CN202305215U - System for testing pressure distortion characteristic of air compressor of turbine shaft engine - Google Patents
System for testing pressure distortion characteristic of air compressor of turbine shaft engine Download PDFInfo
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- CN202305215U CN202305215U CN2011203929191U CN201120392919U CN202305215U CN 202305215 U CN202305215 U CN 202305215U CN 2011203929191 U CN2011203929191 U CN 2011203929191U CN 201120392919 U CN201120392919 U CN 201120392919U CN 202305215 U CN202305215 U CN 202305215U
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Abstract
The utility model relates to a system for testing the pressure distortion characteristic of an air compressor of a turbine shaft engine. The system comprises an air compressor testing device, a motor driving system and a measurement control system, wherein the air compressor testing device is formed by sequentially connecting an air compressor air-inlet passage, distortion generating devices, the air compressor and a throttling device; the motor driving system is formed by sequentially connecting a frequency converter, a driving motor and a coupler; and the measurement control system consists of a computer, a test analyzer and a sensor. A plurality of pressure distortion generating devices are adopted, a pressure distortion flow field is built at an inlet of the air compressor through the distortion generating devices, and parameters, such as air compressor interstage flow field (total pressure, static pressure and total temperature distribution), distortion transfer, air compressor rack performance and the like are measured under the condition of uniform air intake and distortion air intake. Through analysis of the test result, study on the distortion influence mechanism, the performance of the air compressor and the stability of the air compressor is carried out.
Description
Technical field
The utility model relates to a kind of pneumatic plant pressure distortion characteristic test system of turboshaft engine; Be mainly used in the test of the pneumatic plant distortion performance in the various turboshaft engine system in energy source and power and the defence and military field, measure and research and analyse, the teaching and scientific research and the staff training that also can be universities and colleges, research unit and industrial sector provide technical support.
Background technology
A large amount of turboshaft engines that have multi stage axial flow compressor that adopt in modern advanced aero-gas turbine, ground gas turbine and the shipping vehicle gas turbine engine systems.The main effect of pneumatic plant is through impeller rotation, the air of engine intake axial admission is compressed, for the engine acting provides pressurized air.The multi stage axial flow compressor pressure ratio is big, flow is high, function admirable, but can have instability problem.
The factor that influences multi stage axial flow compressor stability is a lot, the most importantly inhomogeneous distortion that causes of compressor inlet air velocity distribution.The even flox condition of engine intake is desired in the design, yet because the profile of air intake duct and geometric configuration, duty and air intake duct and factors such as whether engine matees must make air-flow certain mobile inhomogeneous of gas turbine inlet generation.Under the flight envelope scope and motor-driven attitude of aircraft broadness; The distortion of air intake duct exit flow field is an exist actually; For example aircraft is opened thrust reverser, air intake duct and is not started the disturbance that operating mode etc. all can cause compressor inlet temperature or pressure when weapon delivery, maneuvering flight, flight, and therefore studying the import distortion is very important to the performance of multi stage axial flow compressor and the influence of stability.
Summary of the invention
The purpose of the utility model is to provide a kind of pneumatic plant pressure distortion characteristic test system of turboshaft engine, has adopted multiple pressure distortion generating means, has realized pneumatic plant pressure distortion attribute testing and research.
The technical scheme of the utility model is: a kind of turboshaft engine pneumatic plant pressure distortion characteristic test system; Comprise: pneumatic plant test unit, motor driven systems and Measurement and Control System, said pneumatic plant test unit is connected to form by compressor inlet port, distortion generating means, pneumatic plant and restriction device successively; Said motor driven systems is connected to form by frequency converter, drive motor and shaft coupling successively; Said Measurement and Control System mainly is made up of computing machine, test analytical instrument and sensor.
In the such scheme, in the said pneumatic plant test unit, rake is measured as measuring the cross section, adopt the six roots of sensation that circumferentially is uniformly distributed with in import, inter-stage and three positions of outlet of pneumatic plant, in order to improve efficiency of measurement and accuracy.
In the such scheme, said distortion generating means adopts the version of distortion analog board, distortion simulation net or distortion plate.Wherein, the distortion analog board is in order to the simulation circumferential distortion, and distortion simulation net is in order to simulate circumferential radial distortion, and the distortion plate is in order to simulate circumferential radial distortion.The distortion analog board belongs to stationary apparatus with distortion simulation net, is directly installed on the select location of compressor inlet port.And the distortion plate can be state type also can be portable.
