CN100582712C - Advanced volution combustion-chamber flow characteristic experiment system - Google Patents
Advanced volution combustion-chamber flow characteristic experiment system Download PDFInfo
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- CN100582712C CN100582712C CN200810012173A CN200810012173A CN100582712C CN 100582712 C CN100582712 C CN 100582712C CN 200810012173 A CN200810012173 A CN 200810012173A CN 200810012173 A CN200810012173 A CN 200810012173A CN 100582712 C CN100582712 C CN 100582712C
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Abstract
The invention relates to an advanced vortex combustion chamber flow quality experiment system which belongs to the experimental facility field of advanced vortex combustion chamber cold state flow quality experimental study. An integral experimental facility of the invention consists of an air current supply system, a simulated small and low-speed wind tunnel, a core experimental part, a test system and a console. By the experiment system of the invention, the back blunt bodies of different geometric structures, the distance between a front blunt body and a back blunt body, the total pressure of air current, the influence rule of speed of flow to the AVC total pressure loss, the three-dimensional velocity vector distribution, the pressure distribution, and the vortex structure in a concave cavity formed between the front blunt body and the back blunt body can be researched. By the flow field distribution rule of the AVC cold state air current circulation, the AVC performance and structure can be judged or improved. The experiment system of the invention is mainly applicable to the engine manufacturing field.
Description
Technical field
The invention belongs to the experimental provision field of advanced vortex combustion cavity cold conditions flow characteristics experimental study.
Background technology
Rotary punching engine is that U.S.'s Ramgen utility companies is being developed a kind of aviation Ramjet Technique and gas turbine technology of creatively melting is in the new concept engine of one, and its core technology is pressure rise across shock envelope technology and advanced vortex combustion technology (being called for short AVC).
The AVC principle is to arrange former and later two bluff bodies in the firing chamber, before the airflow, back bluff body, under the shear layer effect, form the serial vortex of arranging alternately and tangling or pin between two bluff bodies, not only having strengthened main flow mixes with pilot fuel, the combustion zone radial expansion, and strengthened the outer flow field pulsating energy power that resists, in the firing chamber, can form stable, burning fully, the main flame region of big control surface, lean fuel and rich fuel flame failure limit are expanded, burning efficiency improves and disposal of pollutants reduces, and burning performance obviously is superior to tradition and stays whirlpool (being called for short TVC) combustion technology.For novel concept engine-rotary punching engine, an important goal of its research improves gas turbine combustion efficient exactly, reduces pollutant emission, the key that target is achieved just is the tissue of AVC technology, just how with the AVC reasonable in technology be applied in the rotary punching unit of high speed rotating.About the stabilization technique research of combustion flame under the high speed rotating condition, relevant both at home and abroad document is very rarely seen.Therefore, AVC is carried out comprehensive, deep research and just seem very necessary.
Summary of the invention
Purpose of the present invention just provides a kind of advanced volution combustion-chamber flow characteristic experiment system of simple in structure, easy to operate, rotary punching engine AVC planar development cold conditions Study of Flow Characteristics that analysis cost is low.
