CN110397615A - A kind of multistage compressor experimental rig - Google Patents
A kind of multistage compressor experimental rig Download PDFInfo
- Publication number
- CN110397615A CN110397615A CN201910703208.2A CN201910703208A CN110397615A CN 110397615 A CN110397615 A CN 110397615A CN 201910703208 A CN201910703208 A CN 201910703208A CN 110397615 A CN110397615 A CN 110397615A
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- Prior art keywords
- casing
- assembly
- experimental rig
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- multistage compressor
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
Abstract
This application involves a kind of multistage compressor experimental rig, the experimental rig includes: front fulcrum support load-bearing frame and rear fulcrum load-bearing frame；Multistage compressor, outlet measurement casing sub-assembly and exit casing sub-assembly and hub cylinder axis, balancing frame rotor stack, rear shaft neck and power transmission shaft between the front fulcrum support load-bearing frame and rear fulcrum load-bearing frame are set；Wherein, there is bypass to move back asthma device for reducing the pressure and temperature in exit casing sub-assembly on the exit casing sub-assembly, wherein, it is described bypass move back asthma device include connect exit casing sub-assembly bypass move back asthma air entraining pipe, with it is described bypass move back asthma air entraining pipe connect metal fairlead, it is multiple be vented column and summarize it is described be vented column exhaust main.The experimental rig of the application can alleviate exerciser in the past under high temperature rise, high pressure at expulsion test capability deficiency.
Description
Technical field
The application belongs to aero-engine test technology field, in particular to a kind of multistage compressor experimental rig.
Background technique
Multistage compressor experimental rig is a kind of device for verifying multistage compressor earlier stages matching relationship, with high pressure
It must be under the weather (winter of high latitude area) of ultralow temperature than with features, the multistage compressor experimental rig such as high exhaust temperature
It can be carried out test just to reduce physics revolving speed to the maximum extent.Due to can be carried out the time of multistage compressor test every year very
It is short, along with the factors such as the assembly of experimental rig is had enough to meet the need, work is added in hardware troubleshooting, the maintenance of testing stand, final available test
Time is very limited, once missing, will cause to delay and (delay at least a year as long as missing) to project development progress.
It is as described in Figure 1 Compressor test device 100 in the prior art comprising: it is front fulcrum load-bearing frame 101, more
Grade compressor 102, exhaust group section 103, drum barrel axis 104, rear shaft neck 105, rear fulcrum load-bearing frame 106 and power transmission shaft
107.However above-mentioned Compressor test device 100 can not achieve it is any under the conditions of test.
Summary of the invention
There is provided a kind of multistage compressor experimental rigs for the purpose of the application, to solve or mitigate in background technique extremely
A few problem.
The technical solution of the application is: a kind of multistage compressor experimental rig, the experimental rig include:
Front fulcrum supports load-bearing frame and rear fulcrum load-bearing frame；
Multistage compressor between the front fulcrum support load-bearing frame and rear fulcrum load-bearing frame is set, outlet measures
Casing sub-assembly and exit casing sub-assembly and hub cylinder axis, balancing frame rotor stack, rear shaft neck and power transmission shaft；
Wherein, there is bypass to move back asthma device for reducing the pressure in exit casing sub-assembly on the exit casing sub-assembly
Power and temperature, wherein the bypass moves back the bypass that asthma device includes connection exit casing sub-assembly and moves back asthma air entraining pipe and the side
Move back the metal fairlead, multiple exhaust columns and the exhaust main for summarizing the exhaust column of asthma air entraining pipe connection in road.
In one embodiment of the application, the metal fairlead is hose.
In one embodiment of the application, the exit casing sub-assembly includes casing in being vented outer casing and being vented, row
The outer casing of gas includes exhaust outer ring leading portion and exhaust outer ring back segment, and being vented interior casing includes after being vented inner ring leading portion and exhaust inner ring
Section has exit casing coupling ring between leading portion and back segment.
