CN114544187B - A device system and method for testing the cooling effect of gas turbine blades - Google Patents
A device system and method for testing the cooling effect of gas turbine blades Download PDFInfo
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- CN114544187B CN114544187B CN202210135307.7A CN202210135307A CN114544187B CN 114544187 B CN114544187 B CN 114544187B CN 202210135307 A CN202210135307 A CN 202210135307A CN 114544187 B CN114544187 B CN 114544187B
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- 238000001816 cooling Methods 0.000 title claims abstract description 243
- 238000012360 testing method Methods 0.000 title claims abstract description 218
- 230000000694 effects Effects 0.000 title claims abstract description 64
- 238000000034 method Methods 0.000 title claims abstract description 35
- 238000002485 combustion reaction Methods 0.000 claims abstract description 84
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 48
- 238000010248 power generation Methods 0.000 claims abstract description 41
- 230000003068 static effect Effects 0.000 claims abstract description 13
- 239000007789 gas Substances 0.000 claims description 181
- 239000002184 metal Substances 0.000 claims description 31
- 230000001105 regulatory effect Effects 0.000 claims description 28
- 239000000498 cooling water Substances 0.000 claims description 18
- 239000002918 waste heat Substances 0.000 claims description 16
- 239000002737 fuel gas Substances 0.000 claims description 8
- 239000000567 combustion gas Substances 0.000 claims 4
- 239000000446 fuel Substances 0.000 description 7
- 230000001502 supplementing effect Effects 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 4
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 238000004378 air conditioning Methods 0.000 description 2
- 239000010963 304 stainless steel Substances 0.000 description 1
- 229920000742 Cotton Polymers 0.000 description 1
- 229910000589 SAE 304 stainless steel Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000010926 purge Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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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
- G01M13/00—Testing of machine parts
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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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
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Abstract
本发明涉及一种用于燃气轮机透平叶片冷却效果试验的装置系统和方法，所述装置系统包括燃烧发电单元、空气冷却单元、试验单元和水冷单元；所述燃烧发电单元中燃烧室的出口与试验单元连接；所述燃烧发电单元中压气机的出口与空气冷却单元连接；所述空气冷却单元的出口与试验单元连接；所述水冷单元的出口分别与试验单元和燃烧发电单元连接；所述试验单元的出口与燃烧发电单元连接。所述方法采用所述装置系统，以燃烧室的燃气为主流燃气，以压气机的空气为冷却空气，进行透平叶片冷却效果试验。本发明提供的装置系统结构简单，减少了试验装置的设备购置费以及耗电费用，可以用来进行透平静叶片、动叶片的全温全压全尺寸试验，能量利用效率高。
The present invention relates to a device system and method for testing the cooling effect of gas turbine blades, the device system comprising a combustion power generation unit, an air cooling unit, a test unit and a water cooling unit; the outlet of the combustion chamber in the combustion power generation unit is connected to the test unit; the outlet of the compressor in the combustion power generation unit is connected to the air cooling unit; the outlet of the air cooling unit is connected to the test unit; the outlet of the water cooling unit is respectively connected to the test unit and the combustion power generation unit; the outlet of the test unit is connected to the combustion power generation unit. The method adopts the device system, uses the combustion chamber gas as the mainstream gas, and uses the compressor air as the cooling air to conduct a turbine blade cooling effect test. The device system provided by the present invention has a simple structure, reduces the equipment purchase cost and power consumption cost of the test device, and can be used to conduct full-temperature, full-pressure and full-scale tests of turbine static blades and moving blades, with high energy utilization efficiency.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a device system and a method for testing the cooling effect of turbine blades of a gas turbine.
Background
The turbine blade cooling design technology belongs to the key technology of a gas turbine, and is a core technology for improving the turbine inlet temperature, improving the efficiency of the gas turbine, prolonging the service life of a hot end part and guaranteeing the long-period stable and safe operation of the gas turbine.
