KR20170045784A - Apparatus for testing gas turbine and method for testing gas turbine - Google Patents

Apparatus for testing gas turbine and method for testing gas turbine Download PDF

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Publication number
KR20170045784A
KR20170045784A KR1020150145450A KR20150145450A KR20170045784A KR 20170045784 A KR20170045784 A KR 20170045784A KR 1020150145450 A KR1020150145450 A KR 1020150145450A KR 20150145450 A KR20150145450 A KR 20150145450A KR 20170045784 A KR20170045784 A KR 20170045784A
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South Korea
Prior art keywords
gas
turbine
section
gas turbine
unit
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KR1020150145450A
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Korean (ko)
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KR101757986B1 (en
Inventor
손정락
임형수
최범석
박무룡
윤의수
박준영
서정민
유일수
황순찬
최원철
방제성
강도원
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한국기계연구원
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Priority to KR1020150145450A priority Critical patent/KR101757986B1/en
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L3/00—Measuring torque, work, mechanical power, or mechanical efficiency, in general
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/02—Details or accessories of testing apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/12—Testing on a test bench

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Testing Of Engines (AREA)

Abstract

The present invention relates to a gas turbine tester, and more particularly, to an apparatus for testing a gas turbine, in which a disk having a diameter smaller than the diameter of the disk is installed and tested with a bladed blades applied to the gas turbine to reduce the power consumed during the test, .

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a gas turbine test apparatus,

The present invention relates to a gas turbine test apparatus and a gas turbine test method using the gas turbine test apparatus. More particularly, the present invention relates to a gas turbine test apparatus, And a gas turbine test method using the gas turbine test apparatus.

Gas Turbine means a rotary power engine that extracts energy from the flow of combustion gas. Such a gas turbine is composed of a compressor, a combustion chamber, a turbine, and the like. In the compressor, air is compressed. In the combustion chamber, compressed air is mixed with the fuel and burned. The turbine is driven by the force generated as the fuel is burned in the above combustion chamber. The energy generated by the above process is used to drive an aircraft, a train, a ship, a generator, a tank, and the like.

In recent years, gas turbine-based power generation facilities have been increasing due to pollution problems caused by rapid industrial development and global warming. In order to produce high-efficiency large-capacity gas turbines, various countries have competitively studied and developed new types of gas turbines . As of 2009, the maintenance market for industrial gas turbines is about 40% of the product market and is expected to grow at an annual average of 3.7% through 2018.

Meanwhile, the blade, which is a core component of the gas turbine, is in direct contact with high-temperature and high-pressure gas at the time of starting, and is exposed to a harsh environment such as rotating at high speed, thereby significantly affecting the performance and lifetime of the gas turbine. Therefore, the test of the gas turbine can be said to be the evaluation of various performances of the above-mentioned blades.

For the accuracy of the test, the performance should be tested using an actual turbine installed in a large unit. However, as described above, since the gas turbine is used as a power means for a large apparatus such as an aircraft, a train, and a generator, when the actual turbine is used as it is, the capacity of the compressor must be equal to the capacity actually used. It should be supplied in the same amount as the actual fuel amount. Therefore, when the actual turbine is used as it is, there is a problem that the equipment for constructing the test apparatus and the energy consumed in the test process are enormous.

In order to reduce the energy consumed in the test process, conventionally, the size of the turbine was reduced and the test was performed. However, in the case of the conventional test described above, since the size of the blades installed on the disk is also reduced in proportion to the reduction of the turbine size, the results for the blade of actual size can not be accurately obtained, do.

SUMMARY OF THE INVENTION The object of the present invention is to solve the above-mentioned problems of the prior art, and it is an object of the present invention to provide a disk unit having a diameter smaller than the diameter of the disk, And a gas turbine test method using the gas turbine test apparatus.