In one embodiment of the application, the bypass is moved back asthma air entraining pipe and is drawn from the exhaust outer ring back segment.
In one embodiment of the application, also there is outlet casing sub-assembly, the outlet in exhaust inner ring leading portion leading portion
Casing sub-assembly includes exporting casing, the casing front end honeycomb of the outlet casing front end being arranged in and is set to the outlet
Blower outlet in the middle part of casing obturages honeycomb.
In one embodiment of the application, the outlet measurement casing sub-assembly includes measurement casing, is connected with measurement casing
The outlet straightening blade that connects, the measuring device being mounted on the dynamometry casing and draw test from the measuring device
Target.
In one embodiment of the application, the balancing frame rotor stack includes at least one balancing frame and transfer panel,
The transfer panel and balancing frame are fixed on the hub cylinder axis.
The multistage compressor experimental rig of the application is improved according to existing Compressor test device, to verify multistage
The experimental rig of the matching relationship of compressor earlier stages, the application is not limited by weather conditions, annual as long as hardware condition has
It can be carried out testing any time.Experimental rig is subjected to adaptive testing repacking simultaneously, can carry out surveying between detailed grade
Examination, traveling probe test carry out the complete full rate performance admission of a wheel.The experimental rig of the application improves multistage compressor
The development efficiency of project has saved cost, has eliminated waste, while not having to consider weather conditions, breaches testing stand heatproof energy
Power, exhaust capacity, the limitation for moving back asthma ability, annual any season can be carried out testing.
Detailed description of the invention
In order to illustrate more clearly of technical solution provided by the present application, attached drawing will be briefly described below.It is aobvious and easy
Insight, drawings discussed below are only some embodiments of the present application.
Fig. 1 is the Compressor test schematic device of the prior art.
Fig. 2 is the multistage compressor experimental rig schematic diagram of the application.
Fig. 3 is the exit casing assembling unit structure schematic diagram in the application.
Fig. 4 is that asthma device scheme of installation is moved back in the bypass in the application.
Fig. 5 is that asthma device and exerciser scheme of installation are moved back in the bypass in the application.
Fig. 6 is the measurement casing sub-assembly schematic diagram in the application.
Fig. 7 is the application middle outlet casing sub-assembly schematic diagram.
Fig. 8 is the balancing frame rotor stack schematic diagram in the application.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.
In order to solve the problems, such as that in the prior art, present applicant proposes a kind of multistage compressor experimental rigs hereinafter referred to as to test dress
200 are set, as shown in Figures 2 to 5, experimental rig 200 includes: front fulcrum support load-bearing frame 210 and rear fulcrum load-bearing frame
290；Multistage compressor 220 between front fulcrum support load-bearing frame 210 and rear fulcrum load-bearing frame 290 is set, outlet is surveyed
Measure casing sub-assembly 230 and exit casing sub-assembly 240 and hub cylinder axis 250, balancing frame rotor stack 260, rear shaft neck 270
With power transmission shaft 280；Wherein, there is bypass to move back asthma device 246 for reducing exit casing group on exit casing sub-assembly 240
Pressure and temperature in component 240, wherein bypass moves back the bypass that asthma device 246 includes connection exit casing sub-assembly 240 and moves back asthma
Air entraining pipe 2461 moves back the metal fairlead 2462 breathing heavily air entraining pipe 2461 and connecting, multiple exhaust columns 2463 with bypass and summarizes row
The exhaust main 2464 of gas column 2463.
In this application, experimental rig 200 exhaust transfer key component, due to experimental rig 200 functionality and band
There is axial force, is the safe and reliable work of guarantee test device 200, turns after the rotor of experimental rig 200 equipped with balancing frame
Sub-assemblies 260 are it is more exact that cooperation disk 262 carrys out the axial force of balancing rig 200, with the peace of guarantee test device 200
Row for the national games.