The international heavy advanced gas turbine is continuously developed towards high parameters, high performance and low pollution, and the important points include further providing higher turbine inlet temperature and actively developing more advanced high-temperature materials and cooling technologies. The full Wen Quanya full-size cooling effect verification test is developed aiming at the turbine blade which is newly designed and processed, and is an important link for developing the gas turbine.
With the continuous rise of the turbine inlet temperature, the existing test stand is difficult to meet the requirements of full Wen Quanya full-size tests of advanced gas turbines, and additionally, a fuel supply system for tests, a combustion chamber for tests, an air electric heater, a main flow air compressor, a cooling air compressor, an air electric heater and other systems or devices are required to be additionally added, so that the purchase cost and the power consumption cost of the devices are greatly increased, and the energy utilization rate is low.
CN105588712a discloses a turbine blade cooling effect test device and method using gas compressor of gas turbine to exhaust, the device uses the exhaust gas of gas compressor as main stream air and burns to form main stream gas, and it needs to set fuel supply system and test combustion chamber, its equipment acquisition cost is expensive, and it is unfavorable for economical efficiency of production.
CN213985690U discloses a gas turbine combustion and turbine comprehensive cooling effect test system, the test system needs to mix main air and fuel in a combustion test section to generate high-temperature high-pressure gas, and needs to simulate the real working environment of a combustion chamber when the gas turbine is running, and the blade cooling effect is obtained by measuring the parameters of gas and cool air and the wall temperature of the outer surface of the blade.
Therefore, a device system and a method for turbine blade cooling effect test which meet the requirements of a full Wen Quanya full-size test of a gas turbine and have simple structure and low cost are important in economic value and use value.
Disclosure of Invention
Compared with the prior art, the device system provided by the invention not only meets the actual working condition of test parameters, but also can reduce equipment investment for test, reduce pollution emission generated by test, improve energy utilization efficiency and reduce the influence of the test on the power of the gas turbine.
In order to achieve the aim of the invention, the invention adopts the following technical scheme:
in a first aspect, the invention provides a device system for testing the cooling effect of turbine blades of a gas turbine, which comprises a combustion power generation unit, an air cooling unit, a test unit and a water cooling unit, wherein an outlet of a combustion chamber in the combustion power generation unit is connected with the test unit, an outlet of a gas compressor in the combustion power generation unit is connected with the air cooling unit, an outlet of the air cooling unit is connected with the test unit, an outlet of the water cooling unit is respectively connected with the test unit and the combustion power generation unit, and an outlet of the test unit is connected with the combustion power generation unit.
According to the invention, through the mutual matching of the combustion power generation unit, the air cooling unit, the test unit and the water cooling unit, the full-Wen Quanya full-size turbine blade cooling effect test with high parameters can be realized, for example, the temperature reaches 1500 ℃, the pressure reaches 2.3MPa, and the turbine blade is tested under the condition of full-size blades, the invention is connected with the test unit through the outlet of the combustion chamber in the combustion power generation unit, part of high-temperature high-pressure gas generated by the combustion chamber is used as main stream gas for testing, the invention is connected with the air cooling unit through the outlet of the compressor in the combustion power generation unit, part of air generated by the compressor is used as cooling air for testing, and finally, the turbine blade cooling effect test is completed in the test unit, so that the parameters of the main stream gas and the cooling air are completely consistent with the working condition of the product, and the equipment investment and the electricity consumption cost are greatly reduced. According to the invention, the outlet of the test unit is connected with the combustion power generation unit, so that the mixed gas generated after the test is returned to the combustion power generation unit again for recycling, the mixed gas can enter the gas-steam combined cycle bottom circulation, the utilization efficiency of the residual heat of the mixed gas is improved, and the output of the gas turbine combined cycle unit under the test working condition is improved.
Preferably, the combustion power generation unit comprises a compressor, a combustion chamber, a power generation turbine, a gas turbine exhaust pipeline and a waste heat boiler which are sequentially connected along the gas flow direction.
The combustion power generation unit is based on a gas turbine power plant, and performs a cooling effect test of turbine blades by utilizing high-temperature gas generated by an original gas turbine of the power plant and compressed air generated by an original gas compressor, so that compared with an independent full-pressure full-temperature full-size turbine blade cooling effect test bed, the equipment investment can be remarkably reduced.
