CN209656289U - A kind of multifunctional modular test bench for gas turbine - Google Patents
A kind of multifunctional modular test bench for gas turbine Download PDFInfo
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- CN209656289U CN209656289U CN201920389499.8U CN201920389499U CN209656289U CN 209656289 U CN209656289 U CN 209656289U CN 201920389499 U CN201920389499 U CN 201920389499U CN 209656289 U CN209656289 U CN 209656289U
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Abstract
The utility model discloses a kind of modular multi-function test bench for gas turbine, including at least gear-box, compressor installation station, turbine installation station and combustion chamber, wherein gear-box includes at least a high speed shaft and at least one slow-speed shaft, one end of the high speed shaft is used for joint test compressor for connecting turning motor, the other end；The slow-speed shaft starts power source or driving power source or load for connecting；Compressor installs station and is provided with gas handling system and inlet plenum for installing test compressor, the compressor installation station；Turbine installation station is provided with exhaust casing, exhaust chamber and exhaust system for installing turbine, the turbine installation station；Combustion chamber is equipped with flange-interface, and the flange-interface includes at least burner inner liner and fuel nozzle for connecting bored plate flange or fuel assembly, the fuel assembly.Compressor test, complete machine no load test, the test of complete machine full load and the operation test in follow-up test power station are carried out by the above-mentioned same testing stand.
Description
Technical field
The utility model relates to a kind of testing stands for gas turbin test, for realizing on the same test bench location
Carry out Compressor test, complete machine no load test, the test of complete machine full load and the operation test in follow-up test power station.
Background technique
Experimental study is to carry out the important method of turbomachine fluidal texture and performance evaluation, it can comprehensively consider influence stream
Dynamic various factors, it is as a result objective reliable.Compressor test can be used for instructing, study and designing compressor, and identification target is calmed the anger
The validity of machine；After combustion engine is completed, need to carry out combustion engine complete machine no load test, main purpose is to examine unit fortune
Row, vibration and thermodynamic property；For the type newly developed, need to test by complete machine full speed full load to investigate combustion comprehensively
The runnability of machine obtains the operating status and heating power data of true reflection complete machine by online experimental study, whole to assess
Machine performance；The long-term reliability of unit can be verified by experimental power station.
Test is an essential link in gas turbine design, and the type needs newly developed are carried out
The case where test for stating several stages generally requires to build multiple test platforms, and there are some equipment and system repeated construction.
Summary of the invention
The technical problems to be solved in the utility model is the multiple experimental stage needs for solving gas turbine in the prior art
Multiple test platforms are built, the defect of some equipment and system repeated construction is caused.
In order to solve the above-mentioned technical problem, a kind of the technical scheme that the utility model is provided is as follows: multifunctional modular combustion
Gas-turbine testing stand, includes at least:
Gear-box, the gear-box include at least a high speed shaft and at least one slow-speed shaft, one end of the high speed shaft
For connecting turning motor, the other end is used for joint test compressor；The slow-speed shaft starts power source or driving for connecting
Power source or load；
Compressor installs station, and the compressor installation station is for installing test compressor, the compressor erector
Position is provided with gas handling system and inlet plenum；
Turbine installs station, and the turbine installation station is provided with exhaust for installing turbine, the turbine installation station
Cylinder, exhaust chamber and exhaust system；
Combustion chamber, the combustion chamber are equipped with flange-interface, and the flange-interface is used to connect bored plate flange or fuel assembly,
The fuel assembly includes at least burner inner liner and fuel nozzle.
A kind of preferred embodiment, Compressor test state, the compressor installation station are equipped with test compressor, institute
It states turbine installation station and aerodynamic turbine is installed, the test compressor and air force worm gear are coaxially connected, the combustion
The flange-interface and bored plate flanged joint, the slow-speed shaft of the gear-box for burning room are connected with driving power source.
A kind of preferred embodiment, the driving power source are variable-frequency motor or generator, the variable-frequency motor or power generation
Machine is respectively connected with static frequency converter.
A kind of preferred embodiment, the test compressor has multistage variable stator blade and multistage bleeding point, described in every grade
The anti-asthma valve of adjustable aperture is provided on the corresponding exhaust pipe of bleeding point；It is adjustable that the air force worm gear is equipped with the first order
Stator blade.
A kind of preferred embodiment, gas turbine complete machine no load test state, the compressor installation station are equipped with
Compressor is tested, the turbine installation station is equipped with aerodynamic turbine, and the test compressor and air force worm gear are same
Axis connection, the flange-interface of the combustion chamber are connected with fuel nozzle and burner inner liner, and the slow-speed shaft of the gear-box has been connected with
Dynamic power source.