For the assembling of guarantee test device 200, exit casing sub-assembly 240 will be vented interior casing 242 and exhaust is outer
It is 4 sections that ring casing 241, which divides, is vented outer casing 241 and includes exhaust outer ring leading portion 2411 and exhaust outer ring back segment 2412, is vented interior machine
Casket 242 includes exhaust inner ring leading portion 2422 and exhaust inner ring back segment 2423, passes through exhaust between exhaust leading portion and exhaust back segment
Casing coupling ring 243 is supported connection, ensure that the realization of experimental rig back segment assembly, also achieves multistage compressor casing
With coupling for discharge portion, and the assembly of multistage compressor balancing frame ensure that.
The structure type of the exit casing sub-assembly 240 of the application may be implemented blower outlet flow path and hold with rear fulcrum
The smooth transfer of power frame 290 guarantees being smoothly discharged for air-flow, simultaneously because experimental rig 200 has balancing frame 262, is arranging
Gas inner ring back segment 2423 is equipped with balancing frame and obturages the use that ring 2424 carrys out complex equilibrium disk 262.
It ensure that the integrality of 200 casing of experimental rig, 262 function of balancing frame by above-mentioned exit casing sub-assembly 240
The realization of energy, experimental rig 200 are assembled feasible.
Each section of exit casing sub-assembly 240 is assembled to form a complete casing by exit casing coupling ring 243
Sub-assembly, front end couple with blower outlet, and rear end couples with the final vacuum section of Compressor test device, while exporting casing
Sub-assembly 2421 and exhaust inner ring back segment 2423 and front and back component are assembled by overlap joint, and casing sub-assembly is exported
2421, it is vented that inner ring leading portion 2422, exhaust inner ring back segment 2423, balancing frame obturages ring assemblies 260 is cantilever design, this structure is protected
The case where entire assembly of exit casing sub-assembly 240 is not in Planar Mechanisms is demonstrate,proved.Can have by exit casing sub-assembly 240
The reliable integrality for guaranteeing Compressor test device 200 of effect, while meeting experimental rig 200 and being wanted using balancing frame 262
It asks, Compressor test device to test, rack bleed, experimental rig also may be implemented by the switching of exit casing sub-assembly 240
Open to atmosphere Functional Requirement.
Exit casing sub-assembly 240 can apply high pressure ratio, big flow Compressor test device on, meet compressor
Experimental rig balancing axial thrust, grate flow channel switching etc. be while require, also can guarantee the testability of experimental rig, assembling,
The related needs such as reliability, maintainability.
In addition, there are also bypasses to move back asthma device 246 in the application, bypass moves back asthma device 246 and is connected to exit casing sub-assembly
On 240.Since the design point parameter of multistage compressor experimental rig 200 is significantly higher than the design objective of compressormeter, tool
There is the characteristics of high pressure ratio, high temperature rise ratio, high exhaust temperature, under the premise of exerciser scarce capacity, asthma device is moved back by bypass
246 can be effectively relieved in test exhaust throttle load, guarantee going on smoothly for Compressor test.
Bypass moves back the bypass that asthma device 246 includes connection exit casing sub-assembly 240 and moves back asthma air entraining pipe 2461, moves back with bypass
Metal fairlead 2462, multiple exhaust columns 2463 and the exhaust main for summarizing exhaust column 2463 that asthma air entraining pipe 2461 connects
2464, the switching that asthma air entraining pipe 2461 is arranged between the measurement casing of Compressor test device 200 and exit casing is moved back in bypass
On ring.In some embodiments, metal fairlead 2462 uses metal hose.
In one embodiment of the application, according to the detailed analysis calculated with test data in compressor flow field, it can be tried
The maximum pressure at expulsion of experiment device 200 is about 1.6Mpa, according to the principle on male and fomale(M&F) butt welding steel pipe flanges side, considers and tests
The structure type of connection and the sealing of device.
The inside nominal diameter Φ 40mm of air entraining pipe is that the operating point that selected state is Compressor test device revolving speed is maximum
Demand point selectes the parameters such as suitable Throttling ratio, flow, pressure ratio and efficiency, and what can be calculated show out that the hole of 8 Φ 40mm can
To meet the requirement of discharge quantity.