Preferably, the air cooling unit includes a cooling air intake valve, a cooling air conditioning valve, and a cooling air flow meter connected in this order in a cooling air flow direction.
Preferably, the test unit comprises a main stream gas inlet valve, a main stream gas regulating valve, a compensator, a turbine blade test device, an exhaust attemperator, an exhaust flowmeter and an exhaust butterfly valve which are connected in sequence along the gas flow direction.
In the invention, the compensator is arranged before the turbine blade test device and is used for absorbing the expansion amount of the air inlet pipeline.
Preferably, the outlet of the combustion chamber of the combustion generating unit is connected with the main stream gas inlet valve of the test unit.
Preferably, the outlet of the compressor of the combustion power generation unit is connected with a cooling air inlet valve of an air cooling unit.
Preferably, the outlet of the cooling air flow meter of the air cooling unit is connected to a turbine blade test device of the test unit.
Preferably, the outlet of the exhaust butterfly valve of the test unit is connected with the gas turbine exhaust pipeline of the combustion power generation unit.
Preferably, the outlet pipe of the combustion chamber is in communication with the inlet pipe of the turbine blade testing apparatus and is a double-layer pipe.
Preferably, the outlet pipe of the turbine blade test apparatus and the inlet pipe of the exhaust attemperator are communicated and are each double-layer pipes.
In the invention, the double-layer pipeline comprises a tube side and a shell side, a high-temperature alloy double-layer cooling structure is adopted, cooling water enters the shell side to cool and protect the pipeline, and the pipeline behind the exhaust attemperator is 304 stainless steel.
Preferably, the housing of the turbine blade test apparatus comprises a double layer structure.
In the invention, the shell of the turbine blade test device is of a double-layer structure, and a heat insulation material is additionally arranged between the double-layer shells, and is generally high silica fiber cotton felt.
Preferably, the water cooling unit comprises a water supplementing component and a cooling tower which are sequentially connected along the water flow direction.
Preferably, the water replenishing component comprises a water replenishing pipeline and a water replenishing valve.
In the invention, cooling water can be supplemented to the cooling tower through the water supplementing pipeline.
In the invention, the water cooling unit further comprises a water pump, a water outlet component and a water inlet component, wherein the water outlet component comprises a water outlet pipeline and a valve, and the water inlet component comprises a water inlet pipeline and a valve.
Preferably, the outlet of the cooling tower is connected to the shell side of the outlet pipe of the combustion chamber.
Preferably, the outlet of the cooling tower is connected with the shell side of the inlet pipe of the exhaust attemperator.
Preferably, the inlet of the cooling tower is connected to the shell side of the inlet pipe of the turbine blade test apparatus.
Preferably, the inlet of the cooling tower is connected to the shell side of the outlet pipe of the turbine blade test apparatus.
According to the invention, the outlet of the cooling tower is connected with the shell side of the outlet pipe of the combustion chamber, and the inlet of the cooling tower is connected with the shell side of the inlet pipe of the turbine blade testing device, so that cooling water can flow from the outlet of the combustion chamber to the inlet of the turbine blade testing device in the shell side of the double-layer pipeline, and then returns to the cooling tower, thereby completing the cooling protection of the pipeline.
According to the invention, the outlet of the cooling tower is connected with the shell side of the inlet pipe of the exhaust desuperheater, and the inlet of the cooling tower is connected with the shell side of the outlet pipe of the turbine blade test device, so that cooling water can flow from the inlet of the exhaust desuperheater to the outlet of the turbine blade test device in the shell side of the double-layer pipeline, and then returns to the cooling tower, thereby completing the cooling protection of the pipeline.
Preferably, the outlet of the cooling tower is connected to the interior of the exhaust attemperator.
In the invention, the outlet of the cooling tower is connected with the interior of the exhaust attemperator, so that cooling water can be directly sprayed into the exhaust attemperator to cool the mixed gas.