A kind of preferred embodiment, the slow-speed shaft of the gear-box are connected with generator, and the generator is connected with static state
Frequency converter, the generator is by the adjustment of static frequency converter as starting power source.
A kind of preferred embodiment, gas turbine complete machine full load trystate, in the gas turbine complete machine airport logistic park
On the basis of trystate, when starting gas turbine, the generator is by the adjustment of static frequency converter as starting power
Source；After gas turbine operation, fuel engine power generation power is absorbed by load equipment.
A kind of preferred embodiment, gas turbine complete machine full load trystate, in the gas turbine complete machine airport logistic park
On the basis of trystate, the output end of the aerodynamic turbine is connected with load compressor.
A kind of preferred embodiment, gas turbine complete machine full load trystate, in the gas turbine complete machine airport logistic park
On the basis of trystate, the gear-box is additionally provided with load connecting shaft, is connected with hydraulic dynamometer in the load connecting shaft.
A kind of preferred embodiment, gas turbine complete machine full load trystate, in the gas turbine complete machine airport logistic park
On the basis of trystate, the generator is connect with dry type load cabinet.
A kind of preferred embodiment, after the test compressor, combustion chamber and aerodynamic turbine installation, in each test
Axial distance and interface ruler under state, between the left side flange of the test compressor and the right flange of aerodynamic turbine
It is very little consistent.
The modular multi-function test bench for gas turbine of the present embodiment, by needing to use to each experimental stage of gas turbine
The equipment arrived carries out modularization decomposition, and immobilizes setting to shared device, ensures that each experimental stage can be same
A testing stand is completed, and is kept the utilization rate of test platform and shared device higher, is avoided unnecessary repeated construction, save
Space requirement and equipment cost.
Detailed description of the invention
Fig. 1 is the structural representation of the modular multi-function test bench for gas turbine in embodiment two under Compressor test state
Figure；
Fig. 2 is the modular multi-function gas turbin test under five Middle combustion engine turbine complete machine full load trystate of embodiment
The structural schematic diagram of platform；
Fig. 3 is the modular multi-function gas turbin test under six Middle combustion engine turbine complete machine full load trystate of embodiment
The structural schematic diagram of platform；
Fig. 4 is the modular multi-function gas turbin test under seven Middle combustion engine turbine complete machine full load trystate of embodiment
The structural schematic diagram of platform；
Fig. 5 is the modular multi-function gas turbin test under eight Middle combustion engine turbine complete machine full load trystate of embodiment
The structural schematic diagram of platform；
Fig. 6 is the modular multi-function gas turbin test under ten Middle combustion engine turbine complete machine full load trystate of embodiment
The structural schematic diagram of platform；
Fig. 7 is the modular multi-function gas turbin test under nine Middle combustion engine turbine complete machine full load trystate of embodiment
The structural schematic diagram of platform；
Fig. 8 is gas handling system, the connection schematic diagram of inlet plenum and gas turbine in the present embodiment；
Fig. 9 is the knot for testing compressor, combustion chamber and aerodynamic turbine in embodiment two under Compressor test state
Structure and connection schematic diagram；
Figure 10 is that compressor, combustion chamber and air are tested under three Middle combustion engine turbine complete machine no load test state of embodiment
The structure and connection schematic diagram of power turbine；
Figure 11 is that compressor, combustion chamber and air are tested under example IV Middle combustion engine turbine complete machine no load test state
The structure and connection schematic diagram of power turbine.
Specific embodiment
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, below in conjunction with attached drawing and implementation
Example, the present invention will be further described in detail.It should be appreciated that specific embodiment described herein is only used to explain
The utility model is not used to limit the utility model.
In the description of the present invention, it should be understood that term " on ", "lower", "front", "rear", "inner", "outside" etc.
The orientation or positional relationship of instruction is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of description the utility model
It is described with simplifying, rather than the device or element of indication or suggestion meaning must have a particular orientation, with specific orientation structure
It makes and operates, therefore should not be understood as limiting the present invention.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, are integrally connected, are also possible to detachably connect
It connects；It can be the connection inside two elements；It can be directly connected, it can also indirectly connected through an intermediary, for this
For the those of ordinary skill in field, the concrete meaning of above-mentioned term in the present invention can be understood with concrete condition.