Pneumatic plant by asynchronous AC motor as driving motor supplies power, by the Frequency Converter Control rotating speed.Pneumatic plant goes out airshed is controlled manual adjustments by restriction device.The collection of various aerodynamic parameters, rotating speed control are all accomplished by Measurement and Control System.
Arrange pressure transducer in compressor inlet, inter-stage, exit position; Through changing the import distortion difference that generating means produced distortion intensity; Observation pneumatic plant different operational characteristics and stall characteristic utilize testing tools such as computing machine and data acquisition system (DAS) that test figure is monitored and record.
Pressure or velocity distribution to characterizing the flow field that import distortion produces are measured, and characteristic working curve and the stalling point of pneumatic plant when import distorts measured.The measurement result of the steady-state characteristic curve (pressure coefficient-coefficient of flow figure) of pneumatic plant in the time of generally will providing the vertical flow field of compressor inlet sectional drawing and have or not the import distortion.
Characteristic quantity (being mostly the unstable state data) to the compressor inlet distortion is measured in real time.Change some initial conditions (like axial location, circumferential width and the gas compressor blade plate shape rotating speed etc. of distortion device) of experiment, along certain independent variable such as time, frequency, circumferential angle etc., the variation of writing down these draws the conclusion with certain scientific research meaning.When being necessary, also to carry out data-switching work such as Fourier transform, FFT etc.
The beneficial effect of the utility model is: adopted multiple pressure distortion generating means.This system is on pneumatic plant ground experiment platform; Utilize the distortion generating means to set up required pressure distortion flow field at compressor inlet; Under even air inlet and distortion inlet air conditions, measure flow field between compressor stage (stagnation pressure, static pressure, stagnation temperature distribute), distortion is transmitted and parameters such as pneumatic plant test stand performance.Through analysis, carry out distortion effects mechanism and pneumatic plant performance and Study on Stability to test findings.
Description of drawings
Fig. 1 is a pneumatic plant distortion performance pilot system synoptic diagram.
Fig. 2 is the structural representation of distortion analog board.
Fig. 3 is the structural representation of whole shape distortion simulation net.
Fig. 4 is the structural representation of crescent distortion simulation net.
Fig. 5 is the structural representation of fan-shaped distortion simulation net.
Fig. 6 is the structural representation of distortion plate.
Fig. 7 is the measuring point layout synoptic diagram that pneumatic plant is measured the cross section.
Among Fig. 1,1-air inlet section, the 2-compressor inlet is measured the cross section; 3-import distortion generating apparatus, 4-pneumatic plant, 5-compressor inlet guiding blade; The 6-compressor rotor, 7-pneumatic plant stator, the 8-blower outlet is measured the cross section; 9-blower outlet restriction device, 10-motor driven systems, 11-compressor stage measurements cross section.
Among Fig. 7, S1-S30 is the static pressure measuring position, and D1-D6 is the dynamic pressure measurement position.
Embodiment
Elaborate below in conjunction with the structure and the principle of work of accompanying drawing to the utility model.
Referring to Fig. 1; The turboshaft engine pneumatic plant pressure distortion characteristic test system of the utility model comprises: pneumatic plant test unit, motor driven systems and Measurement and Control System, and the pneumatic plant test unit is connected to form by compressor air inlet machine section 1, distortion generating means 3, pneumatic plant 4 and restriction device 9 successively; Motor driven systems 10 is connected to form by frequency converter, drive motor and shaft coupling successively; Measurement and Control System mainly is made up of computing machine, test analytical instrument and sensor.At compressor inlet measurement cross section 2 is set, is provided with at blower outlet and measures cross section 8, between compressor stage, be provided with and measure cross section 11, pneumatic plant is provided with guide vane 5, compressor rotor 6 and pneumatic plant stator 7.
Be provided with the distortion generating means apart from the distance to axial in compressor inlet cross section for L/2R=3.5.According to the test needs, adopt distortion analog board, distortion simulation net and three kinds of distortion of distortion plate generating means respectively, the parameter of every kind of device is carried out certain setting according to the test needs.Distortion simulation net is identical with the internal diameter of pneumatic plant passage section with the external profile diameter of distortion analog board.The distortion generating means can be adjusted according to the test needs apart from the axial distance L in compressor inlet cross section, and the ratio L/2R maximum of axial distance L and runner radius R can reach 6.453, and minimum is 1.37.