Preferably, the turbine blade testing apparatus includes at least one stage of a turbine blade set, which may be, for example, a stage one, a stage two, a stage three, or a stage four, but is not limited to the values recited, and other values not recited in the range of values are equally applicable.
Preferably, the turbine blade assembly comprises a turbine vane assembly and/or a turbine blade assembly.
According to the invention, at least one stage of turbine blade group is arranged, and the turbine blade group comprises the turbine stator blade group and the turbine rotor blade group, so that the static cooling effect test of the full-size turbine stator blades can be independently carried out, the static cooling effect test of the full-size turbine rotor blades can be independently carried out, and the turbine stator blade group and the turbine rotor blade group can be connected in series to carry out a combined test.
Preferably, the turbine vane assembly includes at least 4 full-sized turbine vanes, such as 4, 5 or 6, but not limited to the recited values, and other non-recited values within the range of values are equally applicable.
Preferably, the turbine vane set includes at least 3 vane passages, which may be, for example, 3, 4 or 5, but is not limited to the recited values, as other non-recited values within the range of values are equally applicable.
Preferably, the turbine rotor blade set comprises at least 7 full-sized turbine blades, which may be, for example, 7, 8 or 9, but is not limited to the values recited, and other values not recited in the numerical range are equally applicable.
Preferably, the turbine rotor blade set includes at least 6 blade channels, which may be, for example, 6, 7 or 8, but is not limited to the recited values, and other non-recited values within the range of values are equally applicable.
In the invention, two blades at the outermost side are accompanied blades, and the other blades in the middle are test blades.
Preferably, the turbine blade test apparatus is provided with turbine blade internal cooling passages.
According to the invention, the cooling air cools the turbine blade through the cooling channel inside the turbine blade, the turbine blade cooling test is carried out, and the obtained pressure data, temperature data and flow data are collected and analyzed through the instrument and the equipment, so that the cooling effect of the turbine blade is obtained.
In the invention, temperature measuring points and pressure measuring points are arranged at the front end and the rear end of the turbine blade testing device.
In the invention, the temperature of main stream fuel gas is measured by a temperature probe, the metal surface temperature of the turbine blade is measured by a miniature armored thermocouple, a groove is formed on the surface of the turbine blade, the thermocouple is embedded, then the groove is filled up by plasma spraying, and the accuracy of a prototype surface is recovered after polishing.
In a second aspect, the present invention provides a method for gas turbine blade cooling effect testing employing a device system for gas turbine blade cooling effect testing according to the first aspect of the present invention.
The method comprises the following steps:
Extracting gas generated by a combustion chamber as main stream gas, extracting air generated by a gas compressor as cooling air, performing a turbine blade cooling effect test, generating mixed gas, and obtaining test data of a cooling effect;
Cooling water is adopted to cool and protect the pipeline in the turbine blade cooling effect test;
and cooling water is also adopted in the turbine blade cooling effect test to cool the mixed gas, and the cooled mixed gas is subjected to waste heat utilization to generate steam.
According to the invention, the gas generated by the combustion chamber is taken as main flow gas, the air generated by the air compressor is taken as cooling air, and the turbine blade cooling effect test is carried out, so that the parameters of the main flow gas and the cooling air are completely consistent with the working condition of the product, the equipment investment and the power consumption cost are reduced.
Preferably, the main stream gas is extracted from the combustion chamber, and sequentially passes through the main stream gas inlet valve, the main stream gas regulating valve and the compensator to enter the turbine blade test device for turbine blade cooling effect test.
Preferably, the cooling air is extracted from the air compressor, sequentially passes through the cooling air inlet valve, the cooling air regulating valve and the cooling air flowmeter to enter the turbine blade test device, and then the turbine blade cooling effect test is carried out.
Preferably, the cooling air enters the cooling channel inside the turbine blade from the top of the stator blade and/or the root of the moving blade in the turbine blade test device, and the turbine blade cooling effect test is carried out.
Preferably, the mixed gas enters a waste heat boiler through an exhaust attemperator, an exhaust flowmeter, an exhaust butterfly valve and a gas turbine exhaust pipeline to perform waste heat utilization and generate steam.