Embodiment one
As shown in figs. 1-7, a kind of modular multi-function test bench for gas turbine of the present embodiment is provided with compressor and installs
Station and turbine install station, wherein the shared device being fixedly installed includes gear-box 3, combustion chamber 7, is installed on compressor installation
The gas handling system 4 and inlet plenum 5 of station, and it is installed on exhaust casing 9, exhaust chamber 10 and the exhaust system of turbine installation station
11.Wherein, compressor installation station is for installing test compressor 6, and turbine installation station is for installing turbine 8, to be used for
At corresponding test.
In the present embodiment, gear-box 3 includes at least one high speed shaft and at least one slow-speed shaft, wherein one end of high speed shaft
For connecting turning motor 1, the other end is used for joint test compressor 6.Slow-speed shaft on gear-box 3 starts power for connecting
Source or driving power source or load.
In the present embodiment, wherein the structure of gas handling system 11 is as shown in fig. 7, comprises vertical air plenums 18 and horizontal duct 20,
Wherein horizontal duct 20 is connect by air inlet elbow 6 with inlet plenum 5.In the gas handling system of the structure, vertical air plenums 18 close into
The position in air port is equipped with air inlet louvers 19, and the position of close vertical air plenums is equipped with air intake filter 22 in horizontal duct 20, leans on
The position of nearly air inlet elbow 21 is equipped with admission air silencer 24, and air inlet is equipped between air intake filter 22 and admission air silencer 24 and is measured
Section 23.
The gas handling system of above structure has following technical advantage: (1) air inlet louvers is adjustable louver structure, is had
Charge flow rate can be adjusted in certain angle adjustable range, and air inlet measuring section is provided with flow nozzle, enter pressure for measuring
The flow of mechanism of qi, by measuring and adjusting the pressure and flow of air inlet, convenient for calculating and testing Capability of Compressor；(2) by into
The aerodynamic noise that compressor is reversely spread out of can be effectively reduced in the setting of gas muffler 24；(3) setting by air intake filter 22
It sets and foreign matter entrance can be effectively prevented, protect compressor；(4) pass through the air inlet of vertical air plenums and horizontal duct and air inlet elbow
Route setting, it is possible to reduce the temperature change of air inlet；(5) reduce the leaf inlet pressure field distortion of compressor variable stator vane angle and reduction
The inlet air flow angle of attack.
In the present embodiment, the structure of combustion chamber 7 as shown in figs. 9-11, has flange-interface 25, which both may be used
Can be used for connection fuel assembly, wherein fuel assembly generally includes burner inner liner 30 and combustion for connecting bored plate flange 28
Expect nozzle 29.The combustion chamber of the structure can carry out flexible assembling, for carrying out by connecting bored plate flange or fuel assembly
Different types of test can avoid combustion chamber equipment with the high technical advantage of applied widely, testing stand and utilization rate of equipment and installations
Repeated construction.
Embodiment two
As shown in Figure 1, modular multi-function test bench for gas turbine is used for Compressor test in the present embodiment.In the examination
It tests under state, compressor installation station is equipped with test compressor 6, and turbine installation station is equipped with aerodynamic turbine 8.Its
In, test compressor and aerodynamic turbine it is coaxially connected, test compressor connect with inlet plenum, by gas handling system provide into
Gas；Aerodynamic turbine is connect with exhaust casing, and exhaust gas is discharged via exhaust chamber and exhaust system.
In the present embodiment, as shown in figure 9, the flange-interface 25 of combustion chamber is connect with bored plate flange 28, the work of combustion chamber
With compressed gas is only introduced aerodynamic turbine by test compressor, do not have combustion function.
In the present embodiment, as shown in figure 9, the multistage variable stator vane angle 26 of test compressor 6 and multistage bleeding point, the pumping
The anti-asthma valve 17 of adjustable aperture is provided on the corresponding exhaust pipe of port, each anti-asthma valve 17 is connect with control system respectively,
By control system independent control, it opens quantity and aperture, and the size of bleeding point and the diameter of exhaust pipe should be than under design discharges
Corresponding size is big, there are being adjusted up surplus, the settable several grades of valve seat openings of anti-asthma valve, for example, 20%, 40%, 60%,
80%, 100%, it is design discharge when valve is opened to 80%.
In the present embodiment, as shown in figure 9, aerodynamic turbine 8 is provided with first order variable stator vane angle 27, which can
Stator blade 27 is adjusted to connect with control system, the aperture by adjusting first order variable stator vane angle tests compressor to difference when realizing test
The working medium of the demand of back pressure, aerodynamic turbine is air, since aerodynamic turbine has carried out power recovery at this time, output
The power of a part of driving test compressor of power contribution, reduces the power of the external power source of driving test compressor.
