50 can combust fuel such as city gas and generate combustion gas at a high temperature (for example, 1000-1300°C).

Here, the combustor 50 and the air compressor 20 can be connected through a pipe equipped with an on-off valve and a control valve, and this pipe is equipped with an air heater 30 to heat the air compressor 20. Compressed air can be heated and supplied to the combustor (50). The air heater 30 can heat compressed air using an electric heater to simulate the air conditions at the end of air compression in an actual gas turbine, and the temperature can be adjusted to enable thermal durability tests according to atmospheric conditions in summer and winter. do. However, the heating method of the air heater 30 is not limited to the above, and various methods may be applied.

The test rig 100 is connected to the rear end of the combustor 50 and is provided with a passage 230 through which combustion gas flowing in from the combustor 50 flows. In addition, a test specimen including vanes 11 and blades 12 installed in a gas turbine is mounted on the flow path 230, and cooling air, which is unheated compressed air supplied from the air compressor 20, is supplied to the flow path. (230) to test the thermal durability of the vane (11) and the blade (12). Here, the vanes 11 and blades 12, which are test chains, may be at least one of the parts used in an actual gas turbine, and may be mounted by simulating the arrangement in an actual gas turbine.

The cooling unit 60 is connected to the test rig 100 and can cool the air discharged from the test rig 100. Specifically, the cooling unit 60 can be started when the entire system is started, and can cool the high-temperature gas discharged after the thermal durability test in the test rig 100 and discharge it to the outside.

Meanwhile, the control unit can control the pressure and temperature of combustion gas and cooling air flowing into the test rig 100 to simulate the operating environment of a gas turbine by adjusting the combustion temperature distribution inside the test rig 100.

Specifically, since the combustion pattern changes according to the actual operating conditions of the gas turbine, the control unit changes the combustion pattern with cooling air, which is unheated compressed air, inside the test rig 100 installed at the rear of the combustor 50. By doing so, the temperature distribution can be controlled to match actual operating conditions.

In this way, the thermal durability test system 10 for high-temperature components includes an air compressor 20, an air heater 30, a fuel supply unit 40, a combustor 50, and a cooling unit ( 60), it is possible to create an actual operating environment for testing the thermal durability of the vane 11 and blade 12, which are high-temperature component test bodies mounted inside the test rig 100.

Specifically, the test rig 100 may include a first temperature sensor 610 that measures the temperature of air flowing inside, and a pressure sensor 700 that measures the pressure of the air inside.

Additionally, the control unit may receive signals from the first temperature sensor 610 and the pressure sensor 700 to adjust the input amounts of combustion gas and cooling air supplied to the test rig 100.

Meanwhile, as in the embodiment shown in FIG. 15, the thermal durability test system 10 for high-temperature components according to the present invention may further include a monitoring unit. The monitoring unit can display the temperature and pressure received from the first temperature sensor 610 and the pressure sensor 700, and record the received temperature and pressure in real time.

Meanwhile, below, with reference to FIGS. 2 to 13, a test rig 100 for testing the thermal durability of high-temperature components according to an embodiment of the present invention will be described.

As shown in FIGS. 2 to 4, the test rig 100 for testing the thermal durability of high-temperature components according to an embodiment of the present invention includes a housing 200, a test specimen mounting portion, and an air inlet portion for pattern adjustment (500). ) includes.

The housing 200 is connected to the combustor 50 and has an inlet 210 through which combustion gas flows in and an outlet 220 through which combustion gas is discharged, and a passage through which combustion gas flows in a receiving space provided therein. A flow path 230 may be provided.

The test specimen mounting unit is provided in the housing 200, and the test specimen including the vanes 11 and blades 12 installed in the gas turbine can be mounted to be disposed on the flow path 230.

Specifically, Figure 5 shows the shape of the flow path 230 provided inside the housing 200. As shown in the illustrated embodiment, the vanes 11 and blades 12 are mounted in communication with each other on the flow path 230 and may contact combustion gas flowing through the flow path 230.

The air input unit 500 for pattern control is connected to an air compressor 20 that compresses air, and may be coupled to the inlet 210 side of the housing 200. Additionally, cooling air, which is unheated compressed air supplied from the air compressor 20, can be introduced into the flow path 230. Accordingly, the pattern control air inlet unit 500 can simulate the operating environment of a gas turbine by controlling the combustion gas temperature distribution inside the housing 200.

