CN202582906U - Mini compressor/turbine combined testing stand - Google Patents
Mini compressor/turbine combined testing stand Download PDFInfo
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- CN202582906U CN202582906U CN 201220072471 CN201220072471U CN202582906U CN 202582906 U CN202582906 U CN 202582906U CN 201220072471 CN201220072471 CN 201220072471 CN 201220072471 U CN201220072471 U CN 201220072471U CN 202582906 U CN202582906 U CN 202582906U
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Abstract
The utility model relates to a mini compressor/turbine combined testing stand, which comprises a gas source, a heater, a turbine assembly, a compressor assembly, a PC controller, a measurement and data acquisition system, a torque sensor, and a vibration monitoring system. The testing stand has the advantages that high-temperature combustion gas is used to drive a turbine and to drive a compressor to rotate, and an independent compressor air passage and an independent turbine air passage are equipped, so that conditions of the turbine or the compressor can be adjusted independently; that when compressor components are tested the turbine is used as a power source to drive the compressor, and when the turbine components are tested the compressor is used as a load to adjust the output power of the turbine; that the turbine inlet pressure, the turbine inlet temperature, the turbine outlet backpressure and the compressor outlet backpressure are adjusted, so that the turbine matches with the compressor in different rotating speeds and different flow conditions, thereby acquiring a rotating-speed characteristic line of tested impellers; that the independent compressor assembly supports a compress rotator, and the independent turbine assembly supports a turbine rotator, wherein rotary shafts are used for connection; and that the modularized structure design improves both the versatility and the utilization rate.
Description
Technical field
The utility model relates to a kind of device that turbomachine performance is measured that is used for, can accurately measure the minitype compressor/turbine Combined Trials platform and the experiment process of pneumatic plant and turbine wheel characterisitic parameter and part flow field parameter.
Background technology
Miniature turbine engine (MTE) is in light weight, power is big, energy density is high, can be used as the propulsion system of various microminiature guided missiles, unmanned plane and even following individual soldier's aircraft, is a kind of emerging jet-propulsion propulsion system with good application prospect; The miniature turbine engine also can develop into airplane auxiliary power system (being APU), civil aviation field only, and accessory power system just has nearly 10,000,000,000 dollars annual value of production scale.Wheel member (comprising pneumatic plant and turbine) is as the core component of tiny engine, and the accurate measurement of its performance is to checking and improve little impeller design technology, raising engine overall performance is all significant.Yet the performance measurement of little turbomachine is different with conventional yardstick impeller, has its special character: the rotating speed of little turbomachine is much larger than conventional yardstick impeller, generally more than 100,000 rev/mins.The maximum speed of products such as the motor that can buy on the market at present,, dynamometer machine, twist counter generally is no more than 30,000 rev/mins.Under conventional yardstick; General independent the carrying out of the component test of pneumatic plant and turbine, motor can be used as the power source of compressor part test, and the drive pressure mechanism of qi reaches certain rotating speed; And dynamometer machine and twist counter can be used as the load of turbine part test, measure the power output of turbine.Because the existing product rotating speed is lower, desire realizes the impeller performance measurement under the high rotating speed, then only increases variable-speed gear system at impeller shaft and motor/dynamometer machine etc., and this will increase the complicacy of system greatly.
Summary of the invention
The utility model provides a kind of minitype compressor/turbine Combined Trials platform and experiment process, its purpose is intended to overcome the above-mentioned defective of existing in prior technology.Can have pneumatic plant and turbine part performance test function concurrently.The pneumatic plant gas circuit of this device and turbine gas circuit are independent, do not disturb mutually, therefore can regulate pneumatic plant and turbine operating mode respectively, realize the different rotating speeds flow operating mode of test impeller.When carrying out the compressor part test, turbine is as the drive power source pneumatic plant; When carrying out the turbine part test, pneumatic plant is as load measure turbine output rate.