The gas drawn from experimental rig 200 is discharged into atmosphere by gas exhaust piping, and asthma air entraining pipe 2461 is moved back in every group of bypass
The flange of flange and metal fairlead 2462 is tightened by 4 bolts, and centre is enhanced close by way of installing copper backing additional
The metal fairlead 2462 of envelope, exerciser brings great convenience to the installation and adjustment of experimental rig 200.In gas exhaust piping
Between setting two-way valve realize the control and guidance to air-flow.
Easily there is the uncoordinated shape of thermal deformation under the conditions of high temperature, high pressure gas in traditional compressor exerciser exhaust throttle
Condition, causes to move back during asthma and catching phenomenon occurs, becomes the huge hidden danger of testing equipment and experimental rig safe operation.Certain is calmed the anger
Machine has the characteristics that high pressure ratio, high temperature rise than because of the significantly high Mr. Yu's compressormeter design objective of its design point parameter, in order to record
Take under the compressor design speed block up point to asthma point a cmplete characteristic curve, and guarantee into asthma process safety it is reliable, by bypass move back
Asthma device 246 can alleviate exerciser in the past under high temperature rise, high pressure at expulsion test capability deficiency.
For the insufficient limitation of exerciser ability to work under high temperature rise, high pressure at expulsion, the bypass in the application is moved back
Exhaust throttle load has been effectively relieved in our unit is tested in asthma system air entraining pipe and its installation method.Exhaust temperature
Degree, pressure ratio reach the limit values above, and catching phenomenon does not occur in exerciser exhaust throttle, it was demonstrated that the work of asthma system is moved back in the bypass
Effectively, alleviate the exerciser in the past under high temperature rise, high pressure at expulsion test capability deficiency.
As shown in fig. 6, the outlet measurement casing sub-assembly 230 having in the experimental rig 200 of the application includes measuring machine
Casket 233, with the measurement casing 233 outlet straightening blade 234 connecting, the measuring device 231 that is mounted on dynamometry casing 233 and
The test target 232 for drawing measurement device 231, by integrating exit flow field measurement, direction field measurement on measurement casing 233
The test target 232 of measuring device 231 and boundary layer measurement and it can guarantee that air-flow is smoothly discharged with outlet straightening blade 234.
As shown in fig. 7, in this application, in order to realize the smooth switching of earlier stages experimental rig, the test dress of the application
Setting 200 has outlet casing sub-assembly 2421, and outlet casing sub-assembly 2421 includes outlet casing 24211, setting in outlet machine
The casing front end honeycomb 24212 of 24211 front end of casket and the blower outlet for being set to 24211 middle part of outlet casing obturage honeycomb
24213, casing front end honeycomb 24212 can guarantee that multistage compressor turns obturaging between stator, and honeycomb 24213 is obturaged in outlet can
To guarantee that blower outlet is obturaged, outlet casing 24211 is capable of forming smooth flow path, guarantees smooth in exhaust.
For guarantee Compressor test device 200 can safety test, at the rear portion of compressor rotor, experimental rig 200
The front of rear fulcrum load-bearing frame 290 is equipped with balancing frame rotor stack 260, and balancing frame rotor assembly 260 was both adjustable
The axial force of experimental rig 200, the also critical speed of adjustable rotor-support-foundation system.
Balancing frame rotor stack 260 includes at least one balancing frame 262 and transfer panel 261, transfer panel 261 and balancing frame
262 are fixed on hub cylinder axis 250.In the embodiment shown in fig. 8, balancing frame rotor stack 260 includes 262 He of balancing frame
One transfer panel 261, the end that balancing frame 262 is connected to hub cylinder axis 250 by connecting bolt 263.
It is assemblied in due to balancing frame rotor stack 260 on the rotor-support-foundation system of experimental rig 200, and is located at high temperature and pressure
Intracavitary, the Intensity Design of balancing frame 262 is obturaged ability and assembling and can be designed according to actual needs.