In the present embodiment, the slow-speed shaft of gear-box is connected with driving power source, for driving the power source of test compressor
Wasted work and the at this time difference of aerodynamic turbine power of the power when should be greater than test 110% rated speed of compressor, Ke Yixuan
High-power frequency conversion motor 2 is selected as driving power source, SFC (static frequency converter 13) can also be used by generator 2 as motor
It uses.Make to test stable operation under any revolving speed of the compressor between 0~110% rated speed by gear-box again.Pass through
It drives mutual between power source, test compressor multistage entry guide vane, aerodynamic turbine first stage stator blades and anti-asthma valve
Cooperation, the Compressor test platform may be implemented in different rotating speeds, different compressor back pressures, different the case where being evacuated sum of series flow
Test compressor is tested.If it is excessive to test compressor power, power recovery is carried out by air turbine and is also not enough to
The power of power source needed for reducing can save charge flow rate by the angle of air inlet louvers in adjusting gas handling system
Stream further decreases the power of driving compressor.
In the present embodiment, the power of variable-frequency motor 2 is according to testing power input to compressor when 110% rated speed under design condition
The power for subtracting aerodynamic turbine carries out type selecting multiplied by safety coefficient.Specific formula is as follows:
P1=(PC-PT)×δ
Wherein:
P1: variable-frequency motor power；
PC: 110% rated speed power input to compressor under design condition；
PT: 110% rated speed turbine power under design condition；
δ: safety coefficient.
Embodiment three
In the present embodiment, modular multi-function test bench for gas turbine carries out complete machine no load test, the complete machine idling
Lotus is tested by carrying out adjustment appropriate on the basis of the Compressor test of embodiment two.Specifically, as shown in Figure 10,
The bored plate flange connected on the flange-interface of combustion chamber is replaced with by fuel nozzle and burner inner liner
A kind of preferred embodiment, gas turbine complete machine no load test state, the compressor installation station are equipped with
Compressor is tested, the turbine installation station is equipped with aerodynamic turbine, and the test compressor and aerodynamic turbine are same
Axis connection, the flange-interface of the combustion chamber are connected with the fuel assembly that fuel nozzle 29 and burner inner liner 30 are constituted.Wherein fuel
Nozzle 29 and burner inner liner 30 are connected with fuel conduit, fuel system, and improve lubricating oil system, cooling water system, motor control
The other equipment such as cabinet and component, so that the combustion chamber has ignition function.It should be noted that this has ignition function
The combustion chamber and its component of energy belong to the ordinary skill in the art, do not repeat them here at this to its specific structure.
In the present embodiment, first order variable stator vane angle 27 and the control system of aerodynamic turbine 8 are disconnected, and make the first order
Variable stator vane angle 27 no longer has regulatory function.
In the complete machine airport logistic park experiment of the present embodiment, the driving power source in embodiment two makes as power source is started
With.According to the starting curve of unit, modifying SFC parameter makes driving power source and startup of unit process in embodiment two match
.In the present embodiment, the effect for starting power source is starter group, after startup of unit, by test compressor, combustion chamber with
And the gas turbine that constitutes of aerodynamic turbine will under airport logistic park state continuous service, it is corresponding to obtain under airport logistic park state
Parameter.
When the low speed axis connection generator of gear-box, according to gas turbine starting characteristic curve, the defeated of the SFC is adjusted
Parameter out is defeated by the revolving speed of the power frequency change generator of generator by changing, passes through control exciting current, stator terminal electricity
The control generator output torque such as pressure, can become motor starting unit for the generator in this way.It should be noted that this kind
Adjustment also belongs to the ordinary skill in the art with change.
In the present embodiment, it wherein test compressor can be the test compressor in embodiment two, can also be changed to
New test compressor.In replacement process, it is only necessary to the left side flange of guarantee test compressor and the right side of aerodynamic turbine
Axial distance between side flange is consistent with connection size.
Example IV
In the present embodiment, modular multi-function test bench for gas turbine still carries out complete machine no load test, with reality
The difference for applying example three is, as shown in figure 11, aerodynamic turbine 8 is changed to new aerodynamic turbine, the new air
The first stage stator blades 31 of power turbine are non-adjustable stator blade.During replacing aerodynamic turbine, it is only necessary to guarantee test
Axial distance and connection size between the left side flange of compressor and the right flange of aerodynamic turbine is consistent.