The technical solution of the utility model: it is characterized in that comprising source of the gas, warmer, turbine assembly, compressor assemblies, PC controller, measurement and data acquisition system (DAS), torque sensor, vibration monitor system; Wherein: source of the gas connects warmer, and source of the gas is that warmer provides pressure-air; Warmer connects turbine assembly, and the pressurized air that warmer provides source of the gas is heated into hot combustion gas, by the test turbine in the hot gas driven turbine assembly; Turbine assembly is realized the assembling and the parameter measurement of test turbine; Turbine rotor in the turbine assembly connects the compressor rotor in the compressor assemblies through rotating shaft, drives the compressor rotor rotation, and compressor assemblies realizes the assembling and the parameter measurement of test pneumatic plant; A control signal end in the PC controller and up electric control valve, B control signal end and descending electric control valve in the PC controller join, and C control signal end and quick exhaust valve in the PC controller are joined, and D control signal end and oil pump in the PC controller join; Being arranged on the signal output part of the torque sensor in the rotating shaft and first signal input part of measurement and data acquisition system (DAS) joins; The hot combustion gas that is obtained by warmer heating is joined through the secondary signal input end of thermopair and measurement and data acquisition system (DAS); The 3rd signal input part of the signal output part of turbine assembly and measurement and data acquisition system (DAS) joins; The 4th signal input part of the pressure of compressor assemblies, temperature signal output terminal and downlink traffic output terminal, descending line pressure signal output terminal and measurement and data acquisition system (DAS) joins; The 5th signal input part of uplink traffic output terminal and measurement and data acquisition system (DAS) joins; The 6th signal input part of up line pressure signal output terminal and data acquisition system (DAS) joins; The vibration signal test side of vibration monitor system is connected with compressor assemblies with the measuring system vibration signal; The 7th signal input part of the signal output part of vibration monitor system and measurement and data acquisition system (DAS) joins, and the signal output part of data acquisition system (DAS) and PC controller join.
The advantage of the utility model: drive turbine and drive the pneumatic plant rotation with high-temperature fuel gas, have independently pneumatic plant gas circuit and turbine gas circuit, but independent regulation turbine or pneumatic plant operating mode.When carrying out the compressor part test, turbine is as the drive power source pneumatic plant; When carrying out the turbine part test, pneumatic plant is as load regulation turbine output rate.Through regulating turbine inlet pressure, temperature, the turbine outlet back pressure, the blower outlet back pressure realizes turbine and the coupling of pneumatic plant under different rotating speeds, flow operating mode, obtain the test impeller etc. the rotary speed property line.Independently compressor assemblies and turbine assembly support compressor rotor and turbine rotor respectively, and middle dependence rotating shaft connects.Core component adopts the modular construction design, improves the versatility and the utilization factor of device.For preventing bearing failure, and improve experimental enviroment, device possesses the cooling and lubricating oil circuit and takes provision for thermal insulation.
Description of drawings
Accompanying drawing 1 is minitype compressor/turbine Combined Trials platform structured flowchart.
Accompanying drawing 2 is compressor assemblies structural representations.
Accompanying drawing 3 is turbine assembly structural representations.
Accompanying drawing 4 is agent structure synoptic diagram of minitype compressor/turbine Combined Trials platform.
Accompanying drawing 5 is testing table agent structure lubricant passage way and cooling pneumatic diagram.
Accompanying drawing 6 is testing table high-temperature component provision for thermal insulation synoptic diagram.
Accompanying drawing 7 is warmer structural representations.
Accompanying drawing 8 is a kind of structural representations that are used to measure the device of ultrahigh rotating speed impeller shaft moment of torsion.
In the accompanying drawing 1 is the pneumatic plant bearing; The 2nd, compressor air inlet machine rectification pipeline; The 3rd, compressor rotor; The 4th, the compressor rotor casing; The 5th, pneumatic plant stator casing; The 6th, diffuser; The 7th, pneumatic plant exhaust volute; The 8th, pneumatic plant exhaust group section; The 9th, pneumatic plant bearing casing; The 10th, the pneumatic plant return tray; The 11st, the grating dish; The 12nd, rotating shaft; The 13rd, the turbine return tray; The 14th, turbine bearing casing; The 15th, turbine air inlet group section; The 16th, turbine air inlet volute; The 17th, turbine stator casing; The 18th, nozzle ring; The 19th, the castor tooth of obturaging; The 20th, turbine rotor; The 21st, the turbine rotor casing; The 22nd, stifled awl governor motion; The 23rd, the turbine bearing; The 24th, the pneumatic plant core component; The 25th, the turbine core component; The 26th, base; The 27th, lubricating oil; The 28th, pressurized air is used in cooling; The 29th, obturage and use pressurized air; The 30th, heat-barrier material; The 31st, miniature firing chamber.