The measurement mechanism in import distortion generating apparatus and compressor inlet, inner flow field is designed, analyzes and rational layout.Because pressure distortion can be divided into radial distortion, circumferential distortion and radially-circumferentially combined type distortion, so to the demand of simulating different distortion, can adopt different distortion generating meanss.
Referring to Fig. 2,, generally can adopt the distortion analog board of annular for circumferential stagnation pressure distortion.Lath width, the thickness of annular slab can change as required; Various forms of chamferings can be made in the edge of lath; Thereby air-flow forms the turbulent flow of certain intensity behind the plate, and with stagnation pressure distortion of simulation stable state and turbulence level, its advantage is simple in structure; Safe and reliable, but its processing and adjustment are relatively more difficult.Among Fig. 2, R1 is the radius of annular slab flow passage component, and R2 and R3 are respectively the inner edge and the outer rim radius of plate body.
Referring to Fig. 3-Fig. 5,, generally can adopt whole shape, fan-shaped or meniscate distortion simulation net for circumferential and radially stagnation pressure distortion.Distortion simulation net is made up of support, holder net, base net and subsides net, can adopt the mesh and the shape of various different sizes according to different testing requirementss, and its advantage is that making is used fairly simple.Fig. 3 is a whole shape distortion simulation net, and the through-flow zone of whole compressor inlet is covered fully.Fig. 4, Fig. 5 are respectively crescent and fan-shaped distortion net, according to the test needs, can set the angle β and the α of crescent and fan-shaped two ends radius flexibly, in the angle zone, set the distortion screen, thereby produce certain distortion effect.Two kinds of distortion simulation nets are fixed on blower casing and the stator by the steel housing, and wire netting is 100 purpose metal filter screens.
Referring to Fig. 6, the distortion plate is through with the requirement of plate according to different depth, inserts the runner before the engine intake, with this to coming the different disturbance of stream.The distortion plate can produce the pressure loss at compressor inlet; The separated flow at edge can produce turbulent flow; Thereby obtain required specific inlet flow field; Its major advantage be can be between different distortion flow fields conversion at any time and the transposing distortion generator that need not stop, thereby practiced thrift time, intensity and the expense of test.The distortion plate is along radially inserting the pneumatic plant flow section, and the height h2 of plate and width h1 can be provided with according to the test needs, thereby produce certain distortion effect.Between the insertion depth h2 of plate and the radius R of flow area relative depth, its maximal value is h2/R=0.76.The insertion depth h2 of plate is big more, stops up greatlyyer more than the ratio of shared area of section (the plate area with), and then distortion low-pressure area scope behind the plate and intensity are just big more.The distortion plate can be state type or movable type.
Referring to Fig. 7; In distortion test owing in compressor passage, be provided with various forms of distortion devices, the destruction of the distortion flow field effect of generation the compressor air inlet machine condition circumferentially with homogeneity radially; Therefore; Measure at each aerodynamic parameter of measuring on the cross section, 6 measurements having taked circumferentially to be uniformly distributed with are harrowed, and are designated as A, B, C, D, E, F respectively.Measure rake for every and radially wait several total pressure measurement probe aperture of anchor ring integration cloth.On the measurement cross section, 30 static state and 6 dynamic pressure measurement points have been arranged, shown in sequence number S1-S30 and D1-D6 among Fig. 7.On every pressure measurement rake, the static pressure measuring point is followed successively by 0.538,0.671,0.779,0.878,0.961 along relative radius radially.6 dynamic pressure measuring points are arranged on relative radius 0.9 place.
The stable state stagnation pressure is with dynamically the measurement and the record of stagnation pressure are accomplished by high-speed data acquistion system; In the test parallel sampling and store operational mode are all adopted in all stable states and the collection of dynamic stagnation pressure; The SF of stable state stagnation pressure is made as 1000Hz, and dynamically the SF of stagnation pressure is made as 10000Hz.
Claims (6)
1. turboshaft engine pneumatic plant pressure distortion characteristic test system; Comprise: pneumatic plant test unit, motor driven systems and Measurement and Control System is characterized in that: said pneumatic plant test unit is connected to form by compressor inlet port, distortion generating means, pneumatic plant and restriction device successively; Said motor driven systems is connected to form by frequency converter, drive motor and shaft coupling successively; Said Measurement and Control System mainly is made up of computing machine, test analytical instrument and sensor.