Specifically, in an actual gas turbine, the vanes 11 and blades 12 are installed at the rear of the combustor 50 and can receive high-temperature combustion gas. At this time, since the gas turbine changes the thermal stress state of the vanes 11 and blades 12 according to the temperature distribution of the combustion gas, the test rig 100 according to the present invention can also simulate the temperature distribution of the actual combustion gas. There is a need.

Therefore, the pattern control air inlet unit 500 according to the present invention controls the combustion gas temperature distribution inside the housing 200 by injecting cooling air supplied from the air compressor 20 into the passage 230, The operating environment of a gas turbine can be simulated.

In this way, the test rig 100 for testing the thermal durability of high-temperature components according to the present invention, unlike the conventional method of separately producing test pieces and performing thermal durability testing, uses the vanes 11 and blades 12 used in actual gas turbines. By installing and testing according to the operating environment, the reliability of the thermal durability test can be improved.

In addition, according to the present invention, by evaluating the vanes 11 and blades 12 by simulating the thermal stress state occurring in an actual gas turbine, limiting factors are minimized when analyzing the test results, thereby improving the usability and reliability of the evaluation results. The effect of further improving can be obtained.

Specifically, the test specimen mounting unit may further include a vane mounting member 300 and a blade mounting member 400.

The vane mounting member 300 is coupled to the housing 200, and the vane 11 can be mounted thereon. Specifically, the vane mounting member 300 may couple the vane 11 to the housing 200 so that it is disposed on the flow path 230 through which combustion gas flows.

In addition, referring to FIGS. 5 to 7, the blade mounting member 400 is coupled to the housing 200 and the blade 12 is mounted, and the blade 12 is connected to the vane 11 and the flow path 230. It can be installed in communication through. In addition, the blade mounting member 400 is provided to be spaced apart from the vane mounting member 300 in the direction of the outlet 220, and may be provided in a state rotated from the vane mounting member 300 at a preset angle.

In addition, the housing 200 may have a flow path 230 formed in a curved shape to simulate the flow of combustion gas between the vanes 11 and blades 12 in a gas turbine.

Specifically, when the gas turbine is actually operated, the vanes 11 are fixed, and the blades 12 mounted on the turbine rotor can rotate. A plurality of vanes 11 are disposed at a certain angle and can convert thermal energy generated in the combustor 50 into mechanical energy for rotating the rotor and blades 12.

The test specimen mounting unit according to the present invention can arrange a plurality of vanes 11 and blades 12 at angles and spacings applied to an actual gas turbine, unlike conventional tests for thermal durability using separately manufactured test specimens. In addition, the blade mounting member 400 can be provided rotated at a preset angle from the vane mounting member 300 to reflect the operating state of the vanes 11 and blades 12 during gas turbine operation. (See Figure 5).

For example, as shown in the illustrated embodiment, three vanes 11 and eight blades 12 can be arranged at angles and intervals that are actually applied. In addition, boundary conditions are explained and computerized analysis is performed so that the actual operating environment can be simulated with some high-temperature components, and the test specimen can be placed by reflecting the results. However, the number of vanes 11 and blades 12 mounted as a test specimen in the present invention is not limited to the illustrated embodiment and may be applied in various numbers.

Additionally, referring to FIGS. 6 and 7 , the flow path 230 provided in the housing 200 may be formed in a curved shape.

Specifically, the housing 200 may include a lower surface portion 203 that forms the lower surface shape of the flow path 230 and a side surface portion 201 that forms the side surface shape of the flow path 230. Referring to FIG. 6, the blade 12 may be disposed biased to one side with respect to the vane 11, and the side portion 201 is a virtual portion connecting the inlet 210 and the outlet 220 of the housing 200. In the line, the portion on which the blade 12 is mounted may be formed in a curved shape that is biased to one side. Referring to FIG. 7, a vane hole h1 through which the vane 11 is installed and a blade hole h2 through which the blade 12 is installed may be formed through the lower surface 203.

Accordingly, the test rig 100 for testing the thermal durability of high-temperature components can effectively simulate the flow of combustion gas in the turbine when the gas turbine is actually operated. Therefore, limiting factors for analyzing the actual thermal durability of the vanes 11 and blades 12 can be minimized, thereby improving the reliability of test results.