Embodiment
Contrast accompanying drawing 1; The structure of minitype compressor/turbine Combined Trials platform comprises source of the gas, warmer, turbine assembly, compressor assemblies, PC controller, measurement and data acquisition system (DAS), torque sensor, vibration monitor system; Wherein: source of the gas connects warmer, and source of the gas is that warmer provides pressure-air; Warmer connects turbine assembly, and the pressurized air that warmer provides source of the gas is heated into hot combustion gas, by the test turbine in the hot gas driven turbine assembly; Turbine assembly is realized the assembling and the parameter measurement of test turbine; Turbine rotor in the turbine assembly connects the compressor rotor in the compressor assemblies through rotating shaft, drives the compressor rotor rotation, and compressor assemblies realizes the assembling and the parameter measurement of test pneumatic plant; A control signal end in the PC controller and up electric control valve, B control signal end and descending electric control valve in the PC controller join, and C control signal end and quick exhaust valve in the PC controller are joined, and D control signal end and oil pump in the PC controller join; Being arranged on the signal output part of the torque sensor in the rotating shaft and first signal input part of measurement and data acquisition system (DAS) joins; The hot combustion gas that is obtained by warmer heating is joined through the secondary signal input end of thermopair and measurement and data acquisition system (DAS); The 3rd signal input part of the signal output part of turbine assembly and measurement and data acquisition system (DAS) joins; The 4th signal input part of the pressure of compressor assemblies, temperature signal output terminal and downlink traffic output terminal, descending line pressure signal output terminal and measurement and data acquisition system (DAS) joins; The 5th signal input part of uplink traffic output terminal and measurement and data acquisition system (DAS) joins; The 6th signal input part of up line pressure signal output terminal and data acquisition system (DAS) joins; The vibration signal test side of vibration monitor system is connected with compressor assemblies with the measuring system vibration signal; The 7th signal input part of the signal output part of vibration monitor system and measurement and data acquisition system (DAS) joins, and the signal output part and the PC of data acquisition system (DAS) join.
What described PC controller adopted is the TMS320F28027 chip; The major control amount comprises warmer upstream valve aperture, pneumatic plant valve downstream aperture, supplying fuel amount and turbine rotor downstream stifled awl awl position; With system's rotating speed serves as to regulate target; When actual measurement rotating speed and rotating speed of target were inconsistent, the aperture through regulating two valves and the air mass flow of stifled awl awl position adjustment pneumatic plant and turbine were adjusted fuel flow with the change turbine inlet temperature (TIT) through regulating oil pump feed voltage; With this power match relation of regulating pneumatic plant and turbine, obtain required rotating speed, flow status.
Described measurement and data acquisition system (DAS) mainly comprise measuring equipment and NI PXI acquisition systems such as speed probe, pressure scanning valve, temperature polling instrument, differential pressure type V cone flow meter, photoelectricity torque sensor, total/static probe, thermopair, dynamic pressure transducer; Accomplish each cross section of this testing table aerodynamic parameter (comprise stable state total/static pressure, dynamically static pressure, stable state total/static temperature), the measurement of rotating speed, pneumatic plant/turbine air flow, rotating shaft moment of torsion etc.; And utilize the PXI acquisition system with the test figure that collects SF storage and uniform as required, make things convenient for the follow-up test interpretation of result.
Described vibration monitor system mainly comprises acceleration transducer, vibration monitor; In compressor rotor casing vertical direction and horizontal direction an acceleration transducer is set respectively; The radial vibration of detection system and axial vibration, and with testing result demonstration in real time on monitor.
Contrast accompanying drawing 2; Its structure comprises pneumatic plant bearing, pneumatic plant bearing casing, air inlet rectification pipeline 2, pneumatic plant exhaust group section 8, pneumatic plant exhaust volute 7, compressor rotor 3, diffuser 6, compressor rotor casing 4, pneumatic plant stator casing 5, rotating shaft 12; Wherein: air inlet rectification pipeline 2 is linked in sequence with compressor rotor casing 4, pneumatic plant stator casing 5, diffuser 6, pneumatic plant bearing casing 9, pneumatic plant exhaust group section 8; Pneumatic plant exhaust volute is connected with pneumatic plant exhaust group section; Rotating shaft 12 relies on bearings in pneumatic plant bearing casing with compressor rotor, and this part assembly all is placed on the pneumatic plant bearing.Environmental gas after 2 rectifications of air inlet rectification pipeline, flow through compressor rotor 3, diffuser 6, pneumatic plant exhaust group section 8 and exhaust volute; In the volute downstream flowmeter survey compressor air flow is installed, install adjustment valve regulation pneumatic plant back pressure changes the pneumatic plant operating mode in the flowmeter downstream.Measuring point is set on pneumatic plant stator casing 5 measures compressor rotor outlet stagnation temperature, stagnation pressure and static pressure, measuring point is set on the compressor rotor casing measures dynamic pressure signal in the pneumatic plant flow field.