Embodiment five
In the present embodiment, progress complete machine is complete after modular multi-function test bench for gas turbine carries out complete machine no load test
Load test.
As shown in Fig. 2, the present embodiment is on the basis of embodiment three and example IV, the output end of aerodynamic turbine 8
It is connected to load compressor 12, the power of gas turbine is absorbed using load compressor 12.
As shown in Fig. 2, connecting generator 2 on the slow-speed shaft of gear-box in the present embodiment, which is connected with SFC.
In the present embodiment, generator 2 uses under the adjustment of SFC as starting power source.After startup of unit, calmed the anger by test
The gas turbine that machine, combustion chamber and aerodynamic turbine are constituted will persistently be transported under the load condition with load compressor
Row, to obtain corresponding parameter in the loaded state.
Embodiment six
In the present embodiment, progress complete machine is complete after modular multi-function test bench for gas turbine carries out complete machine no load test
Load test.
As shown in figure 3, the present embodiment and the difference of embodiment five are, starting power source is to connect with the slow-speed shaft of gear-box
The variable-frequency motor connect, the variable-frequency motor are connected with SFC.
Embodiment seven
In the present embodiment, progress complete machine is complete after modular multi-function test bench for gas turbine carries out complete machine no load test
Load test.
As shown in figure 4, the present embodiment and the difference of embodiment five are, the output end of aerodynamic turbine 8 and load are pressed
Mechanism of qi disconnects, and gear-box 3 is changed to new gear-box, and new gear-box not only includes for connecting turning motor
High speed shaft and for connect start power source slow-speed shaft, further include for connect load load connecting shaft.Wherein, described
It is connected with hydraulic dynamometer 14 in load connecting shaft, which is used to absorb the power of gas turbine.
In the present embodiment, generator 2 is connected on the slow-speed shaft of gear-box, which is connected with SFC.In this embodiment party
In formula, generator 2 is used under the adjustment of SFC as starting power source.After startup of unit, by test compressor, combustion chamber with
And aerodynamic turbine constitute gas turbine by the continuous service under the load condition with hydraulic dynamometer 14, to obtain
Corresponding parameter under load condition.
Embodiment eight
In the present embodiment, progress complete machine is complete after modular multi-function test bench for gas turbine carries out complete machine no load test
Load test.
As shown in figure 5, the present embodiment and the difference of embodiment seven are, starting power source is to connect with the slow-speed shaft of gear-box
The variable-frequency motor connect, the variable-frequency motor are connected with SFC.
Embodiment nine
In the present embodiment, progress complete machine is complete after modular multi-function test bench for gas turbine carries out complete machine no load test
Load test.
As shown in fig. 7, the present embodiment and the difference of embodiment five are, the output end of aerodynamic turbine 8 and load are pressed
Mechanism of qi disconnects, and generator 2 is connect with dry type load cabinet 32, which is used to absorb the power of gas turbine.
Embodiment ten
In the present embodiment, progress complete machine is complete after modular multi-function test bench for gas turbine carries out complete machine no load test
Load test.
As shown in fig. 6, the present embodiment, on the basis of embodiment five, output end and the load of aerodynamic turbine 8 are calmed the anger
Machine 12 disconnects, and generator 2 is connect with power grid.
In the complete machine full load test of the present embodiment, under starting state, generator 2 is used as under the corrective action of SFC
Dynamic power source uses.After startup of unit, gas turbine operate normally, generator 2 restores the function of generator itself, will issue
Electricity be delivered directly to power grid, carry out on-line operation test.
It should be noted that on-line operation test is generally directed to lower-powered gas turbine unit.
To sum up, the modular multi-function test bench for gas turbine of the application can complete combustion gas in the same testing stand
The test of each experimental stage of turbine, keeps the utilization rate of test platform and shared device higher, avoids unnecessary repetition
Construction, saves space requirement and equipment cost.
Modular multi-function test bench for gas turbine in the application after the completion of the test of complete machine full load, improves auxiliary system
System and electric utility, such as increase combustion engine housing, housing ventilation and gas detection system, fire-fighting system, generator protection cabinet,
The equipment such as neutral point cabinet, outgoing line cabinet, synchronization device can be used as experimental power station longtime running, to verify the reliability of unit.
In short, the above is only the preferred embodiment of the utility model only, it is not intended to limit the utility model, it is all
Any modifications, equivalent replacements, and improvements made within spirit of the present utility model and principle etc. should be included in practical
Within novel protection scope.
