CN113267342A - Embedded series-mounted test platform for gas turbine parts, components and systems - Google Patents
Embedded series-mounted test platform for gas turbine parts, components and systems Download PDFInfo
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- CN113267342A CN113267342A CN202110406272.1A CN202110406272A CN113267342A CN 113267342 A CN113267342 A CN 113267342A CN 202110406272 A CN202110406272 A CN 202110406272A CN 113267342 A CN113267342 A CN 113267342A
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- turbine
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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
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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
- G01M15/02—Details or accessories of testing apparatus
Abstract
The embedded series-mounting test platform of the gas turbine parts, components and systems has the advantages that the parts or components such as the gas compressor, the combustion chamber, the turbine and the like are serially mounted through the gas path pipeline, so that the parts or components can be separated by a certain distance, test equipment is conveniently arranged, a test object is conveniently installed and debugged, and the influence of other parts on the test object is reduced, wherein the test object can be the parts or components of the gas turbine such as the gas compressor, the combustion chamber, the turbine and the like, and can also be the systems or subsystems of the gas turbine such as an air system and the like; a plurality of compressor turbine units with different sizes can be serially arranged through the gas path pipeline, so that the test working condition is adjusted or higher test pressure is obtained; the test platform can also directly connect the gas compressor, the combustion chamber and the turbine together without using a gas circuit pipeline to form a compact configuration; the test of some spare parts that do not come out through the pipe connection mode independence is realized.
Description
Technical Field
The invention belongs to the technical field of testing of parts, components and systems of a gas turbine, and relates to an embedded series-mounted testing platform for the parts, the components and the systems of the gas turbine.
Background
Conventional gas turbine test platforms: the device depends on equipment such as a compressor set, a gas tank, a motor and the like, the occupied area is large, the power is low, the flow of a gas source is low, and the requirements on sites and facility equipment are high, so that part of rotation tests are replaced by static tests, the influence of rotation on test results is ignored, and the working state of the gas turbine is difficult to simulate.
In addition, the testing of parts, components and systems can be performed directly on gas turbines of practical size and operation, but the following problems exist: firstly, the cost is high when tests are carried out on the gas turbine with actual size and working conditions, secondly, the actual gas turbine has compact and complex structure and narrow internal space, and complex measuring equipment is difficult to arrange, and thirdly, the working states of all parts, components and systems of the actual gas turbine are closely related, and the single part, component or system is difficult to carry out test research.
Disclosure of Invention
In order to solve the problems, the invention provides an embedded series test platform for gas turbine parts, components and systems, which is a universal platform capable of testing the gas turbine parts, components and systems.
The invention relates to an embedded series-mounted test platform for gas turbine parts, components and systems. In the compressor turbine unit, the compressor, the combustion chamber and the turbine are serially arranged through gas path pipelines, so that parts or components can be separated by a certain distance, test equipment is convenient to arrange, a test object is convenient to install and debug, and the influence of other parts on the test object is reduced.
In addition, the test platform can also serially install a plurality of compressor turbine units with different sizes through the gas circuit pipeline, so as to adjust the test working condition or obtain higher test pressure.
Meanwhile, the test platform can directly connect the gas compressor, the combustion chamber and the turbine together without using a gas circuit pipeline to form a compact configuration; some parts that were not separated by plumbing were tested.
The invention has the advantages that:
1. the test platform is convenient for measuring and researching parts or components of the gas turbine. The test platform is characterized in that parts such as the gas compressor, the combustion chamber, the turbine and the like are serially arranged through the gas circuit pipeline, so that the part or the part serving as a test object is not required to be compactly assembled with other parts or parts, but can be isolated through the connection of the gas circuit pipeline, measuring equipment can be conveniently arranged around the test object, and a rectifying device can be arranged at an inlet and an outlet, so that the interference of other parts to the test object is reduced.
2. The test platform can change test parameters through the serial assembly of the gas compressors and the heat exchangers among the gas compressors. The test platform can realize the high pressure ratio by serially assembling a plurality of gas compressors through the gas path pipeline, and compared with the mode of realizing the high pressure ratio by adopting a plurality of shafts in the prior gas turbine, the test platform has a simple structure, and the serial gas compressors have independent mechanical rotation, thereby improving the reliability of the system.