Contrast accompanying drawing 4; Combined Trials platform agent structure is made up of compressor assemblies and turbine assembly two large divisions; Mainly comprise pneumatic plant bearing 1, pneumatic plant core component 24, pneumatic plant exhaust volute 7, base 26, turbine bearing 23, turbine air inlet volute 16, stifled awl governor motion 22, wherein: pneumatic plant core component 24 all is installed on the pneumatic plant bearing 1 with pneumatic plant exhaust volute 7 forms compressor assemblies; Turbine core component 25, turbine air inlet volute 16 all are installed on the turbine bearing 1 with stifled awl governor motion 22 forms turbine assembly; Compressor assemblies and turbine assembly are installed on the base 26 simultaneously, constitute the agent structure part of testing table.Compressor assemblies and turbine assembly have supported a whole set of rotor-support-foundation system and have arranged most measuring points, to accomplish the measurement of pneumatic plant and turbine performance.Because pneumatic plant gas circuit and turbine gas circuit are independent, the gas after the pneumatic plant supercharging is not imported turbine end, so compressor assemblies and turbine assembly are middle by the rotating shaft connection as two modular structures independently.
Contrast accompanying drawing 5; Its structure comprises nozzle ring 18, turbine bearing casing 14, the castor tooth 19 of obturaging, turbine rotor 20, rotating shaft 12, turbine return tray 13, grating dish 11; Wherein: nozzle ring 18 is installed on the turbine bearing casing 14, and rotating shaft 12 is placed in turbine bearing casing 14 center pits, and turbine rotor 20 is installed in the rotating shaft 12 with grating dish 11; Turbine return tray 13 is connected with turbine bearing casing 14, and above-mentioned parts constitute a ring cavity.Because the test wheel speed is up to more than 100,000 rev/mins, so bearing produces a large amount of heats in operation process, influence its normal operation; Therefore the lubricant passage way that has been design bearing; To reduce the bearing working temperature, its structure is: adopt oil pump to infeed lubricating oil 27 through the inclined hole on the turbine bearing casing 14, lubricating oil 27 flows into turbine bearing casing 14 center pits through bearing; In rotating shaft 12 flows to turbine return tray 13; Accumulate in grating dish 11 end face sides, extract out, realize the circulation of lubricating oil with dump pump.Owing to have the gap between grating dish 11 and the turbine return tray 13; For prevent that parts of lubricating oil from spilling in this gap; Therefore in circumferential 3 pores of turbine return tray, infeed pressure-air, form high pressure air film, the leakage of shutoff lubricating oil in the gap between grating dish and turbine return tray.For turbine assembly the cooling gas circuit is set simultaneously; Reduce the turbine assembly DIE Temperature; Its structure is: 4 pores through turbine bearing casing 14 back sides feed cooling air, and cooling air accumulates in the ring cavity of the bearing casing and castor tooth 19 formations of obturaging, and 36 holes in spraying from castor tooth 19 back sides of obturaging are mapped to the turbine rotor disc back of the body again; With the leakages of high-temperature fuel gas in the minimizing nozzle ring 18 in turbine rotor disc back of the body cavity, and the temperature of reduction turbine core component.
Contrast accompanying drawing 6 because turbine assembly temperature in process of the test is higher, distributes a large amount of heats to the external world; Worsen experimental enviroment; Be prone to cause electronic component failure, therefore lay heat-barrier material 30, reduce the heat radiation of high-temperature component to environment in turbine air inlet volute 16 outside wall surface.