Technical solution of the present invention is, advanced volution combustion-chamber flow characteristic experiment system comprises the air-flow feed system, simulates small-sized low-speed wind tunnel, core experimental piece, test macro and control desk form.The air-flow feed system comprises motor, high pressure centrifugal ventilator, admission air silencer, conciliation air door, gas pipe line tube of pressure-stabilizing.High pressure centrifugal ventilator links to each other with admission air silencer, and the admission air silencer outlet links to each other with the import of conciliation air door, reconciles the air door outlet and links to each other with the gas pipe line tube of pressure-stabilizing.The gas pipe line tube of pressure-stabilizing changes square tube with the small-sized wind-tunnel circle of simulation and links to each other by flange.Simulating small-sized low-speed wind tunnel is made up of circle commentaries on classics square tube, screens, square tube.Circle changes square tube and links to each other by flange with square tube, arranges screens between two flanges.Simulate on the small-sized low-speed wind tunnel upper cover plate and have measured hole.The core experimental piece is positioned over the small-sized low-speed wind tunnel of simulation inside.The core experimental piece is made up of square duct, preceding bluff body, back bluff body and front and back bluff body distance adjusting mechanism.The square duct inlet is wedge shape.In square duct, in axial direction arrange forward and backward bluff body.Back bluff body links to each other with the back bluff body with front and back bluff body distance adjusting mechanism.The square duct base plate has back bluff body slideway.The core experimental piece is by having instrument connection on the square duct upper cover plate.Test macro comprises velocity probe, five-hole probe, frame of axes, thermometer, barometer, pressure unit.Velocity probe is fixed on the cover plate of the small-sized low-speed wind tunnel square tube of simulation, and the stagnation pressure of velocity probe, baroport link to each other with pressure unit by plastic flexible pipe respectively, and the pressure unit signal wire links to each other with the control desk data acquisition board.Data acquisition board is placed in the control desk.Five-hole probe is fixed on the frame of axes, and five pressure ports of five-hole probe link to each other with pressure unit respectively by plastic flexible pipe, and the pressure unit signal wire links to each other with the control desk data acquisition board.Frame of axes links to each other with stepping motor, and control step motor data line links to each other with control desk with lead.
Experimental technique of the present invention: the back bluff body of selected a certain size, it is installed in the square duct of core experimental piece, regulate back bluff body and front and back bluff body distance adjusting mechanism and arrive to set a distance.Reconcile the air door flashboard and transfer to minimum, starter motor drives blower fan, regulates conciliation air door control gas and flows under given flow velocity and the stagnation pressure condition.On the computing machine of control desk, by five-hole probe location session window probe initial coordinate position is set, then, distance, scope and measuring point interval etc. that probe moves in x, y, three directions of z are set.Start-up control platform testing button, the measurement data of the space measuring point that computer acquisition arranges in advance.Utilize the correction coefficient of five-hole probe, the relational expression that fluid control fundamental equation draws, establishment disposal data program is analyzed image data.
The invention has the beneficial effects as follows, by the present invention, can study the influence of the stagnation pressure, flow velocity of back bluff body, the distance between the bluff body of front and back, the air-flow of different geometries to spiral structure in the cavity that forms between AVC pitot loss, three dimensional velocity vectors distribution, pressure distribution and front and back bluff body, by the Flow Field Distribution rule of AVC cold conditions airflow, can judge or improve its performance and structure.
Description of drawings
The present invention is further described below in conjunction with the drawings and specific embodiments.
Fig. 1 is an one-piece construction synoptic diagram of the present invention.
Fig. 2 is an experimental section structural representation of the present invention.
Fig. 3 is the small-sized wind-tunnel cover plate of a simulation of the present invention synoptic diagram.
Fig. 4 is a core experimental piece synoptic diagram of the present invention.
Fig. 5 is a core experimental piece signal rotation diagram of the present invention.
Among the figure, 1. motor, 2. high pressure centrifugal ventilator, 3. conciliation air door, 4. gas pipe line tube of pressure-stabilizing, 5. support, 6. circle changes square tube, 7. simulation small-sized low-speed wind tunnel square tube, 8. thermometer, 9. velocity probe, 10. five-hole probe, 11. velocity probes, 12. five-hole probe is fixed in frame of axes, 13. control desks, 14. signal wires and lead, 15. support, 16. screenses, 17. core experimental piece square ducts, 18. preceding bluff body, 19. back bluff bodies, the small-sized low-speed wind tunnel square tube cover plate of 20. simulations, 21. inlet velocity probe gaging hole, 22. the five-hole probe gaging hole, 23. velocity of discharge probe gaging holes, 24. core experimental piece square duct wedge shape imports, 25. core experimental piece square duct base plate, 26. back bluff body slideway, 27. pull bars, 28. governor motion supports, 29. core experimental piece square duct changes plate, 30. core experimental piece square duct side plates.