Preferably, the flow rate of the main stream gas is controlled by a main stream gas inlet valve and a main stream gas regulating valve.
Preferably, the pressure of the main stream gas is controlled by an exhaust butterfly valve.
Preferably, the flow rate of the cooling air is controlled by a cooling air intake valve and a cooling air conditioning valve.
Preferably, the flow rate of the main stream gas in each turbine blade set is 5.71-5.83% of the total flow rate of the combustion chamber outlet gas, for example, 5.71%, 5.72%, 5.73%, 5.74%, 5.75%, 5.76%, 5.77%, 5.78%, 5.79%, 5.80%, 5.81%, 5.82% or 5.83%, but not limited to the recited values, and other non-recited values in the range of values are equally applicable.
Preferably, the flow rate of the cooling air in each stage of the turbine blade set is 0.43-0.58% of the total flow rate of the compressor outlet air, and may be, for example, 0.43%, 0.44%, 0.46%, 0.48%, 0.50%, 0.52%, 0.54%, 0.56% or 0.58%, but is not limited to the recited values, and other non-recited values within the numerical range are equally applicable.
Preferably, the test data includes a metal surface temperature of the turbine blade, a temperature of the main flow gas before the turbine blade test apparatus, a pressure of the main flow gas before the turbine blade test apparatus, an outlet static pressure of the turbine blade test apparatus, a flow rate of the mixed gas after the turbine blade test apparatus, a temperature of the cooling air before the turbine blade test apparatus, a pressure of the cooling air before the turbine blade test apparatus, and a flow rate of the cooling air before the turbine blade test apparatus.
Preferably, the metal surface temperature of the turbine blade comprises a blade body metal wall temperature of the turbine blade, an upper endwall metal surface temperature of the turbine stator blade, a lower endwall metal surface temperature of the turbine stator blade and a platform metal surface temperature of the turbine blade.
As a preferred embodiment of the second aspect of the present invention, the method includes the steps of:
Extracting main flow gas from a combustion chamber, sequentially passing through a main flow gas inlet valve, a main flow gas regulating valve and a compensator to enter a turbine blade test device, extracting cooling air from a gas compressor, sequentially passing through a cooling air inlet valve, a cooling air regulating valve and a cooling air flowmeter to enter the turbine blade test device, and enabling the cooling air to enter a cooling channel in the turbine blade from the top of a stator blade and/or the root of a rotor blade to perform a turbine blade cooling effect test to generate mixed gas and obtain test data of a cooling effect;
in the turbine blade cooling effect test, cooling water enters from an outlet pipe of a combustion chamber, flows out from an inlet pipe of a turbine blade test device along a shell pass of a double-layer pipeline and returns to a cooling tower, and cooling water also enters from an inlet pipe of an exhaust attemperator, flows out from an outlet pipe of the turbine blade test device along the shell pass of the double-layer pipeline and returns to the cooling tower to finish cooling protection of the pipeline;
In the turbine blade cooling effect test, cooling water is further adopted to enter the exhaust attemperator to cool the mixed gas to the temperature of less than 700 ℃, and the cooled mixed gas enters the waste heat boiler through an exhaust flowmeter, an exhaust butterfly valve and a gas turbine exhaust pipeline to perform waste heat utilization to generate steam;
The flow of the main stream gas is controlled by a main stream gas inlet valve and a main stream gas regulating valve, the pressure of the main stream gas is controlled by an exhaust butterfly valve, the flow of the cooling air is controlled by a cooling air inlet valve and a cooling air regulating valve, the flow of the main stream gas in each turbine blade group accounts for 5.71-5.83% of the total flow of the combustion chamber outlet gas, and the flow of the cooling air in each turbine blade group accounts for 0.43-0.58% of the total flow of the compressor outlet gas;
The test data comprise the metal surface temperature of the turbine blade, the temperature of main flow gas before the turbine blade test device, the pressure of main flow gas before the turbine blade test device, the outlet static pressure of the turbine blade test device, the flow of mixed gas after the turbine blade test device, the temperature of cooling air before the turbine blade test device, the pressure of cooling air before the turbine blade test device and the flow of cooling air before the turbine blade test device, wherein the metal surface temperature of the turbine blade comprises the blade body metal wall temperature of the turbine blade, the upper end wall metal surface temperature of the turbine stator blade, the lower end wall metal surface temperature of the turbine stator blade and the platform metal surface temperature of the turbine movable blade.