Impeller adiabatic efficiency is as the important indicator of its performance, and the emphasis of paying close attention to when being the design of this device is the accurate measurement of realization quick runner efficient, and it is unpractical relying on present power measurement product.For this reason, the torch measuring system of this device adopts a kind of device that is used to measure ultrahigh rotating speed impeller shaft moment of torsion, can realize 12.5 ten thousand rev/mins high speed rotating shaft torque measurement, and precision is up to ± 1%.This torque-measuring apparatus is arranged wide grating in the rotating shaft both sides; The light that light source sends is received by light activated element through grating and is converted into electric signal output; Utilize rotating shaft receive moment of torsion twist the distortion cause the both sides grating to deflect; The principle that light path narrowed width, electric signal change is accurately measured the rotating shaft moment of torsion.This device belongs to non-contact measurement, and electromagnetic interference (EMI) is little, has higher response speed, can realize the collection of high-frequency signal.
Minitype compressor/turbine Combined Trials bench teat is in order to measure the impeller characteristic of diameter 78mm centripetal turbine and diameter 84mm centrifugal compressor.Debugging on testbed is the result show: system works well, and each functions of modules basically all can normally be brought into play, and has accomplished the part cold and hot state performance test of diameter 78mm centripetal turbine with this equipment.
Test method comprises pneumatic plant test method and turbine test method, wherein:
The pneumatic plant test method: start air compressor machine, pressurized air is transported to steady pressure in the buffer tank after filtration, drying, open warmer upstream regulation valve; Pressurized air is flowed through and is got into warmer after flowmeter is measured air mass flow; Ignition in warmer, reach uniform temperature after, be transported to turbine air inlet volute and flow into guides through turbine air inlet group section; In guides, quicken the back and impact turbine rotor, make it drive compressor rotor and rotate together.Utilize galvanomagnetic effect to measure wheel speed through a pair of magnetic bead that is installed in the compressor disc back of the body; And on monitor screen, show in real time; If wheel speed is higher than rotating speed of target; Then suitably reduce warmer upstream valve aperture and reduce air mass flow, or reduce warmer fuel delivery reduction turbine inlet stagnation temperature, make wheel speed be reduced to desired value; Otherwise then suitably strengthening warmer upstream valve aperture increases air mass flow, or increases warmer fuel delivery raising turbine inlet stagnation temperature, makes wheel speed increase to desired value.Keep rotating speed of target 30 ~ 60s, gather the air mass flow of turbine and pneumatic plant, import and export pressure, the temperature in cross section, parameters such as rotating shaft moment of torsion.After accomplishing this state point pneumatic plant performance measurement; Regulate pneumatic plant valve downstream aperture, the pneumatic plant back pressure changes, and flow, rotating speed all change thereupon; If the pneumatic plant rotating speed is lower than rotating speed of target; Then increase turbine flow or improve turbine inlet temperature (TIT), increase the turbine output rate, make wheel speed increase to desired value; Otherwise, then reduce turbine flow or reduce turbine inlet temperature (TIT), reduce the turbine output rate, make wheel speed reduce to desired value.Keep rotating speed of target 30 ~ 60s, gather parameters, accomplish the pneumatic plant performance measurement of this rotating speed, flow status point.In like manner, constantly regulate pneumatic plant back pressure and turbine output rate, make wheel speed maintain desired value, can obtain the compressor characteristic curves under this rotating speed state.
The turbine test method: start air compressor machine, pressurized air is transported to steady pressure in the buffer tank after filtration, drying, open warmer upstream regulation valve; Pressurized air is flowed through and is got into warmer after flowmeter is measured air mass flow; Ignition in warmer, reach uniform temperature after, be transported to turbine air inlet volute and flow into guides through turbine air inlet group section; In guides, quicken the back and impact turbine rotor, make it drive compressor rotor and rotate together.Utilize galvanomagnetic effect to measure wheel speed through a pair of magnetic bead that is installed in the compressor disc back of the body; And on monitor screen, show in real time; If wheel speed is higher than rotating speed of target; Then suitably reduce warmer upstream valve aperture and reduce air mass flow, or reduce warmer fuel delivery reduction turbine inlet stagnation temperature, make wheel speed be reduced to desired value; Otherwise then suitably strengthening warmer upstream valve aperture increases air mass flow, or increases warmer fuel delivery raising turbine inlet stagnation temperature, makes wheel speed increase to desired value.Keep rotating speed of target 30 ~ 60s, gather the air mass flow of turbine and pneumatic plant, import and export pressure, the temperature in cross section, parameters such as rotating shaft moment of torsion.After accomplishing this state point turbine performance and measuring, regulate stifled awl awl position, turbine downstream, the turbine back pressure changes; Flow, rotating speed all change thereupon, if secondary speed is lower than rotating speed of target, then reduce pneumatic plant valve downstream aperture; Reduce load pneumatic plant power demand, make wheel speed increase to desired value; Otherwise, increase pneumatic plant valve downstream aperture, increase load pneumatic plant power demand, make wheel speed increase to desired value.Keep rotating speed of target 30 ~ 60s, gather parameters, accomplish the turbine performance of this rotating speed, flow status point and measure.In like manner, constantly regulate turbine back pressure and load pneumatic plant power demand, make wheel speed maintain desired value, can obtain the turbine characteristic line under this rotating speed state.