Embodiment
Advanced volution combustion-chamber flow characteristic experiment system comprises the air-flow feed system, simulates small-sized low-speed wind tunnel, core experimental piece, test macro and control desk form.The air-flow feed system comprises high pressure centrifugal ventilator 2, admission air silencer, conciliation air door 3, the gas pipe line tube of pressure-stabilizing 4 of motor 1,75KW.Regulate damper 3 flashboards and can adjust the stagnation pressure and the speed of air-flow.Simulating small-sized low-speed wind tunnel is made up of circle commentaries on classics square tube 6, screens 16, square tube 17.It is the thick steel plate of 5mm that circle changes square tube 6.Circle changes square tube 6 outlets and square tube 17 and links to each other by flange, and the layout porosity is 0.85 screens 16 between two flanges.Square tube 17 is angle iron frame structures, and cover plate 20 and base plate are the thick poly (methyl methacrylate) plates of 8mm, and sidewall paneling is the poly (methyl methacrylate) plate of 10mm, has instrument connection on the cover plate 20, does not arrange that instrument connection shut by sprue.The core experimental piece is positioned over the small-sized low-speed wind tunnel of simulation inside.The core experimental piece is made up of square passage, preceding bluff body 18, back bluff body 19 and front and back bluff body distance adjusting mechanism 27 and 28.Square duct is that 100 * 100mm square tube constitutes, square tube base plate 25 is the thick aluminium sheet of 8mm, side plate 30 is the 8mm poly (methyl methacrylate) plate for 10mm poly (methyl methacrylate) plate, cover plate 29, opens instrument connection on the cover plate.Square duct inlet 24 is that angle is less than 20 degree wedge shapes.In square duct, arrange forward and backward bluff body along direction.Before the bluff body head be rectangular parallelepiped for semicircle, rear portion, be 181.5mm along the axis direction length of core experimental piece, transverse width is 63mm, height is 100mm.The width of back bluff body changes between 20-40 at variation, thickness between the 25-60.Core experimental piece base plate has rail groove, and back bluff body is placed on the floor rail groove.Back bluff body links to each other with the back bluff body with front and back bluff body distance adjusting mechanism, and the distance adjustment scope between the forward and backward bluff body is between 25mm-70mm.Test macro comprises velocity probe 9 and 11, five-hole probe 10, frame of axes 12, thermometer 8, barometer, pressure unit composition.L shaped velocity probe 9 and 11 is fixed on the cover plate 20 of the small-sized low-speed wind tunnel square tube of simulation, and the stagnation pressure 9 of velocity probe links to each other with pressure unit by plastic flexible pipe respectively with 11 baroports, and pressure unit signal wire 14 links to each other with the control desk data acquisition board.Five-hole probe 10 is that five hole bulb-ended probes, head diameter are 5mm.Five-hole probe 10 is fixed on the frame of axes 12, and five pressure ports link to each other with pressure unit respectively by plastic flexible pipe, and pressure unit signal wire 14 links to each other with control desk 13 data acquisition board.Stationary probe frame of axes 12 can lifting, also can laterally vertically move.
Experiment:
The back bluff body of selected respectively 29.56mm, 37.92mm, 46.28mm, 50.64mm is installed on it in square duct of core experimental piece, regulates back bluff body and front and back bluff body distance adjusting mechanism to being respectively 37.8mm to set a distance, 44.1mm, 50.4mm.Reconcile the air door flashboard and transfer to minimum, starter motor drives blower fan, regulates to reconcile air door control gas and flow to stagnation pressure when being 103941.4Pa, exports to be local atmospheric pressure.On the computing machine of control desk, probe initial coordinate position is set respectively on z=10mm, 20mm, 30mm, 40mm, 50mm, 60mm, 70mm, 80mm, 90mm surface level by five-hole probe location session window, then, distance, scope and the measuring point interval etc. that probe moves at x, y both direction are set.Start-up control platform testing button, the measurement data of measuring point on the z=50mm surface level that computer acquisition arranges in advance.Utilize the correction coefficient of five-hole probe, the relational expression that fluid control fundamental equation draws, establishment disposal data program is analyzed image data.The spatial value of measuring point, inlet temperature, intake pressure, import stagnation pressure, outlet stagnation pressure, local atmospheric pressure, five-hole probe five hole force value reach the numerical value such as angle around y axle and the rotation of z axle under the computer recording.Utilize the correction coefficient of five-hole probe, the relational expression that fluid control fundamental equation draws, establishment disposal data program is analyzed image data.