Meanwhile, as in the embodiment shown in FIGS. 8 to 10, the air input unit 500 for pattern adjustment may include a main body 510 and a first cooling air injection pipe 530.

One side of the main body 510 is coupled to the housing 200, the other side is coupled to the combustor 50, and an air passage 511 communicating with the flow path 230 may be provided therein. Specifically, the main body 510 has a housing coupling portion 514 coupled to the inlet 210 side of the housing 200 on one side, and a combustor coupled to the rear end of the combustor 50 on the other side of the main body 510. A coupling portion 514 may be provided.

The first cooling air injection pipe 530 is mounted on the main body 510 in communication with the air passage 511 and is connected to the air compressor 20, so that the cooling air supplied from the air compressor 20 flows through the air passage (511). 511). That is, the first cooling air injection pipe 530 can connect the air passage 511 and the air compressor 20. At this time, the compressed air flowing into the air passage 511 is cooled air that has not passed through the air heater 30, has a lower temperature than the combustion gas flowing into the air passage 511 from the combustor 50, and is a combustion gas. Before flowing into the housing 200, the temperature pattern of the combustion gas can be adjusted and supplied to the flow path 230.

Here, a plurality of first cooling air injection pipes 530 may be installed in the circumferential direction of the main body 510. For example, as shown in FIG. 10, when the pattern control air inlet 500 is viewed from the I-I direction of FIG. 8, there are three first cooling air injection pipes 530 on the upper side of the air passage 511 and three on the lower side. Two can be placed, one on each side.

In this way, cooling air at a uniform pressure flows into the air passage 511 through the plurality of first cooling air injection pipes 530, so that temperature patterns can be easily controlled.

More preferably, the main body 510 may further include a supply slit 540 recessed in the thickness direction on the inner peripheral surface. The supply slits 540 are provided in plural numbers to be connected to each of the plurality of first cooling air injection pipes 530, and may be formed long on the inner peripheral surface of the main body 510.

By using such a plurality of supply slits 540, a large area of the inner peripheral surface of the main body 510 can be subdivided. Therefore, cooling air can be evenly injected into all areas of the air passage 511.

Meanwhile, below, with reference to FIGS. 11 and 12, the vane mounting member 300 and the blade mounting member 400 will be described in detail. Figures 11 (a) to 11 (e) are diagrams showing the process of assembling the vane mounting member 300 and the vane 11. In addition, Figures 12 (a) to 12 (d) are diagrams showing the process of assembling the blade mounting member 400 and the blade 12.

Referring to FIG. 11, the vane mounting member 300 is mounted on the lower surface 203 of the housing 200, and includes a vane lower fixing block 310 to which the lower end of the vane 11 is assembled, and the housing 200. It is mounted on the upper surface of and may include a vane upper fixing block 330 to which the upper end of the vane 11 is assembled.

Specifically, the vane 11 may be installed to penetrate the upper and lower surfaces 203 of the housing 200. In addition, the vane lower fixing block 310 and the vane upper fixing block 330 are coupled to the upper and lower ends of the penetrating vane 11, connect the plurality of vanes 11, and attach the vanes 11 to the housing 200. ) can be combined. At this time, the vane mounting member 300 can detachably assemble the vane 11 to the housing 200. Accordingly, since the vane 11, which is the test chain, can be replaced, various vanes 11 can be tested.

Additionally, the vane mounting member 300 may further include a second cooling air injection pipe 350.

The second cooling air injection pipe 350 is connected to the air compressor 20 and communicates with the inside of the vane 11 to inject the cooling air supplied from the air compressor 20 into the vane 11. The vane can be installed through the upper fixing block 330.

Specifically, the second cooling air injection pipe 350 may communicate with the inside of the vane 11 and the air compressor 20. Accordingly, the cooling air supplied from the air compressor 20 can be introduced into the vane 11 to cool the vane 11. This applies the cooling function of high-temperature components in an actual gas turbine to the vane 11 inserted into the present invention, which is a test body. As a result, the operating environment of an actual gas turbine can be more closely simulated, and the high-temperature combustion gas The lifespan of the exposed test object, the vane 11, can be extended.