Claims (4)
1. minitype compressor/turbine Combined Trials platform; It is characterized in that comprising source of the gas, warmer, turbine assembly, compressor assemblies, PC controller, measurement and data acquisition system (DAS), torque sensor, vibration monitor system; Wherein: source of the gas connects warmer, and source of the gas is that warmer provides pressure-air; Warmer connects turbine assembly; Turbine rotor in the turbine assembly connects the compressor rotor in the compressor assemblies through rotating shaft; A control signal end and up electric control valve in the PC controller join; B control signal end and descending electric control valve in the PC controller join, and C control signal end and quick exhaust valve in the PC controller are joined, and D control signal end and oil pump in the PC controller join; Being arranged on the signal output part of the torque sensor in the rotating shaft and first signal input part of measurement and data acquisition system (DAS) joins; The hot combustion gas that is obtained by warmer heating is joined through the secondary signal input end of thermopair and measurement and data acquisition system (DAS); The 3rd signal input part of the signal output part of turbine assembly and measurement and data acquisition system (DAS) joins; The 4th signal input part of the pressure of compressor assemblies, temperature signal output terminal and downlink traffic output terminal, descending line pressure signal output terminal and measurement and data acquisition system (DAS) joins; The 5th signal input part of uplink traffic output terminal and measurement and data acquisition system (DAS) joins; The 6th signal input part of up line pressure signal output terminal and data acquisition system (DAS) joins; The vibration signal test side of vibration monitor system is connected with compressor assemblies with the measuring system vibration signal; The 7th signal input part of the signal output part of vibration monitor system and measurement and data acquisition system (DAS) joins, and the signal output part and the PC of data acquisition system (DAS) join.
2. minitype compressor according to claim 1/turbine Combined Trials platform; It is characterized in that compressor assemblies comprises pneumatic plant bearing, pneumatic plant bearing casing, air inlet rectification pipeline, pneumatic plant exhaust group section, pneumatic plant exhaust volute, compressor rotor, diffuser, compressor rotor casing, pneumatic plant stator casing, rotating shaft; Wherein: air inlet rectification pipeline and compressor rotor casing, pneumatic plant stator casing, diffuser, pneumatic plant bearing casing, pneumatic plant exhaust group section are linked in sequence; Pneumatic plant exhaust volute is connected with pneumatic plant exhaust group section; Install and measure the flowmeter of compressor air flow in the volute downstream, change the variable valve of pneumatic plant operating mode in this flowmeter downstream install adjustment pneumatic plant back pressure; The measuring point of measuring compressor rotor outlet stagnation temperature, stagnation pressure and static pressure is set on pneumatic plant stator casing, the measuring point of measuring dynamic pressure signal in the pneumatic plant flow field is set on the compressor rotor casing.
3. minitype compressor according to claim 1/turbine Combined Trials platform; It is characterized in that turbine assembly comprises turbine bearing, turbine bearing casing, turbine air inlet volute, turbine air inlet group section, nozzle ring, turbine rotor, rotating shaft, turbine rotor casing, turbine stator casing, stifled awl governor motion; Wherein: turbine air inlet volute is connected with turbine air inlet group section; Turbine air inlet group section and turbine bearing casing, nozzle ring, turbine stator casing, turbine rotor casing are linked in sequence; Rotating shaft and turbine rotor rely on bearings in turbine bearing casing; Stifled awl governor motion is connected turbine rotor casing downstream, installs and measures the flowmeter of turbine air flow at the warmer upper reaches, at this flowmeter upper reaches install adjustment valve; Stifled awl governor motion is installed in the turbine rotor downstream, and the measuring point of measuring guides import stagnation temperature, stagnation pressure and static pressure is set on the guides casing, and the measuring point of measuring turbine rotor outlet stagnation temperature, stagnation pressure and static pressure is set on the turbine rotor casing.