Claims (1)
1. advanced volution combustion-chamber flow characteristic experiment system is characterized in that, comprises the air-flow feed system, simulates small-sized low-speed wind tunnel, core experimental piece, test macro and control desk; The air-flow feed system comprises motor (1), high pressure centrifugal ventilator (2), admission air silencer, conciliation air door (3), gas pipe line tube of pressure-stabilizing (4); High pressure centrifugal ventilator (2) links to each other with admission air silencer, and the admission air silencer outlet links to each other with the import of conciliation air door (3), reconciles air door (3) outlet and links to each other with gas pipe line tube of pressure-stabilizing (4); Gas pipe line tube of pressure-stabilizing (4) changes square tube (6) with the small-sized wind-tunnel circle of simulation and links to each other by flange; Simulating small-sized low-speed wind tunnel is made up of circle commentaries on classics square tube (6), screens (16), square tube (17); Circle changes square tube (6) and links to each other by flange with square tube (17), arranges screens (16) between two flanges; Simulate on the small-sized low-speed wind tunnel square tube cover plate (20) and have measured hole; The core experimental piece is positioned over the small-sized low-speed wind tunnel of simulation inside; The core experimental piece is made up of square duct, preceding bluff body (18), back bluff body (19) and front and back bluff body distance adjusting mechanism, and front and back bluff body distance adjusting mechanism is made up of pull bar (27) and governor motion (28); Square duct inlet (24) is a wedge shape; Bluff body (18), back bluff body (19) before in square duct, in axial direction arranging; Front and back bluff body distance adjusting mechanism links to each other with back bluff body (19); Square duct base plate (25) has back bluff body slideway (26); The core experimental piece is by having instrument connection on the square duct upper cover plate; Test macro comprises first velocity probe (9), second speed probe (11), five-hole probe (10), frame of axes (12), thermometer (8), barometer and pressure unit; First velocity probe (9) and second speed probe (11) are fixed on the small-sized low-speed wind tunnel square tube cover plate of simulation (20), stagnation pressure, the baroport of first velocity probe (9) and second speed probe (11) link to each other with pressure unit by plastic flexible pipe respectively, and the pressure unit signal wire links to each other with control desk (13) data acquisition board; Data acquisition board is placed in the control desk (13); Five-hole probe (10) is fixed on the frame of axes (12), (10) five pressure ports of five-hole probe link to each other with pressure unit respectively by plastic flexible pipe, frame of axes (12) links to each other with stepping motor, and control step motor data line links to each other with control desk with lead (14).
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| CN200810012173A CN100582712C (en) | 2008-07-02 | 2008-07-02 | Advanced volution combustion-chamber flow characteristic experiment system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2017092041A1 (en) * | 2015-12-04 | 2017-06-08 | 深圳智慧能源技术有限公司 | Injection type combustion device and protective cover thereof |
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| CN102455196B (en) * | 2010-10-27 | 2014-01-01 | 中国北车集团大连机车研究所有限公司 | Air test system used for service test of cooling device |
| CN103174547A (en) * | 2013-03-06 | 2013-06-26 | 中国航空工业集团公司沈阳发动机设计研究所 | Mixer suitable for binary spray tube |
| CN109210573B (en) * | 2018-08-10 | 2023-08-18 | 江苏大学 | Novel variable cross-section aeroengine combustion chamber |
| CN111587707B (en) * | 2020-04-20 | 2022-06-10 | 武汉大学 | Experimental device for research biology is to sand blown reaction behavior |
| CN112556978B (en) * | 2021-02-20 | 2021-05-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test airflow field rotation measuring device |
| CN113029497B (en) * | 2021-03-26 | 2022-11-15 | 中国空气动力研究与发展中心超高速空气动力研究所 | Modular test section for large-caliber hypersonic wind tunnel |
| CN114593929B (en) * | 2022-03-18 | 2022-12-23 | 南京航空航天大学 | Blunt body wake flow field generating device for PET detector and using method |
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| WO2017092041A1 (en) * | 2015-12-04 | 2017-06-08 | 深圳智慧能源技术有限公司 | Injection type combustion device and protective cover thereof |
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