2. according to the described pneumatic plant pressure distortion of claim 1 characteristic test system, it is characterized in that: in the said pneumatic plant test unit, rake is measured as measuring the cross section, adopt the six roots of sensation that circumferentially is uniformly distributed with in import, inter-stage and three positions of outlet of pneumatic plant.
3. according to claim 1 or 2 described pneumatic plant pressure distortion characteristic test systems, it is characterized in that: said distortion generating means adopts the version of distortion analog board, distortion simulation net or distortion plate.
4. according to the described pneumatic plant pressure distortion of claim 3 characteristic test system, it is characterized in that: said distortion analog board is annular, and lath width, thickness can change as required, and the edge of lath can have various forms of chamferings.
5. according to the described pneumatic plant pressure distortion of claim 3 characteristic test system, it is characterized in that: said distortion simulation net is whole shape, fan-shaped or meniscate version.
6. according to the described pneumatic plant pressure distortion of claim 3 characteristic test system, it is characterized in that: said distortion plate is along radially inserting the pneumatic plant flow section, and height and width that plate inserts can be regulated, and plate can be state type or movable type.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011203929191U CN202305215U (en) | 2011-10-14 | 2011-10-14 | System for testing pressure distortion characteristic of air compressor of turbine shaft engine |
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| CN2011203929191U CN202305215U (en) | 2011-10-14 | 2011-10-14 | System for testing pressure distortion characteristic of air compressor of turbine shaft engine |
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| CN103115747A (en) * | 2012-12-21 | 2013-05-22 | 中国飞行试验研究院 | Large-size composite material air inlet passage measuring rake |
| CN103234756A (en) * | 2013-04-16 | 2013-08-07 | 中国航空工业集团公司沈阳发动机设计研究所 | Net type distortion device for large-bypass-ratio engines |
| CN103234730A (en) * | 2013-05-20 | 2013-08-07 | 中国航空动力机械研究所 | Pneumatic performance testing method as well as pneumatic performance testing device |
| CN103471851A (en) * | 2013-09-27 | 2013-12-25 | 北京动力机械研究所 | Movable pressure distortion simulation inserting plate |
| CN103471850A (en) * | 2013-09-27 | 2013-12-25 | 北京动力机械研究所 | Adjustable pressure distortion simulator and transmission device thereof |
| CN103471852A (en) * | 2013-09-27 | 2013-12-25 | 北京动力机械研究所 | Flow distortion simulation device |
| CN103512738A (en) * | 2013-09-23 | 2014-01-15 | 西安交通大学 | Low-temperature hydraulic turbine closed type experimental system and test method |
| CN105466689A (en) * | 2014-09-09 | 2016-04-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Installation technology of gas compressor blade surface dynamic pressure measurement device |
| CN105841971A (en) * | 2016-04-26 | 2016-08-10 | 中科合肥微小型燃气轮机研究院有限责任公司 | Gas turbine gas inlet measurement device |
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| CN106404407A (en) * | 2016-10-20 | 2017-02-15 | 北京动力机械研究所 | Adjustable fan-shaped plate flow field distortion simulator |
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| CN112610518A (en) * | 2020-11-24 | 2021-04-06 | 南京航空航天大学 | Rotatable steady-state total pressure distortion generator |
| CN112610518B (en) * | 2020-11-24 | 2021-10-22 | 南京航空航天大学 | Rotatable steady-state total pressure distortion generator |
| CN112254973A (en) * | 2020-12-21 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | High-pressure compressor test piece mechanism |
| CN112985814A (en) * | 2021-01-29 | 2021-06-18 | 中国航发沈阳发动机研究所 | Core machine pressure distortion precise control environment simulation tester |
| CN113361211A (en) * | 2021-04-15 | 2021-09-07 | 中国航发湖南动力机械研究所 | Method, system, equipment and medium for calculating aerodynamic stability of turboshaft engine |
| CN114215780A (en) * | 2021-12-06 | 2022-03-22 | 中国航发沈阳发动机研究所 | Compressor interstage total temperature measurement structure |
| CN114942119A (en) * | 2022-04-21 | 2022-08-26 | 北京理工大学 | High-temperature high-speed rotating impeller mechanical transient flow field testing system |
| CN114942119B (en) * | 2022-04-21 | 2023-10-03 | 北京理工大学 | High-temperature high-speed rotating impeller machinery transient flow field test system |
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