4. minitype compressor according to claim 3/turbine Combined Trials platform is characterized in that turbine air inlet volute outside wall surface lays heat-barrier material.
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| CN102589894A (en) * | 2012-03-01 | 2012-07-18 | 南京航空航天大学 | Micro gas compressor/turbine combined test bed and test method |
| CN103487251A (en) * | 2013-10-18 | 2014-01-01 | 福州大学 | Electric-heating-based turbo-supercharger checking test bench and turbo-supercharger property testing method |
| CN104458273A (en) * | 2014-10-28 | 2015-03-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Safe running poor flameout threshold value setting method of combustion gas turbine |
| CN111379728A (en) * | 2020-04-29 | 2020-07-07 | 北京动力机械研究所 | Closed circulation centrifugal compressor characteristic test device |
| CN111379727A (en) * | 2020-04-29 | 2020-07-07 | 北京动力机械研究所 | Closed circulation centrifugal compressor characteristic test method |
| CN112179665A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Method for acquiring inlet stagnation pressure of low-pressure turbine performance test |
| CN112286098A (en) * | 2020-10-29 | 2021-01-29 | 中国航发南方工业有限公司 | Conversion board subassembly, gas turbine generating set's digital electronic control device |
| CN112729856A (en) * | 2020-12-23 | 2021-04-30 | 南京航腾机电科技有限公司 | Measurement and control system of air turbine starter comprehensive test bed |
| CN114136645A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Inlet flow field measuring device for turbine component tester |
-
2012
- 2012-03-01 CN CN 201220072471 patent/CN202582906U/en not_active Expired - Lifetime
Cited By (17)
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| CN102589894A (en) * | 2012-03-01 | 2012-07-18 | 南京航空航天大学 | Micro gas compressor/turbine combined test bed and test method |
| CN102589894B (en) * | 2012-03-01 | 2014-01-15 | 南京航空航天大学 | Micro gas compressor/turbine combined test bed and test method |
| CN103487251A (en) * | 2013-10-18 | 2014-01-01 | 福州大学 | Electric-heating-based turbo-supercharger checking test bench and turbo-supercharger property testing method |
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| CN104458273B (en) * | 2014-10-28 | 2017-08-04 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The poor stall threshold establishing method of gas turbine safe operation |
| CN111379727B (en) * | 2020-04-29 | 2022-02-15 | 北京动力机械研究所 | Closed circulation centrifugal compressor characteristic test method |
| CN111379727A (en) * | 2020-04-29 | 2020-07-07 | 北京动力机械研究所 | Closed circulation centrifugal compressor characteristic test method |
| CN111379728B (en) * | 2020-04-29 | 2022-02-11 | 北京动力机械研究所 | Closed circulation centrifugal compressor characteristic test device |
| CN111379728A (en) * | 2020-04-29 | 2020-07-07 | 北京动力机械研究所 | Closed circulation centrifugal compressor characteristic test device |
| CN112179665A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Method for acquiring inlet stagnation pressure of low-pressure turbine performance test |
| CN112286098A (en) * | 2020-10-29 | 2021-01-29 | 中国航发南方工业有限公司 | Conversion board subassembly, gas turbine generating set's digital electronic control device |
| CN112286098B (en) * | 2020-10-29 | 2022-08-26 | 中国航发南方工业有限公司 | Conversion board subassembly, gas turbine generating set's digital electronic control device |
| CN112729856A (en) * | 2020-12-23 | 2021-04-30 | 南京航腾机电科技有限公司 | Measurement and control system of air turbine starter comprehensive test bed |
| CN112729856B (en) * | 2020-12-23 | 2023-03-17 | 南京航腾机电科技有限公司 | Air turbine starter combined test platform system of observing and controling |
| CN114136645A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Inlet flow field measuring device for turbine component tester |
| CN114136645B (en) * | 2021-10-20 | 2023-06-02 | 中国航发四川燃气涡轮研究院 | Inlet flow field measuring device for turbine component tester |
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