In order to install the vane mounting member 300 to the housing 200, first, the vane lower fixing block 310 is mounted on the lower surface 203 of the housing 200 (see (a) of FIG. 11), and the vane (11) can be installed penetrating the housing 200 and assembled on the lower fixing block 310 with the lower end cut off (see (b) of FIG. 11). In addition, the vane upper fixing block 330 can be assembled on the upper part of the vane 11 (see (c) of FIG. 11).

Additionally, the second cooling air injection pipe 350 communicates with the interior of the vane 11 and may be installed penetrating the vane upper fixing block 330. At this time, a lower cover 320 and an upper cover 340 are further provided to cover the vane lower fixing block 310 and the vane upper fixing block 330, so that the vane 11 can be installed more stably (Figure (see (d) of 11). In addition, an upper flange 341 is further provided on the top of the vane upper fixing block 330, so that the second cooling air injection pipe 350 can be installed more firmly (see Figure 11 (e)).

Meanwhile, as in the embodiment shown in FIG. 12, the housing 200 may further include a root insertion groove 250 into which the roots 13 of the plurality of blades 12 are inserted. And, the blade mounting member 400 includes the roots 13 of the plurality of blades 12 and the root insertion groove 250 to fix the root 13 of the blade 12 to the root insertion groove 250. It may include a blade fixing block 410 fitted between both ends and a pin plate 430 fitted between the roots 13 of the plurality of blades 12. At this time, the blade mounting member 400 can attach and detachably assemble the blade 12 to the housing 200 by inserting and assembling the blade 12 into the housing 200. Here, the root insertion groove 250 may be injection molded to correspond to the shape of the blade root 13, but is not limited thereto, and can be modified into various shapes if the blade 12 can be stably fixed. It can be.

Additionally, the blade mounting member 400 may further include a third cooling air injection pipe 450.

The third cooling air injection pipe 450 is connected to the air compressor 20 and communicates with the inside of the root 13 to inject the cooling air supplied from the air compressor 20 into the blade 12. It can be installed through the housing 200.

Specifically, the third cooling air injection pipe 450 may communicate with the inside of the blade 12 and the air compressor 20. Accordingly, the blade 12 can be cooled by flowing the cooling air supplied from the air compressor 20 into the blade 12.

To install the blade mounting member 400 in the housing 200, first, the blade fixing block 410 can be inserted and installed into one end of the root insertion groove 250 provided in the housing 200 (see Figure 12). (see (a)). And, while inserting the blade root 13 into the root insertion groove 250, a plurality of blades 12 can be installed (see (b) of FIG. 12). At this time, the gap between the blade roots 13 can be narrowed by inserting the pin plate 430 between the blade roots 13 (see (c) of FIG. 12).

After insertion and installation of the blade 12 is completed, the blade fixing block 410 can be installed at the other end of the root insertion groove 250 (see (d) of FIG. 12). And, referring to (d) of FIGS. 2 and 12 , the third cooling air injection pipe 450 communicates with the inside of the blade 12 and may be installed penetrating the housing 200.

Meanwhile, referring to FIGS. 2, 4, and 8 to 10, the test rig 100 for testing the thermal durability of high-temperature components according to the present invention may further include a first temperature sensor 610.

The first temperature sensor 610 is provided in at least the pattern control air inlet 500 among the housing 200, the test specimen mounting part, and the pattern control air inlet part 500, and measures the temperature of the air flowing therein. You can.

Specifically, the first temperature sensor 610 is for measuring the temperature inside the passage 230 provided in the housing 200, and is installed in the air inlet unit 500 for pattern adjustment. Additionally, it may be installed on the vane mounting member 300, the blade mounting member 400, and the housing 200.

Additionally, the air input unit 500 for pattern control may further include a pressure sensor 700.

The pressure sensor 700 may be installed through the main body 510 in communication with the air passage 511 to measure the pressure of combustion gas flowing into the housing 200. Using this pressure sensor 700, the magnitude of disturbance caused by combustion instability occurring inside the test rig 100 due to high-temperature combustion gas can be measured in real time.

Through the first temperature sensor 610 and the pressure sensor 700, the temperature and pressure inside the air input unit 500 for pattern control can be checked in real time. Accordingly, the flow environment of the combustion gas inside the pattern control air inlet 500 can be simulated similarly to the environment at the rear of the combustor 50 of an actual gas turbine.