Claims (10)
1. a kind of multifunctional modular test bench for gas turbine, which is characterized in that include at least:
Gear-box, the gear-box include at least a high speed shaft and at least one slow-speed shaft, and one end of the high speed shaft is used for
Turning motor is connected, the other end is used for joint test compressor；The slow-speed shaft starts power source or driving power for connecting
Source or load；
Compressor installs station, and the compressor installation station is set for installing test compressor, the compressor installation station
It is equipped with gas handling system and inlet plenum；
Turbine installs station, and the turbine installation station is provided with exhaust casing, row for installing turbine, the turbine installation station
Gas chamber and exhaust system；
Combustion chamber, the combustion chamber are equipped with flange-interface, and the flange-interface is described for connecting bored plate flange or fuel assembly
Fuel assembly includes at least burner inner liner and fuel nozzle.
2. multifunctional modular test bench for gas turbine described in accordance with the claim 1, which is characterized in that Compressor test shape
State, the compressor installation station are equipped with test compressor, and the turbine installation station is equipped with aerodynamic turbine, described
It tests compressor and aerodynamic turbine is coaxially connected, the flange-interface of the combustion chamber and bored plate flanged joint, the gear
The slow-speed shaft of case is connected with driving power source.
3. multifunctional modular test bench for gas turbine according to claim 2, which is characterized in that the driving power source
For variable-frequency motor or generator, the variable-frequency motor or generator are respectively connected with static frequency converter.
4. multifunctional modular test bench for gas turbine according to claim 2, which is characterized in that the test compressor
With multistage variable stator blade and multistage bleeding point, adjustable aperture is provided on the corresponding exhaust pipe of every grade of bleeding point
Anti-asthma valve；The aerodynamic turbine is equipped with first order variable stator vane angle.
5. multifunctional modular test bench for gas turbine described in accordance with the claim 1, which is characterized in that gas turbine complete machine is empty
Load test state, the compressor installation station are equipped with test compressor, and it is dynamic that the turbine installation station is equipped with air
Power turbine, the test compressor and air force worm gear are coaxially connected, and the flange-interface of the combustion chamber is connected with fuel spray
Mouth and burner inner liner, the slow-speed shaft of the gear-box are connected with starting power source.
6. multifunctional modular test bench for gas turbine according to claim 5, which is characterized in that the gear-box it is low
Fast axis connection has generator, and the generator is connected with static frequency converter, and the generator is made by the adjustment of static frequency converter
To start power source.
7. multifunctional modular test bench for gas turbine according to claim 6, which is characterized in that gas turbine complete machine is complete
Load test state, on the basis of the gas turbine complete machine no load test state, when starting gas turbine, the hair
Motor is by the adjustment of static frequency converter as starting power source；After gas turbine operation, pass through gear-box low speed axis connection
Load equipment or generator connection dry type load cabinet or generator be directly connected with power grid absorption gas turbine power generation function
Rate.
8. multifunctional modular test bench for gas turbine according to claim 5, which is characterized in that gas turbine complete machine is complete
Load test state, on the basis of the gas turbine complete machine no load test state, the output of the aerodynamic turbine
End is connected with load compressor.
9. multifunctional modular test bench for gas turbine according to claim 5, which is characterized in that gas turbine complete machine is complete
Load test state, on the basis of the gas turbine complete machine no load test state, the gear-box is additionally provided with load and connects
Spindle is connected with hydraulic dynamometer in the load connecting shaft.
10. according to the described in any item multifunctional modular test bench for gas turbine of claim 2-9, which is characterized in that described
After testing compressor, combustion chamber and aerodynamic turbine installation, under each trystate, the left side method of the test compressor
Axial distance and connection size between the blue and right flange of aerodynamic turbine is consistent.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109827779A (en) * | 2019-03-26 | 2019-05-31 | 杭州汽轮动力集团有限公司 | A kind of multifunctional modular test bench for gas turbine |
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| CN109827779A (en) * | 2019-03-26 | 2019-05-31 | 杭州汽轮动力集团有限公司 | A kind of multifunctional modular test bench for gas turbine |
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Address after: 357 Shiqiao Road, Xiacheng District, Hangzhou City, Zhejiang Province Patentee after: Hangzhou Steam Turbine Holding Co.,Ltd. Address before: 357 Shiqiao Road, Xiacheng District, Hangzhou City, Zhejiang Province Patentee before: HANGZHOU TURBINE POWER GROUP CO.,LTD. |
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| CP01 | Change in the name or title of a patent holder |