Compared with the prior art, the invention has the following beneficial effects:
(1) Compared with an independent full-pressure full-temperature full-size turbine blade cooling effect test bed, the device for testing the cooling effect of the turbine blade of the gas turbine is simple in structure, reduces the settings of a fuel supply system for testing, a combustion chamber for testing, an air electric heater, a main flow air compressor, a cooling air compressor, an air electric heater and the like, and reduces the equipment purchase cost of the testing device and the power consumption cost of high-pressure compression equipment and the air electric heater.
(2) The method for testing the cooling effect of the turbine blade of the gas turbine provided by the invention takes part of the gas generated by the combustion chamber as main flow gas and part of the air generated by the gas compressor as cooling air, so that the parameters of the cooling effect test of the turbine blade are completely consistent with the actual working conditions, and the method can be used for carrying out full Wen Quanya full-size test of the turbine stator blade and the moving blade.
(3) According to the method for testing the cooling effect of the turbine blade of the gas turbine, the mixed gas after testing is reinjected into the combustion power generation unit, so that the mixed gas enters the gas-steam combined cycle bottom circulation, the utilization efficiency of the residual heat of the mixed gas is improved, and the output of the gas turbine combined cycle unit under the test working condition is improved.
Drawings
FIG. 1 is a schematic illustration of the apparatus system for testing the cooling effect of a turbine blade of a gas turbine according to example 1 of the present invention.
Fig. 2 is a schematic view of a first stage rotor blade set according to embodiment 1 of the present invention.
The system comprises a 1-combustion power generation unit, a 2-air cooling unit, a 3-test unit, a 4-water cooling unit, a 5-combustion chamber, a 6-compressor, a 7-power generation turbine, an 8-gas turbine exhaust pipeline, a 9-cooling air inlet valve, a 10-cooling air regulating valve, an 11-cooling air flowmeter, a 12-main flow gas inlet valve, a 13-main flow gas regulating valve, a 14-compensator, a 15-turbine blade test device, a 16-exhaust desuperheater, a 17-exhaust flowmeter, an 18-exhaust butterfly valve, a 19-water supplementing pipeline and valve, a 20-cooling tower, a 21-water pump, a 22-water outlet pipeline and valve, a 23-water inlet pipeline and valve and a 24-first-stage moving blade set.
Detailed Description
The technical scheme of the invention is further described by the following specific embodiments. It will be apparent to those skilled in the art that the examples are merely to aid in understanding the invention and are not to be construed as a specific limitation thereof.
Example 1
The embodiment provides a device system for testing the cooling effect of turbine blades of a gas turbine, which comprises a combustion power generation unit 1, an air cooling unit 2, a test unit 3 and a water cooling unit 4, wherein an outlet of a combustion chamber 5 in the combustion power generation unit 1 is connected with the test unit 3, an outlet of a gas compressor 6 in the combustion power generation unit 1 is connected with the air cooling unit 2, an outlet of the air cooling unit 2 is connected with the test unit 3, an outlet of the water cooling unit 4 is respectively connected with the test unit 3 and the combustion power generation unit 1, and an outlet of the test unit 3 is connected with the combustion power generation unit 1.