In order to guarantee that assembling is reasonable, in the rear design plate nut 264 of balancing frame 262, both guarantee to assemble in this way
It is convenient, and the space of rear fulcrum has been saved, it ensure that the span of experimental rig 200.
The top comb tooth and coating of balancing frame 262 have design gaps, and design gaps will guarantee that excessive draw of rubbing will not be touched
Experimental rig vibration is played, guarantees the reliability obturaged again, does not leak, is rationally determined and is sealed according to the radial displacement of balancing frame 262
Tight gap guarantees that balancing frame 262 has the function of separating pressure chamber.
By adjusting the shape and rigging position of transfer panel 261, the critical speed of adjustable compressor rotor makes to calm the anger
The critical speed of machine and the nargin of working speed meet the requirement of safety test.
It is difficult that the multistage compressor experimental rig of the application solves multistage compressor experimental rig verifying in the prior art
The problem of, realize the Successful tests of earlier stages experimental rig.By testing in our unit, stage plus design technology before verifying is reached
Purpose, also demonstrate the feasibility of the experimental rig structure of the application.
The multistage compressor experimental rig of the application is improved according to existing Compressor test device, to verify multistage
The experimental rig of the matching relationship of compressor earlier stages, the application is not limited by weather conditions, annual as long as hardware condition has
It can be carried out testing any time.Experimental rig is subjected to adaptive testing repacking simultaneously, can carry out surveying between detailed grade
Examination, traveling probe test carry out the complete full rate performance admission of a wheel.The experimental rig of the application improves multistage compressor
The development efficiency of project has saved cost, has eliminated waste, while not having to consider weather conditions, breaches testing stand heatproof energy
Power, exhaust capacity, the limitation for moving back asthma ability, annual any season can be carried out testing.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (7)
1. a kind of multistage compressor experimental rig, which is characterized in that the experimental rig (200) includes:
Front fulcrum supports load-bearing frame (210) and rear fulcrum load-bearing frame (290)；
Multistage compressor between front fulcrum support load-bearing frame (210) and rear fulcrum load-bearing frame (290) is set
(220), outlet measurement casing sub-assembly (230) and exit casing sub-assembly (240) and hub cylinder axis (250), balance disc rotor
Sub-assembly (260), rear shaft neck (270) and power transmission shaft (280)；
Wherein, on the exit casing sub-assembly (240) there is the bypass of connection exit casing sub-assembly (240) to move back asthma device
(246), for reducing the pressure and temperature in exit casing sub-assembly (240), wherein asthma device (246) packet is moved back in the bypass
The bypass for including connection exit casing sub-assembly (240) moves back asthma air entraining pipe (2461), moves back asthma air entraining pipe (2461) even with the bypass
Metal fairlead (2462), multiple exhausts column (2463) and the exhaust main for summarizing exhaust column (2463) connect
(2464)。
2. multistage compressor experimental rig as described in claim 1, which is characterized in that the metal fairlead (2462) is soft
Pipe.
3. multistage compressor experimental rig as described in claim 1, which is characterized in that the exit casing sub-assembly (240)
Including casing (242) in being vented outer casing (241) and being vented, be vented outer casing (241) including be vented outer ring leading portion (2411) and
It is vented outer ring back segment (2412), being vented interior casing (242) includes being vented inner ring leading portion (2422) and exhaust inner ring back segment (2423),
There is exit casing coupling ring (243) between leading portion and back segment.
4. multistage compressor experimental rig as claimed in claim 3, which is characterized in that asthma air entraining pipe (2461) is moved back in the bypass
It is drawn from the exhaust outer ring back segment (2412).
5. multistage compressor experimental rig as described in claim 3 or 4, which is characterized in that in exhaust inner ring leading portion (2422)
Leading portion also has outlet casing sub-assembly (2421), and the outlet casing sub-assembly (2421) includes outlet casing (2424), sets
It sets in the casing front end honeycomb (2422) for exporting casing (2424) front end and is set in the outlet casing (2424)
The blower outlet in portion obturages honeycomb (2424).