In addition, the test rig 100 for testing the thermal durability of high-temperature components according to the present invention may further include a cooling water pipe 800. The cooling water pipe 800 may be provided in at least one of the housing 200, the test specimen mounting portion, and the pattern adjustment air inlet portion 500, and may be connected to the cooling portion 60. Accordingly, the test rig 100 can be cooled by flowing the cooling water generated in the cooling unit 60 into the test rig 100.

Meanwhile, referring to FIGS. 2 and 13, the test rig 100 for testing the thermal durability of high-temperature components according to the present invention includes a second temperature sensor 620 that measures the surface temperature of the vane 11, which is a test body, and a blade. It may further include a third temperature sensor 630 that measures the surface temperature of (12).

The second temperature sensor 620 may be installed in a through hole of the vane 11 formed through the surface of the vane 11. Additionally, the third temperature sensor 630 may be installed in a through hole of the blade 12 formed through the surface of the blade 12. At this time, the vane 11 through hole and the blade 12 through hole may be holes drilled for installing the second temperature sensor 620 and the third temperature sensor 630, and the blade 12 and the vane 11 ) may be a cooling hole provided for cooling. Reference numeral 621 in FIG. 13 is a wire connected to the second temperature sensor 620 and the third temperature sensor 630.

In this way, the second temperature sensor 620 or the third temperature sensor 630 is installed penetrating the surface of the vane 11 or the surface of the blade 12 to measure the surface temperature of the high-temperature component as a test object during the thermal durability test. When doing this, interference with the flow pattern of combustion gas can be minimized due to the second temperature sensor 620 or the third temperature sensor 630.

Meanwhile, below, with reference to FIGS. 1, 14, and 15, a method for testing the thermal durability of high-temperature components according to another aspect of the present invention will be described.

Referring to Figure 14, the thermal durability test method of high-temperature parts according to the present invention includes a compressed air generation step (S120), a compressed air heating step (S130), a combustion gas generation step (S140), and a combustion gas supply step. It may include (S151) and a cooling air supply step (S153).

In the compressed air generation step (S120), compressed air can be generated by compressing air through the air compressor 20.

In the compressed air heating step (S130), the compressed air generated in the compressed air generating step (S120) may be heated to a preset temperature through the air heater (30). Specifically, in the compressed air heating step (S130), the air heater 30 is operated and set to 200-300 degrees, and then the compressed air can be preheated to a temperature for combustion.

In the combustion gas generation step (S140), the compressed air heated in the compressed air heating step (S130) and the fuel supplied from the fuel supply unit 40 are supplied to the combustor 50, and the fuel is burned to produce high temperature combustion gas. It can occur. Specifically, when the air for combustion is preheated to a preset temperature, the combustion gas valve may be opened to allow heated compressed air to flow into the front end of the combustor 50. Then, by opening the fuel line valve, fuel from the fuel supply unit 40 can be supplied to the combustor 50, and the fuel can be burned to generate combustion gas.

Afterwards, the combustion gas supply step (S151) supplies the combustion gas generated in the combustion gas generation step (S140) to the test rig 100 equipped with the vanes 11 and blades 12 installed in the gas turbine. You can. While monitoring the temperature inside the test rig 100 through the first temperature sensor 610, high-temperature combustion gas is supplied to perform a thermal durability test of the test specimen at the temperature to be tested (e.g., 800 - 1000°C). It can be done.

Meanwhile, the cooling air supply step (S153) may be performed together with the combustion gas supply step (S151) described above. In the cooling air supply step (S153), cooling air, which is unheated compressed air generated in the air compressor 20, is supplied to the test rig 100 to determine the temperature of the air flowing inside the test rig 100. Distribution can be controlled. Through the cooling air supply step (S153), the combustion gas temperature distribution in the internal flow path 230 of the test rig 100 can be adjusted to effectively simulate the flow of combustion gas of the gas turbine.

Specifically, the cooling air supply step (S153) may include a flow path temperature control step and a test body temperature control step.

In the flow path temperature control step, cooling air may be supplied to the flow path 230 provided inside the test rig 100, which is a passage through which combustion gas flows. Specifically, in the temperature control step of the flow path 230, cooling air supplied from the air compressor 20 is supplied through the first cooling air injection pipe 530 provided in the pattern control air inlet 500 through the air passage 511. ) and inputting it into the flow path 230, the temperature of the flow path 230 can be adjusted.