3. The test platform has the capability of independent operation independent of external facility equipment. The air source and the power supply of the test platform have the self-supply capacity, and do not depend on power consumption equipment such as a dynamometer, on one hand, the turbine provides power output for the gas compressor, and the gas compressor also provides load for the turbine, and the test platform can be independent of external facilities and equipment to operate independently, so that the requirements on test environment, field and facilities are reduced, the test can be conveniently carried out in an open field outdoors, and the test platform can be conveniently moved and transported through a transport tool.
Drawings
Fig. 1 is a schematic view of a turbine unit of a gas compressor in the test platform of the present invention.
FIG. 2 is a schematic view of a series installation mode of a turbine unit and a combustion chamber of a gas compressor and an installation mode of test equipment in the test platform.
FIG. 3 is a schematic diagram of a plurality of compressor turbine units in series in the test platform of the present invention.
FIG. 4 is a schematic diagram of a compact configuration of the test platform of the present invention.
FIG. 5 is a schematic diagram of an inner embedding test of a turbine outer ring block by applying the test platform of the invention.
In the figure:
1-compressor inlet section 2-compressor main body 3-compressor outlet gas collecting cavity
4-turbine main body 5-turbine outlet section 6-turbine inlet gas collecting cavity
7-transmission shaft 8-outlet gas collection cavity outlet section 9-turbine inlet gas collection cavity inlet section of compressor outlet
10-combustion chamber inlet section 11-combustion chamber main body 12-combustion chamber outlet section
13-combustion chamber inlet gas path pipeline 14-combustion chamber outlet gas path pipeline 15-pressure sensor
16-temperature sensor 17-PIV Camera 18-stationary part
No. 19-glass transparent window 20-2 compressor gas circuit pipeline and No. 21-2 turbine gas circuit pipeline
No. 22-3 compressor gas circuit pipeline, No. 23-3 turbine gas circuit pipeline, No. 24 combustion chamber inlet gas circuit pipeline
25-combustion chamber outlet gas path pipeline 26-mounting edge 27-bolt
28-nut 29-turbine outer ring block 30-turbine blade
31-turbine casing 32-turbine front pressure measuring point 33-turbine front temperature measuring point
34-turbine rear pressure measuring point 35-turbine rear temperature measuring point 36-cooling air pipeline
37-cooling air temperature measuring point 38-turbine outer ring block surface temperature measuring point
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The invention relates to an embedded series-mounted test platform of gas turbine parts, components and systems, which comprises: the device comprises a compressor turbine unit, a combustion chamber, a gas path pipeline, test equipment, data acquisition equipment for signal acquisition of the test equipment, a support for supporting the compressor turbine unit and the combustion chamber, and auxiliary equipment for realizing the work of the compressor turbine, wherein the compressor turbine unit, the combustion chamber, the gas path pipeline, the test equipment, the data acquisition equipment for signal acquisition of the test equipment, the support for supporting the compressor turbine unit and the combustion chamber, the auxiliary equipment for realizing the work of the compressor turbine.
As shown in fig. 1, the compressor turbine unit includes a compressor, a turbine and a drive shaft 7, the turbine is connected to the compressor through the drive shaft 7, and the turbine transmits power to the compressor through the drive shaft 7. The compressor comprises a compressor inlet section 1, a compressor main body 2 and a compressor outlet gas collecting cavity 3 arranged at the compressor outlet. The compressor inlet section 1 is used for guiding gas to enter the compressor main body 2 and has the effects of rectification and diffusion; the compressor main body 2 is used for increasing the pressure of airflow; the compressor outlet gas collecting cavity 3 is used for collecting gas at the outlet of the compressor. The turbine comprises a turbine body 4, a turbine outlet section 5 and a turbine inlet plenum 6 mounted at the turbine inlet. Wherein, the turbine inlet gas collecting cavity 6 is used for collecting the airflow entering the turbine and has the rectification effect. The turbine body 4 is used for extracting work from the airflow so as to drive the compressor to rotate through the transmission shaft 7; the turbine outlet section 5 serves to guide the gas discharge. The air flow flows into the compressor turbine unit from the compressor inlet section 1, enters the compressor main body 2 through rectification and diffusion of the compressor inlet section 1, enters the compressor outlet gas collecting cavity 3 and then is discharged from the compressor outlet gas collecting cavity outlet section 8. In addition, the air flow flows into the turbine inlet gas collecting cavity 6 from the turbine inlet gas collecting cavity inlet section 9, then flows into the turbine main body 5, and finally is discharged out of the compressor turbine unit through the turbine outlet section 4.