The above object is achieved according to the present invention by providing a gas compression apparatus comprising: a first compression section for compressing a gas; A fuel supply unit for supplying fuel; A combustion section that is supplied with the gas compressed from the first compression section and supplies the fuel from the fuel supply section to generate a gas by combustion; A disc portion provided at a relatively smaller diameter than an imprinted disc to be applied to the gas turbine and to which a bladed blades applied to the gas turbine are installed, and a rotary shaft on which the disc portion is provided, A rotating turbine section; And a power measuring section for measuring the power generated in the turbine section.

Here, it is preferable that one disk portion is provided on the rotary shaft.

Further, the present invention may further include a torque measuring unit measuring a torque of the rotating shaft.

The present invention may further comprise a second compression unit for compressing the gas and cooling the turbine unit by supplying the compressed gas to the turbine unit.

The above object is achieved by a gas turbine test method using a gas turbine test apparatus for testing the performance of a gas turbine including a disk on which a plurality of blades are installed and a rotary shaft on which the disk is installed, A compression step in which the gas is compressed; A supply step of supplying fuel from the fuel supply unit to the combustion unit; A combustion step in which the gas compressed by the compression step and the fuel supplied by the supply step are mixed and combusted in the combustion section; A rotating step of rotating the turbine section by supplying gas generated by the combustion step to a turbine section including a disk having a diameter smaller than the diameter of the disk and a rotating shaft having the disk section; And a power measuring step of measuring power of the turbine section.

In addition, it is preferable that the rotating step is performed by providing one disk part on the rotating shaft.

Further, the present invention may further include a torque measuring step of measuring a torque of the rotating shaft before the power measuring step.

Further, the present invention may further include a cooling step of compressing the gas and supplying the compressed gas to the turbine section, thereby cooling the turbine section.

According to the present invention, the reliability of the test can be improved because the actual turbine blades are used while reducing power consumption and facility installation cost during the test.

In addition, since the cross-sectional area of the flow path through which the gas flows is reduced by the disk portion provided with the diameter smaller than the diameter of the disk, the amount of gas supplied to the flow path is reduced so that the consumption power required for the test and the installation cost are significantly reduced .

In addition, the use of the blades of the threaded shape is used as it is, and the reliability of the test is improved.

Further, the gas turbine test can be continuously carried out by cooling the turbine section by using the second compressed section that supplies the compressed gas to the turbine section.

Fig. 1 shows the overall configuration of a gas turbine test apparatus according to an embodiment of the present invention,
2 shows a turbine section of a gas turbine test apparatus according to an embodiment of the present invention,
3 shows a disc portion and a blade of a gas turbine test apparatus according to an embodiment of the present invention with a conventional disc and a blade,
4 is a flowchart of a gas turbine test method using a gas turbine testing apparatus according to an embodiment of the present invention,
FIG. 5 shows a rotating step of a gas turbine test method using a gas turbine test apparatus according to an embodiment of the present invention.

Hereinafter, a gas turbine test apparatus according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

FIG. 1 shows a general configuration of a gas turbine testing apparatus according to an embodiment of the present invention. FIG. 2 shows a turbine section of a gas turbine testing apparatus according to an embodiment of the present invention, A disk and a blade, and a disk portion and a blade of a gas turbine test apparatus according to an embodiment of the present invention.

1 and 2, a gas turbine test apparatus 100 according to an embodiment of the present invention includes a first compression unit 110, a fuel supply unit 120, a combustion unit 130, 140, a power measuring unit 150, a second compression unit 160, and a torque measuring unit 170.

The first compression unit 110 compresses the gas and communicates with the combustion unit 130, which will be described later. The first compression unit 110 supplies the compressed gas to the combustion unit 130.

The first compression unit 110 may be arranged in series or in parallel so that the plurality of compressors satisfy the target flow rate and pressure.

The fuel supply unit 120 supplies fuel and is connected to a combustion unit 130, which will be described later. The fuel supply unit 120 supplies fuel to the combustion unit 130.

The combustion unit 130 communicates with the first compression unit 110 and the fuel supply unit 120 to receive the compressed gas from the first compression unit 110 and receive the fuel from the fuel supply unit 120, , The compressed gas and the fuel are mixed and combusted to generate the gas.