In the test specimen temperature control step, cooling air can be introduced into the vane 11 and the blade 12. Specifically, from the air compressor 20 through the second cooling air injection pipe 350 provided in the vane mounting member 300 and the third cooling air injection pipe 450 provided in the blade mounting member 400. By injecting the supplied cooling air into the vanes 11 and blades 12, the vanes 11 and blades 12 can be cooled.

Meanwhile, the thermal durability test method of high-temperature components according to the present invention may further include a cooling unit driving step (S110). In the cooling unit driving step (S110), the cooling unit 60 connected to the test rig 100 may be driven to cool the gas discharged from the test rig 100.

Meanwhile, the thermal durability test method for high-temperature components according to the present invention may further include a monitoring step. In the monitoring step, the flow rate of cooling air introduced into the test rig 100 may be displayed, and the temperature and pressure inside the test rig 100 may be displayed. In addition, the operator can adjust the amount of cooling air input according to the temperature and pressure inside the test rig 100.

Meanwhile, below, with reference to FIGS. 15 and 16, an embodiment of the thermal durability test system 10 and method for high-temperature components according to the present invention will be described. FIG. 15 is a diagram capturing a thermal durability test operation program for high-temperature components, and FIG. 16 is a flowchart of a procedure for executing the operation program shown in FIG. 15.

The thermal durability test operation program shown in FIGS. 15 and 16 is an example for concretely realizing the test system and test method according to the present invention. However, the thermal durability test system 10 and method for high-temperature components according to the present invention are not limited to the illustrated embodiment, and can be modified into various programs within the technical scope of the present invention.

First, the thermal durability test operation program shown in FIG. 15 briefly displays the parts shown in FIG. 1 on the screen and can display the status of the valve connected to the pipe connecting each part. Here, the valve connected to the pipe may include an opening/closing valve (V1) and a flow control valve (V2). In particular, the piping connected to each part of the air compressor 20 and the test rig 100 is equipped with a flow control valve (V2), so that the temperature pattern inside the test rig 100 can be adjusted by adjusting the flow rate of the cooling air. there is. In addition, it is provided with a display unit (M1) that displays the opening state of the flow control valve (V2) and a display unit (M2) that displays and inputs the flow rate flowing through the pipe, and monitors and inputs the pressure of the supplied cooling air in real time. It can be adjusted.

In addition, it may further include a display unit (M3) that displays the heating temperature of the air heater (30) and a display unit (M4) that displays the flow rate and pressure of the fuel supplied from the fuel supply unit (40) to the combustor (50). there is. In addition, a display unit (M5) that displays and inputs the temperature and pressure of the air or coolant supplied to the test rig 100 from the cooling unit 60 may be further included.

Also, although not shown, the thermal durability test operation program shown can record the temperature and pressure (flow rate) displayed by the display units (M1, M2, M3, M4, M5) in real time.

Next, with reference to FIG. 16, a procedure for executing the driving program shown in FIG. 15 will be described.

First, create a driving environment by implementing the on-site inspection manual before driving. Then, the valves (V1, V2) and all systems are set to their initial state through program reset.

Afterwards, the cooling unit 60 for system cooling can be driven and the air compressor 20 can be operated to generate compressed air. The generated compressed air can be injected into the test rig 100 or the vane 11 and blade 12 while controlling the flow rate and temperature through the above-mentioned operation program.

When the flow rate of air supplied to the test rig 100 and the temperature and pressure of the heated compressed air reach the preset standards, the fuel line valve is opened and fuel is supplied to the test rig 100, thereby controlling the flow rate in real time. It can be monitored.

The test conditions of the test object, such as temperature and pressure, can be monitored and adjusted to suit the test conditions. When the test conditions are reached, the heat durability test of the test body, the vane 11 and the blade 12, can be performed.

When the thermal durability test is completed, the operation of each component is stopped, and the air discharged from the test rig 100 can be cooled and discharged through the cooling unit 60.

In this way, the test rig for testing the thermal durability of high-temperature components according to the present invention, unlike the conventional method of separately producing test pieces and performing thermal durability testing, tests by installing and testing vanes and blades used in actual gas turbines according to the operating environment, The reliability of thermal durability tests can be improved.