The combustion chamber was isolated by the above design for the test operation, as shown in fig. 2. The combustion chamber comprises a combustion chamber inlet section 10, a combustion chamber main body 11 and a combustion chamber outlet section 12; the combustion chamber inlet section 10 and the combustion chamber outlet section 12 are respectively connected with one end of a combustion chamber inlet gas circuit pipeline 13 and one end of a combustion chamber outlet gas circuit pipeline 14 through flange structures designed at the end parts; the other ends of the combustion chamber inlet gas path pipeline 13 and the combustion chamber outlet gas path pipeline 14 are respectively connected with the outlet section 8 of the gas collecting cavity of the compressor outlet and the inlet section 9 of the gas collecting cavity of the turbine inlet through flange structures designed at the end parts, so that the compressor, the turbine and the combustion chamber are connected in series. The air flow is discharged out of the compressor main body 2 from the compressor outlet gas collecting cavity 3, enters the combustion chamber inlet section 10 through the combustion chamber inlet gas path pipeline 15, sequentially passes through the combustion chamber main body 11 and the combustion chamber outlet section 12, then enters the turbine inlet gas collecting cavity 6 through the combustion chamber outlet gas path pipeline 14, passes through the turbine main body 4, and finally is discharged out of the turbine outlet section 5. The gas circuit pipeline is used for serially mounting each part, so that each part can be separated by a distance, the arrangement of test equipment is facilitated, the test object can be conveniently mounted and debugged, and the influence of other parts on the test object is reduced.
When the combustion chamber is connected with the compressor turbine unit, the selection of the combustion chamber needs to enable the internal pressure and flow of the combustion chamber to be matched with the pressure and flow of the outlet section 6 of the gas collecting cavity at the outlet of the compressor in the compressor turbine unit connected with the combustion chamber.
As shown in FIG. 2, the test equipment comprises a pressure sensor 15 which is arranged at the rear part of the turbine body 4 and is used for measuring the rear pressure of the turbine body 2; a temperature sensor 16 is installed at the rear of the combustion chamber main body 11 for measuring the temperature at the rear of the combustion chamber main body 11; the PIV (particle image velocimetry) camera 17 is mounted in front of a transparent glass window 19 formed on a static part 18 of the turbine and can shoot the flow in the turbine body 4. The test object can be parts or components of a gas turbine such as a turbine blade, a compressor, a combustor, a turbine and the like, and can also be a system or a subsystem of the gas turbine such as an air system and the like.
Due to the limited supercharging capacity of a single compressor, for example, the supercharging ratio of the single compressor is about 5, if the test platform works at sea level by sucking air, the pressure of the compressor outlet collecting cavity 3, the combustion chamber and the turbine inlet collecting cavity 6 is about 5 atmospheric pressures, and the components work in the test environment. If a higher-pressure test environment is needed, a higher pressure ratio can be realized by serially mounting a plurality of air compressors, for example, 2 air compressors with a pressure ratio of about 5 are serially mounted, so that the pressure ratio can reach 25, and a part test with higher environmental pressure is carried out. The embedded series-mounting test platform of the gas turbine part, component and system designed by the invention can realize series mounting of multiple gas compressors, and the specific mode is as follows:
between two adjacent compressor turbine units, the compressor inlet section 1 of the rear compressor turbine unit is connected with the compressor outlet gas collecting cavity outlet section 8 of the front compressor turbine unit through a gas path pipeline in a flange connection mode. The turbine outlet section 5 of the rear compressor turbine unit is connected with the turbine inlet gas collecting cavity inlet section 9 of the front compressor turbine unit through a gas path pipeline in a flange connection mode. And finally, the tail end compressor turbine unit is connected with the combustion chamber in the mode. The size of the rear compressor turbine unit is determined by the pressure and the flow of the compressor outlet gas collecting cavity 3 of the front compressor turbine unit.