The combustion power generation unit 1 comprises a compressor 6, a combustion chamber 5, a power generation turbine 7, a gas turbine exhaust pipeline 8 and a waste heat boiler which are sequentially connected along the gas flow direction, the air cooling unit 2 comprises a cooling air inlet valve 9, a cooling air regulating valve 10 and a cooling air flowmeter 11 which are sequentially connected along the cooling air flow direction, and the test unit 3 comprises a main flow gas inlet valve 12, a main flow gas regulating valve 13, a compensator 14, a turbine blade test device 15, an exhaust attemperator 16, an exhaust flowmeter 17 and an exhaust butterfly valve 18 which are sequentially connected along the gas flow direction;
The outlet of the combustion chamber 5 of the combustion power generation unit 1 is connected with the main flow gas inlet valve 12 of the test unit 3, the outlet of the gas compressor 6 of the combustion power generation unit 1 is connected with the cooling air inlet valve 9 of the air cooling unit 2, the outlet of the cooling air flow meter 11 of the air cooling unit 2 is connected with the turbine blade test device 15 of the test unit 3, the outlet of the exhaust butterfly valve 18 of the test unit 3 is connected with the gas turbine exhaust pipeline 8 of the combustion power generation unit 1, the outlet pipe of the combustion chamber 5 is communicated with the inlet pipe of the turbine blade test device 15 and is a double-layer pipeline, the outlet pipe of the turbine blade test device 15 and the inlet pipe of the exhaust attemperator 16 are communicated and are double-layer pipelines, and the shell of the turbine blade test device 15 is of a double-layer structure;
The water cooling unit 4 comprises a water supplementing component and a cooling tower 20 which are sequentially connected along the water flow direction, wherein the water supplementing component comprises a water supplementing pipeline and a valve 19, the water cooling unit 4 further comprises a water pump 21, a water outlet component and a water inlet component, the water outlet component comprises a water outlet pipeline and a valve 22, the water inlet component comprises a water inlet pipeline and a valve 23, the outlet of the cooling tower 20 is connected with the shell side of the outlet pipe of the combustion chamber 5, the outlet of the cooling tower 20 is connected with the shell side of the inlet pipe of the exhaust attemperator 16, the inlet of the cooling tower 20 is connected with the shell side of the inlet pipe of the turbine blade test device 15, the inlet of the cooling tower 20 is connected with the shell side of the outlet pipe of the turbine blade test device 15, and the outlet of the cooling tower 20 is connected with the interior of the exhaust attemperator 16;
The turbine blade test apparatus 15 includes a first stage turbine blade set including a turbine vane set (denoted as a first stage vane set) including 4 full-size turbine blades and 3 blade runners and a turbine blade set (denoted as a first stage blade set 24) including 7 full-size turbine blades and 6 blade runners as shown in FIG. 2.
The embodiment also provides a method for testing the cooling effect of turbine blades of a gas turbine by using the device system, which comprises the following steps:
Extracting main flow gas from a combustion chamber 5, sequentially passing through a main flow gas inlet valve 12, a main flow gas regulating valve 13 and a compensator 14 to enter a turbine blade test device 15, extracting cooling air from a gas compressor 6, sequentially passing through a cooling air inlet valve 9, a cooling air regulating valve 10 and a cooling air flowmeter 11 to enter the turbine blade test device 15, and allowing the cooling air to enter a cooling channel inside a turbine blade from the top of a stator blade and the root of a rotor blade to perform a turbine blade cooling effect test to generate mixed gas and obtain test data of the cooling effect;
In the turbine blade cooling effect test, cooling water enters from an outlet pipe of the combustion chamber 5, flows out from an inlet pipe of the turbine blade test device 15 along a shell side of a double-layer pipeline and returns to the cooling tower 20, and cooling water also enters from an inlet pipe of the exhaust attemperator 16, flows out from an outlet pipe of the turbine blade test device 15 along the shell side of the double-layer pipeline and returns to the cooling tower 20 to finish cooling protection of the pipeline;
In the turbine blade cooling effect test, cooling water is further adopted to enter the exhaust attemperator 16 to cool the mixed gas to 650 ℃, and the cooled mixed gas enters the waste heat boiler through the exhaust flowmeter 17, the exhaust butterfly valve 18 and the gas turbine exhaust pipeline to perform waste heat utilization to generate steam;