The turbine portion 140 is rotated by gas and communicates with the combustion portion 130 to receive the gas from the combustion portion 130. The turbine portion 140 includes a disk portion 141 and a rotation shaft 142.

The disc portion 141 is provided with a threaded blade b and is provided with a diameter smaller than the diameter of the disc d (see Fig. 3 (a)). The disc portion 141 is provided in a disc shape, and a plurality of threaded blades b are provided along the circumferential direction of the disc.

The blade (b) is a key component of the gas turbine because it directly contacts the high-temperature and high-pressure gas during start-up, and is exposed to a harsh environment such as rotating at a high speed and has a considerable effect on the performance and lifetime of the gas turbine . Therefore, the gas turbine test apparatus according to the embodiment of the present invention can be said to evaluate various performance of the blade (b), so that the blade (b) is made of the size and material actually used in the field It is necessary to be a bladed blade (b).

Therefore, as described above, the reliability of the gas turbine test can be greatly improved by the disc portion 141 on which the threaded-shaped blade (b) is installed.

On the other hand, as shown in FIG. 3B or FIG. 3C, since the disk portion 141 described above is provided with a smaller diameter than the disk d of the threaded shape, the cross-sectional area of the flow path through which the gas flows is reduced . Therefore, when the gas turbine test is performed using the disk portion 141, the amount of gas supplied to the flow path, that is, the amount of gas supplied from the first compression portion 110 and the amount of gas supplied from the fuel supply portion 120 It is possible to greatly reduce the amount of fuel, and it is possible to carry out the test using the first compression portion 110 having a relatively low capacity. At this time, since the blade (b) provided on the disk portion 141 can be used in the form of a yarn without reduction in size, the disk portion 141 described above can reduce power consumption required in the gas turbine test, Can be maintained.

The rotation shaft 142 is provided with the disk portion 141 described above, and is rotated by the rotation of the disk portion 141. [

The power measuring unit 150 measures the power generated by the turbine unit 140 and is installed in the turbine unit 140. The power measuring unit 150 measures the power generated in the turbine unit 140 from the supplied gas amount, the rotational speed of the rotating shaft 142, and the rotational speed variation amount. With this power measuring unit 150, the result of the test of the gas turbine can be derived.

A load bank 180 for consuming the power generated by the turbine unit 140 may be disposed at a rear end of the power measuring unit 150. It is also possible to supply the power generated by the turbine section 140 to the power system by being linked to the power system instead of the load bank 180.

The second compression unit 160 compresses the gas and supplies the compressed gas to the turbine unit 140 to cool the turbine unit 140 and to communicate with the turbine unit 140. By this second compression section 160, the turbine section 140 is cooled, whereby the turbine can be driven for a long time, and the gas turbine test can be continuously carried out.

The torque measuring unit 170 measures the torque of the above-described rotating shaft 142 and is connected to the rotating shaft 142. The torque of the rotating shaft 142 can be easily measured by the torque measuring unit 170. [

The first compression unit 110, the fuel supply unit 120, the combustion unit 130, the turbine unit 140, the power measurement unit 150, the second compression unit 160, and the torque measurement unit 170 According to the gas turbine test apparatus 100 according to the embodiment of the present invention, the reliability of the test can be improved while the power consumed in the test is reduced.

Hereinafter, a gas turbine test method using a gas turbine test apparatus according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

FIG. 4 is a flow chart of a gas turbine testing method using a gas turbine testing apparatus according to an embodiment of the present invention, and FIG. 5 is a flowchart illustrating a rotating step of a gas turbine testing method using the gas turbine testing apparatus according to an embodiment of the present invention. Respectively.

4, a gas turbine test method (S100) using a gas turbine test apparatus according to an embodiment of the present invention includes a compression step (S110), a supply step (S120), a combustion step (S130), and a rotation step (S140), a torque measuring step (S150), and a power measuring step (S160).