The foregoing multi-compressor series arrangement will be described by way of example below:
when a combustion chamber test is carried out and the test pressure of the combustion chamber is required to reach about 125 atmospheric pressures, 3 compressor turbine units and 1 combustion chamber are adopted and are arranged in series, as shown in figure 3.
Respectively arranging No. 1-No. 3 gas compressors on the 3 gas compressor turbine units 1 from front to back; the air compressor inlet section 1 of the No. 2 air compressor is connected with the air compressor outlet air collecting cavity outlet section 8 of the No. 1 air compressor through an air passage pipeline 20 of the No. 2 air compressor; the turbine outlet section 5 of the No. 2 gas compressor is connected with the turbine inlet gas collecting cavity inlet section 9 of the No. 1 gas compressor through a No. 2 turbine gas path pipeline 21; and finishing serial assembly of the No. 1 and No. 2 compressors. Similarly, the compressor inlet section 1 of the No. 3 compressor is connected with the compressor outlet gas collecting cavity outlet section 8 of the No. 2 compressor through the No. 3 compressor gas path pipeline 22; the turbine outlet section 5 of the No. 3 compressor is connected with the turbine inlet gas collecting cavity inlet section 9 of the No. 2 compressor through a No. 3 turbine gas path pipeline 23; and finishing serial assembly of the No. 2 and No. 3 compressors. The outlet section 8 of the compressor outlet gas collecting cavity of the No. 3 compressor and the inlet section 9 of the turbine inlet gas collecting cavity are respectively connected with the inlet section 10 of the combustion chamber and the outlet section 12 of the combustion chamber through an inlet gas path pipeline 24 of the combustion chamber and an outlet gas path pipeline 25 of the combustion chamber. The air flow flows in from the compressor No. 1, enters the compressor No. 2 through the compressor No. 1-compressor No. 2 air path pipeline 20, enters the compressor No. 3 through the compressor No. 2-compressor No. 3 air path pipeline 22, enters the combustion chamber through the compressor No. 3-combustion chamber inlet air path pipeline 24, then enters the turbine No. 3 through the combustion chamber-combustion chamber outlet air path pipeline 25-No. 3 turbine air path pipeline 23, enters the turbine No. 2 through the turbine No. 3-turbine No. 2 air path pipeline 21, finally enters the turbine No. 1 through the turbine No. 2-turbine air path pipeline 21 and is finally discharged. 3 compressor turbine units with different sizes are serially arranged through a gas path pipeline, very high pressure can be obtained after the No. 3 compressor, and the test working condition can be adjusted by changing the number of the serially arranged compressor turbine units or serially arranging the compressor turbine units with different parameters.
The embedded series test platform of the gas turbine part, part and system can also remove the gas collecting cavity 3 at the outlet of the gas compressor and the gas collecting cavity 6 at the inlet of the turbine under the condition of not leading a gas path pipeline, and then the gas compressor, the combustion chamber and the turbine are connected into a whole through the mounting edge 26, the bolt 27 and the nut 28, so that compact configuration gas flow is formed, enters the turbine through the combustion chamber after flowing in from the gas compressor and is finally discharged. The compact structure can be used for researching the mutual influence of the components (such as the turbine outer ring block, the bearing, the turbine disc and the like) under the condition of common work.
In summary, the test object of the embedded series test platform of the gas turbine parts, components and systems of the invention is not limited to the turbine, compressor and combustor, but can also be used for testing a part of the turbine (such as a turbine blade), or a small part (such as a turbine outer ring block), or other subsystems (such as an air system), and the parts are not separated by a pipeline mode, but can be directly tested in the test platform with a compact configuration.
The compact configuration test method will be described below by taking an example of the turbine outer ring block insertion test. Fig. 5 is an enlarged view of the turbine body 4 of the test platform, the turbine outer ring block 29 is positioned at the periphery of the turbine blade 30 and is installed on the turbine casing 31, the turbine outer ring block 29 is washed by high-temperature combustion gas, cooling air is needed for cooling to prevent the surface of the turbine outer ring block 29 from exceeding the allowable temperature of the material, and therefore measuring the surface temperature distribution of the turbine outer ring block 29 is the main purpose of the insert test of the turbine outer ring block 29. The turbine front pressure measuring point 32 and the turbine front temperature measuring point 33 respectively measure the gas pressure and the temperature in front of the turbine body 4; the turbine rear pressure measuring point 34 and the turbine rear temperature measuring point 35 respectively measure the gas pressure and the temperature behind the turbine body 4, thereby determining the working state and the working environment of the turbine body 4. A cooling air duct 36 passes cooling air into the interior of the turbine outer ring block 29, and a cooling air temperature measurement point 37 is used to measure the temperature of the cooling air. The surface of the turbine outer ring block 31 is provided with a turbine outer ring block surface temperature measuring point 38 for measuring the temperature distribution of the surface of the turbine outer ring block 29, so that whether the surface temperature of the turbine outer ring block 29 exceeds the allowable temperature of the material under various working states and working environments can be researched.