In addition, according to the present invention, by evaluating vanes and blades by simulating the thermal stress state occurring in an actual gas turbine, limiting factors are minimized when analyzing test results, which has the effect of further improving the usability and reliability of the evaluation results. You can get it.

Additionally, according to the present invention, the flow of combustion gas in a gas turbine can be simulated by adjusting the arrangement of the vanes and blades to the operating environment of the gas turbine.

Additionally, according to the present invention, test conditions and results can be monitored and recorded in real time.

Above, specific embodiments of the present invention have been described in detail, but the spirit and scope of the present invention are not limited to these specific embodiments, and those skilled in the art in the technical field to which the present invention pertains will recognize the patent claims as described in the claims. Various modifications and variations are possible without changing the gist of the present invention.

10: Thermal durability test system for high temperature parts 20: Air compressor
30: air heater 40: fuel supply unit
50: combustor 60: cooling unit
100: Test rig for testing the thermal durability of high temperature parts
200: housing 210: inlet
220: outlet 230: flow path
250: Root insertion groove 300: Vane mounting member
310: Vane lower fixing block 330: Vane upper fixing block
350: Second cooling air injection pipe 400: Blade mounting member
410: Blade fixing block 430: Pin plate
450: Third cooling air injection pipe 500: Air inlet for pattern control
510: Main body 511: Air passage
530: First cooling air injection pipe 540: Supply slit
610: first temperature sensor 620: second temperature sensor
630: Third temperature sensor 700: Pressure sensor
800: Coolant piping

Claims (20)