The compressing step (S110) is a step in which the gas is compressed in the first compressor (110), and is performed by the first compressor (110). The compressed gas generated in the above-described compression step (S110) is used in the combustion step (S130) described later.

The supplying step S120 is a step of supplying fuel from the fuel supplying unit 120 to the combustion unit 130. [

The combustion step S130 is a step in which the gas compressed by the compression step S110 and the fuel supplied by the supply step S120 are mixed and combusted in the combustion part 130, do. Gas is generated by the above-described combustion step (S130), and the generated gas is supplied to the turbine section (140).

The rotating step S140 includes a disk portion 141 provided with a threaded blade b and a diameter smaller than the diameter of the disk d of the threaded shape and a rotating shaft 142 provided with the disk portion 141 The step of supplying the gas generated by the combustion step S130 to the turbine section 140 to rotate the turbine section 140 is performed in the turbine section 140.

The blade (b) is a key component of the gas turbine because it directly contacts the high-temperature and high-pressure gas during start-up, and is exposed to a harsh environment such as rotating at a high speed and has a considerable effect on the performance and lifetime of the gas turbine . Therefore, the gas turbine test apparatus according to the embodiment of the present invention can be said to evaluate various performance of the blade (b), so that the blade (b) is made of the size and material actually used in the field It is necessary to be a bladed blade (b).

Therefore, as described above, the reliability of the gas turbine test can be greatly improved by the rotation step S140 using the disk portion 141 on which the threaded-shaped blade b is installed.

On the other hand, since the disk portion 141 is provided with a diameter smaller than that of the disk d, the sectional area of the flow path through which the gas flows is reduced. Therefore, when the gas turbine test is performed using the disk portion 141, the amount of gas supplied to the flow path, that is, the amount of gas supplied from the first compression portion 110 and the amount of the gas supplied from the fuel supply portion 120 It is possible to greatly reduce the amount of fuel, and it is possible to carry out the test using the first compression portion 110 having a relatively low capacity. Since the blade (b) provided in the disk portion 141 can be used as it is in the form of a seal without reduction in size, according to the rotation step (S140) using the disk portion 141 described above, As the power is reduced, the reliability of the test can be maintained.

If the turbine section 140 is provided in a multi-stage structure, the following will be described. Here, the stage refers to a part of the entire turbine section 140 that includes one disk section 141 provided with a smaller diameter than the disk d of the annular shape and a rotation shaft 142 provided with one disk section 141 ≪ / RTI > That is, the turbine unit 140 is provided with a plurality of disc units 141 on the rotating shaft 142, and is provided in a multi-stage. As described above, when the test is performed using the multi-stage, that is, the entirety of the turbine section 140, the capacity of the power measuring section 150 and the torque measuring section 170 connected to the rotating shaft 142 must be increased, to be.

5, when the turbine section 140 is used as a single stage, that is, when the turbine section 140 is divided into a single disk section 141 and a single disk section 141, The capacity of the power measuring unit 150 and the torque measuring unit 170 can be greatly reduced by using only a portion of the rotating shaft 142 on which the disk unit 141 of the disk unit 141 is provided.

Therefore, it is preferable that the rotation step S140 is performed by installing only one of the plurality of disk portions 141 on the rotation shaft 142. [

The torque measuring step S150 is a step of measuring the torque of the rotating shaft 142 and is performed by the torque measuring unit 170. [ By this torque measuring step S150, the torque of the rotating shaft 142 can be easily measured.

The power measurement step (S160) is a step of measuring the power of the turbine section (140), which is performed by the power measurement section (150). By this power measurement step (S160), the result of the test of the gas turbine can be derived.

On the other hand, a separate cooling step may be further included to drive the turbine for a long time. The cooling step compresses the gas and supplies the compressed gas to the turbine section 140 to cool the turbine section 140 and is performed by the second compression section 160. By this cooling step, the turbine section 140 is cooled, whereby the gas turbine test can be continuously carried out.