The flow rate of the main flow gas is controlled by a main flow gas inlet valve and a main flow gas regulating valve, the pressure of the main flow gas is controlled by an exhaust butterfly valve 18, the flow rate of the cooling air is controlled by a cooling air inlet valve and a cooling air regulating valve, the flow rate of the main flow gas in a first-stage stationary blade set is 5.71% of the total flow rate of the gas at the outlet of a combustion chamber 5, the flow rate of the cooling air is 0.58% of the total flow rate of the air at the outlet of a compressor 6, the flow rate of the main flow gas in a first-stage moving blade set 24 is 5.83% of the total flow rate of the gas at the outlet of the combustion chamber 5, and the flow rate of the cooling air is 0.43% of the total flow rate of the air at the outlet of the compressor 6;
The test data comprise the metal surface temperature of the turbine blade, the temperature of main flow gas before the turbine blade test device 15, the pressure of main flow gas before the turbine blade test device 15, the outlet static pressure of the turbine blade test device 15, the flow of mixed gas after the turbine blade test device 15, the temperature of cooling air before the turbine blade test device 15, the pressure of cooling air before the turbine blade test device 15 and the flow of cooling air before the turbine blade test device 15, wherein the metal surface temperature of the turbine blade comprises the blade body metal wall temperature of the turbine blade, the upper end wall metal surface temperature of the turbine stator blade, the lower end wall metal surface temperature of the turbine stator blade and the platform metal surface temperature of the turbine rotor blade.
With the above system and method, the calculation results of the main stream gas flow and the cold zone gas flow are shown in Table 1, for a certain model of 400MW G/H gas turbine, with a compressor inlet air flow of 855kg/s and a combustor fuel flow of 20 kg/s.
TABLE 1
As can be seen from table 1, in the device system and method provided in this embodiment, in the first stage stator blade set and the first stage rotor blade set, the flow of the main flow gas is less than 5.83% of the total flow of the gas at the outlet of the combustion chamber, and the flow of the cooling gas is less than 0.58% of the total flow of the air at the outlet of the compressor, so that the safe operation of the gas turbine of the power plant is not affected.
Compared with an independent full-pressure full-temperature full-size turbine blade cooling effect test bed, the embodiment can reduce a fuel supply system for tests, a combustion chamber, a main flow air compressor, a cooling air compressor and an air electric heater, wherein the reduced fuel supply system comprises a regulating valve station, a heating device, a cutting valve group, a regulating valve group, a measuring device, a nitrogen purging device and the like.
Compared with an independent full-pressure full-temperature full-size turbine blade cooling effect test bed, the device purchase cost can be saved by 5000-9000 kiloyuan, the power of the devices is 25000-30000kW, 5 working conditions are made according to a turbine blade cooling effect test, each working condition is calculated according to 1 hour, test power consumption is 125000 kW.h-150000 kW.h, and if industrial power consumption is calculated according to power consumption cost of 0.9 yuan/kW.h, 112500-135000 yuan can be saved by adopting the device system and the method provided by the embodiment.
Compared with an independent full-pressure full-temperature full-size turbine blade cooling effect test bed, the device system and the method provided by the embodiment improve the output of a turbine by 6% by utilizing the mixed gas to enter the waste heat boiler, and can increase the power generation by 12MW in the test period according to the output of the turbine being 200 MW.
In summary, the device system for the cooling effect test of the turbine blade of the gas turbine can save equipment cost and power consumption cost, and the method for the cooling effect test of the turbine blade of the gas turbine can improve the utilization efficiency of capacity and the output of the combined cycle unit of the gas turbine under test working conditions.
The applicant declares that the above is only a specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and it should be apparent to those skilled in the art that any changes or substitutions that are easily conceivable within the technical scope of the present invention disclosed by the present invention fall within the scope of the present invention and the disclosure.
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| CN207178041U (en) * | 2017-07-31 | 2018-04-03 | 中国电力工程顾问集团西北电力设计院有限公司 | A kind of OTC cooling systems for Combined cycle gas-steam turbine |
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| CN207178041U (en) * | 2017-07-31 | 2018-04-03 | 中国电力工程顾问集团西北电力设计院有限公司 | A kind of OTC cooling systems for Combined cycle gas-steam turbine |
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