A housing connected to a combustor and formed with an inlet through which combustion gas flows in, an outlet through which the combustion gas is discharged, and a passage through which the combustion gas flows is provided in a receiving space provided therein;
A test specimen mounting portion provided in the housing and configured to dispose a test specimen including a vane and a blade installed in a gas turbine on the flow path; and,
It is connected to an air compressor that compresses air to simulate the operating environment of a gas turbine by adjusting the temperature distribution of combustion gas inside the housing, is coupled to the inlet side of the housing, and is connected to the unheated air compressor supplied from the air compressor. An air inlet unit for pattern control that injects cooling air, which is compressed air, into the flow path.
Including,
The test specimen mounting part,
A vane mounting member coupled to the housing and on which the vane is mounted; and
It is coupled to the housing, the blade is mounted in communication with the vane and the passage, is provided to be spaced apart from the vane mounting member in the outlet direction, and is rotated at a preset angle from the vane mounting member. Blade mounting member
Includes,
The housing is a test rig for testing the thermal durability of high-temperature components, wherein the passage is formed in a curved shape to simulate the flow of combustion gas between the vane and the blade in a gas turbine. delete According to paragraph 1,
The air input unit for pattern control,
a main body having one side coupled to the housing, the other side coupled to the combustor, and having an air passage communicating with the flow passage therein; and,
Heat of high-temperature parts, including a first cooling air injection pipe that is mounted on the main body in communication with the air passage, is connected to the air compressor, and injects the cooling air supplied from the air compressor into the air passage. Test rig for durability testing. According to paragraph 3,
A test rig for testing the thermal durability of high-temperature components, wherein a plurality of first cooling air injection pipes are installed in the circumferential direction of the main body. According to paragraph 4,
The main body is recessed in the thickness direction on the inner peripheral surface of the main body, is provided in plurality to be connected to each of the plurality of first cooling air injection pipes, and further includes a long supply slit formed on the inner peripheral surface of the main body. Test rig for thermal durability testing. According to paragraph 1,
The vane has upper and lower ends penetrating the upper and lower surfaces of the housing,
The vane mounting member,
A vane lower fixing block mounted on the lower surface of the housing and into which the lower end of the vane is assembled; and,
A test rig for testing the thermal durability of high-temperature components, which is mounted on the upper surface of the housing and includes a vane upper fixing block to which the upper end of the vane is assembled. The method of claim 6, wherein the vane mounting member,
It further includes a second cooling air injection pipe connected to the air compressor and installed through the upper fixing block of the vane to communicate with the inside of the vane to inject the cooling air supplied from the air compressor into the inside of the vane. A test rig for testing the thermal durability of high-temperature components. According to paragraph 1,
The housing further includes a root insertion groove into which blade roots provided on the plurality of blades are inserted,
The blade mounting member,
a blade fixing block fitted between a plurality of blade roots and both ends of the root insertion groove to fix the blade root to the root insertion groove; and,
A test rig for testing the thermal durability of high-temperature components, including a pin plate sandwiched between a plurality of blade roots. The method of claim 8, wherein the blade mounting member,
Further comprising a third cooling air injection pipe connected to the air compressor and installed through the housing to communicate with the inside of the root so as to inject the cooling air supplied from the air compressor into the inside of the blade. Test rig for testing the thermal durability of high-temperature components. According to paragraph 1,
Thermal durability of the high-temperature part, further comprising a first temperature sensor provided in at least the pattern control air inlet part among the housing, the test specimen mounting part, and the pattern control air inlet part, and measuring the temperature of the air flowing therein. Test rig for testing purposes. According to clause 10,
A second temperature sensor installed in a vane through-hole formed through the surface of the vane; and,
A test rig for testing the thermal durability of high-temperature components, further comprising a third temperature sensor installed in a blade penetration hole formed through the surface of the blade. According to paragraph 3,
The air input unit for pattern control further includes a pressure sensor installed through the main body in communication with the air passage to measure the pressure of combustion gas flowing into the housing. An air compressor that compresses air to produce compressed air;
a combustor in which the compressed air supplied from the air compressor is heated and supplied by an air heater, and combusts the fuel supplied from the fuel supply unit to generate high-temperature combustion gas;
It is connected to the rear end of the combustor, and is provided with a passage through which the combustion gas flowing in from the combustor flows. A test specimen including vanes and blades installed in the gas turbine is mounted on the passage, and the air compressor a test rig for testing the thermal durability of the vane and the blade by injecting cooling air, which is unheated compressed air supplied from, into the flow path;
A cooling unit connected to the test rig and cooling the air discharged from the test rig; and,
Heat of high-temperature components, including a control unit that adjusts the pressure and temperature of the combustion gas and the cooling air flowing into the test rig to simulate the operating environment of a gas turbine by adjusting the combustion temperature distribution inside the test rig. Durability test system. According to clause 13,
The test rig includes a first temperature sensor that measures the temperature of the air flowing inside, and a pressure sensor that measures the pressure of the air inside,
The control unit receives signals from the temperature sensor and the pressure sensor to adjust the input amounts of the combustion gas and cooling air supplied to the test rig. According to clause 14,
A thermal durability test system for high-temperature components, further comprising a monitoring unit that displays the temperature and pressure received from the temperature sensor and the pressure sensor, and records the received temperature and pressure in real time. According to clause 13,
The test rig further includes a vane mounting member on which the vane is mounted, and a blade mounting member provided to be spaced apart from the vane mounting member and rotated at a preset angle from the vane mounting member,
The flow path is formed in a curved shape to simulate the flow of combustion gas between the vane and the blade in a gas turbine. A compressed air generation step of compressing air through an air compressor to generate compressed air;
A compressed air heating step of heating the compressed air generated in the compressed air generating step to a preset temperature through an air heater;
A combustion gas generation step of supplying the compressed air heated in the compressed air heating step and fuel supplied from a fuel supply unit to a combustor, and burning the fuel to generate high temperature combustion gas;
A combustion gas supply step of supplying the combustion gas generated in the combustion gas generation step to a test rig equipped with vanes and blades installed in a gas turbine;
In addition to the combustion gas supply step, a cooling air supply step of supplying cooling air, which is unheated compressed air generated in the air compressor, to the test rig to adjust the temperature distribution of the air flowing inside the test rig; and
A cooling unit driving step of driving a cooling unit connected to the test rig to cool the gas discharged from the test rig.
Thermal durability test method of high temperature parts including. According to clause 17,
The cooling air supply step is,
A flow path temperature control step of supplying the cooling air to a flow path provided inside the test rig through which the combustion gas flows; and,
A method for testing the thermal durability of high-temperature parts, including a test specimen temperature control step of introducing the cooling air into the interior of the vane and the blade. delete According to clause 17,
A monitoring step of displaying the flow rate of the cooling air introduced into the test rig, displaying the temperature and pressure inside the test rig, and adjusting the amount of cooling air input according to the temperature and pressure inside the test rig. Including, thermal durability test method of high temperature parts.

Images