Therefore, in one embodiment of the present invention including the compression step S110, the supplying step S120, the combustion step S130, the rotating step S140, the torque measuring step S150, and the power measuring step S160, The gas turbine test method (S100) using the gas turbine test apparatus according to the present invention can improve the reliability of the test while reducing the power consumed in the test.

The scope of the present invention is not limited to the above-described embodiments, but may be embodied in various forms of embodiments within the scope of the appended claims. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the present invention as defined by the appended claims.

100: a gas turbine test apparatus according to an embodiment of the present invention
110: first compression unit 120: fuel supply unit
130: Combustion part 140: Turbine part
141: Disk section 142:
150: power measuring unit 160: second compression unit
170: torque measuring unit 180: load bank
b: blade d: disk
S100: Gas turbine test method using gas turbine tester according to one embodiment of the present invention
S110: compression step S120: supply step
S130: combustion step S140: rotation step
S150: torque measuring step S160: power measuring step

Claims (8)

A first compression unit for compressing the gas;
A fuel supply unit for supplying fuel;
A combustion section that is supplied with the gas compressed from the first compression section and supplies the fuel from the fuel supply section to generate a gas by combustion;
A disc portion provided at a relatively smaller diameter than an imprinted disc to be applied to the gas turbine and to which a bladed blind applied to the gas turbine is installed; and a rotating shaft on which the disc portion is provided, A rotating turbine section; And
And a power measuring unit for measuring the power generated by the turbine unit. The method according to claim 1,
Wherein one disk portion is provided on the rotating shaft. The method according to claim 1,
And a torque measuring section for measuring a torque of the rotating shaft. 4. The method according to any one of claims 1 to 3,
And a second compression section for compressing the gas and for cooling the turbine section by supplying the compressed gas to the turbine section. A gas turbine test method using a gas turbine tester for testing the performance of a gas turbine including a disk on which a plurality of blades are installed and a rotary shaft on which the disk is installed,
Compressing the gas in the first compressor;
A supply step of supplying fuel from the fuel supply unit to the combustion unit;
A combustion step in which the gas compressed by the compression step and the fuel supplied by the supply step are mixed and combusted in the combustion section;
There is provided a gas turbine comprising a turbine section including a disk section provided with a relatively smaller diameter than an impeller-shaped disk to be applied to a gas turbine and equipped with an impeller blade to be applied to a gas turbine, To rotate the turbine section; And
And a power measuring step of measuring power of the turbine section. 6. The method of claim 5,
Wherein,
And one disc portion is provided on the rotating shaft. The method according to claim 6,
And measuring a torque of the rotating shaft before the power measuring step. 8. The method according to any one of claims 5 to 7,
And a cooling step of compressing the gas and supplying the compressed gas to the turbine section to cool the turbine section.
KR1020150145450A 2015-10-19 2015-10-19 Apparatus for testing gas turbine and method for testing gas turbine KR101757986B1 (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108931380A (en) * 2017-05-27 2018-12-04 清华大学 The turbo blade test macro of gas source driving
CN108931359A (en) * 2017-05-27 2018-12-04 清华大学 The turbo blade test macro of compressor driving
CN114252268A (en) * 2021-12-15 2022-03-29 北京航空航天大学 Gas generator head cavity filling test device with gas blowing and test method

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006075441A1 (en) * 2005-01-11 2006-07-20 The Tokyo Electric Power Company, Incorporated Process quantity measurement method and device
KR200447336Y1 (en) * 2009-09-09 2010-01-19 주식회사 이지가스터빈 Micro gas turbine engine test cell

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108931380A (en) * 2017-05-27 2018-12-04 清华大学 The turbo blade test macro of gas source driving
CN108931359A (en) * 2017-05-27 2018-12-04 清华大学 The turbo blade test macro of compressor driving
CN114252268A (en) * 2021-12-15 2022-03-29 北京航空航天大学 Gas generator head cavity filling test device with gas blowing and test method

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