6. multistage compressor experimental rig as described in claim 1, which is characterized in that the outlet measures casing sub-assembly
It (230) include measurement casing (233), the outlet straightening blade (234) connecting with measurement casing (233) is mounted on the dynamometry
Measuring device (231) on casing (233) and draw test target (232) from the measuring device (231).
7. multistage compressor experimental rig as described in claim 1, which is characterized in that the balancing frame rotor stack
It (260) include at least one balancing frame (262) and transfer panel (261), the transfer panel (261) and balancing frame (262) are fixed on
On the hub cylinder axis (250).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910703208.2A CN110397615A (en) | 2019-07-31 | 2019-07-31 | A kind of multistage compressor experimental rig |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910703208.2A CN110397615A (en) | 2019-07-31 | 2019-07-31 | A kind of multistage compressor experimental rig |
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ID=68326978
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| CN201910703208.2A Pending CN110397615A (en) | 2019-07-31 | 2019-07-31 | A kind of multistage compressor experimental rig |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111312058A (en) * | 2019-11-29 | 2020-06-19 | 中国科学院工程热物理研究所 | Test piece structure of gas compressor |
| CN112283142A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Gas compressor testing device, sealing device and manufacturing method thereof |
| CN112360793A (en) * | 2020-11-06 | 2021-02-12 | 中国船舶重工集团公司第七0三研究所 | Diffusion casing for large-flow ship gas turbine compressor test |
| CN114323652A (en) * | 2020-09-28 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | Exhaust and gas collection device of axial flow compressor tester |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204314065U (en) * | 2014-11-21 | 2015-05-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of Compressor test part rock-steady structure |
| CN105443439A (en) * | 2015-05-19 | 2016-03-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Exhaust casing assembly used for test piece of gas compressor |
| CN105971920A (en) * | 2016-06-22 | 2016-09-28 | 中国航空工业集团公司沈阳发动机设计研究所 | Compressor test device |
| GB2541065A (en) * | 2015-05-19 | 2017-02-08 | Snecma | Assembly for an engine which can define a blade break-off test device |
| CN106989929A (en) * | 2017-04-19 | 2017-07-28 | 中国航发沈阳发动机研究所 | A kind of high-pressure compressor testpieces structure |
-
2019
- 2019-07-31 CN CN201910703208.2A patent/CN110397615A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204314065U (en) * | 2014-11-21 | 2015-05-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of Compressor test part rock-steady structure |
| CN105443439A (en) * | 2015-05-19 | 2016-03-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Exhaust casing assembly used for test piece of gas compressor |
| GB2541065A (en) * | 2015-05-19 | 2017-02-08 | Snecma | Assembly for an engine which can define a blade break-off test device |
| CN105971920A (en) * | 2016-06-22 | 2016-09-28 | 中国航空工业集团公司沈阳发动机设计研究所 | Compressor test device |
| CN106989929A (en) * | 2017-04-19 | 2017-07-28 | 中国航发沈阳发动机研究所 | A kind of high-pressure compressor testpieces structure |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111312058A (en) * | 2019-11-29 | 2020-06-19 | 中国科学院工程热物理研究所 | Test piece structure of gas compressor |
| CN111312058B (en) * | 2019-11-29 | 2022-02-25 | 中国科学院工程热物理研究所 | Test piece structure of gas compressor |
| CN114323652A (en) * | 2020-09-28 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | Exhaust and gas collection device of axial flow compressor tester |
| CN114323652B (en) * | 2020-09-28 | 2023-10-13 | 中国航发商用航空发动机有限责任公司 | Exhaust and gas collection device of axial-flow compressor tester |
| CN112360793A (en) * | 2020-11-06 | 2021-02-12 | 中国船舶重工集团公司第七0三研究所 | Diffusion casing for large-flow ship gas turbine compressor test |
| CN112283142A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Gas compressor testing device, sealing device and manufacturing method thereof |
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Application publication date: 20191101 |