Claims (5)
1. The embedded series-mounted test platform of the gas turbine parts, components and systems comprises a gas compressor turbine unit, a combustion chamber and a gas path pipeline; the combustion chamber is characterized in that in the compressor turbine unit, a compressor, a combustion chamber and a turbine are serially arranged through gas path pipelines.
2. The in-line tandem test platform for gas turbine parts, components and systems according to claim 1, wherein: the gas collecting cavity is arranged at the outlet of the gas compressor; the air flow flows into a compressor turbine unit from an inlet section of a compressor, enters a compressor main body through rectification and diffusion of the inlet section of the compressor, then enters a gas collecting cavity at an outlet of the compressor and is discharged from an outlet section of the gas collecting cavity at the outlet of the compressor;
a turbine inlet gas collecting cavity is arranged at the turbine inlet; the gas flow flows into the turbine inlet gas collecting cavity from the inlet section of the turbine inlet gas collecting cavity, then flows into the turbine main body, and finally is discharged through the turbine outlet section;
the outlet section of the gas collecting cavity at the outlet of the gas compressor and the inlet section of the gas collecting cavity at the inlet of the turbine are respectively connected with the inlet section and the outlet section of the combustion chamber through the inlet gas path pipeline and the outlet gas path pipeline of the combustion chamber; the gas flow is discharged out of the compressor main body from the compressor outlet gas collecting cavity, enters the combustion chamber inlet section through the combustion chamber inlet gas path pipeline, sequentially passes through the combustion chamber main body and the combustion chamber outlet section, and then enters the turbine inlet gas collecting cavity through the combustion chamber outlet gas path pipeline.
3. The in-line tandem test platform for gas turbine parts, components and systems according to claim 1, wherein: serially mounting the compressor turbine units with different sizes through a gas path pipeline so as to adjust the test working condition or obtain higher test pressure; between two adjacent compressor turbine units, the compressor inlet section of the rear compressor turbine unit is connected with the compressor outlet gas collecting cavity outlet section of the front compressor turbine unit through a gas path pipeline; the turbine outlet section of the rear compressor turbine unit is connected with the turbine inlet gas collecting cavity inlet section of the front compressor turbine unit through a gas path pipeline; and finally, the outlet section of a compressor outlet gas collecting cavity and the inlet section of a turbine inlet gas collecting cavity of the tail end compressor turbine unit are respectively connected with the inlet section and the outlet section of the combustion chamber through an inlet gas path pipeline and an outlet gas path pipeline of the combustion chamber.
4. The in-line tandem test platform for gas turbine parts, components and systems according to claim 1, wherein: the test equipment is respectively a pressure sensor for measuring the pressure at the back of the turbine; a temperature sensor for measuring a temperature of a rear portion of the combustion chamber main body; and the PIV camera is used for shooting the flow inside the turbine main body.
5. The in-line tandem test platform for gas turbine engine parts, components and systems according to claim 2, wherein: the gas collecting cavity at the outlet of the gas compressor, the gas collecting cavity at the inlet of the turbine and the gas path pipeline are all detachable structures, and the gas compressor, the combustion chamber and the turbine are changed into a direct connection mode after being detached, so that a compact configuration is formed.
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| CN202110272231 | 2021-03-12 |
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| CN113267342B CN113267342B (en) | 2022-03-04 |
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Cited By (1)
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| CN114216685A (en) * | 2021-10-20 | 2022-03-22 | 中国航发四川燃气涡轮研究院 | Main combustion chamber component test piece for simulating radial velocity field of outlet of gas compressor |
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| CN113267342B (en) | 2022-03-04 |
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