CN104483093A - Variable mach number transonic rigid free jet nozzle - Google Patents
Variable mach number transonic rigid free jet nozzle Download PDFInfo
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- CN104483093A CN104483093A CN201410776293.2A CN201410776293A CN104483093A CN 104483093 A CN104483093 A CN 104483093A CN 201410776293 A CN201410776293 A CN 201410776293A CN 104483093 A CN104483093 A CN 104483093A
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Abstract
The invention relates to a variable mach number transonic rigid free jet nozzle which comprises a left sidewall (1), a right sidewall (10), an upper support plate (4) and a lower support plate (5), wherein the left sidewall (1) and the right sidewall (10) are bilaterally symmetric, and are fixed and connected into an open nozzle frame in a supporting way by virtue of the upper support plate (4) and the lower support plate (5), which are symmetrically arranged; an upper molded surface mechanism (2) and a lower molded surface mechanism (3) are longitudinally and symmetrically arranged in the nozzle frame. The variable mach number transonic rigid free jet nozzle is characterized by also comprising an upper right semicircular bearing (6) and an upper left semicircular bearing (7). According to the variable mach number transonic rigid free jet nozzle, the pneumatic flow field is good, and a design method is reasonable; a semicircular shaft design is adopted for the tail end of a rigid molded surface, so that the area of an outlet of the open nozzle is kept constant, and an airflow field at the outlet of the nozzle is uniform and regular; an obvious uniform test area can be formed at the outlet of the nozzle, so that test requirements are met, and good effects are achieved in a high-altitude stand air blowing test.
Description
Technical field:
Wind tunnel test or aeromotor HIGHER ALTITUDE TEST FACILITY aerodynamic testing.
Background technology:
The important means that free jet test is tested as simulated altitude Inlet engine matching, its admission gear effect is the Parameter Conditions such as Mach number, stagnation pressure, air-flow angle making the air-flow through this device reach testing requirements simulation in free jet test in regulation pilot region.Free jet admission gear (abbreviation jet pipe) is the core section setting up FLOW FIELD IN FREE JETS, the height of its designing quality, directly determine the flow field quality of free jet, determine reliability and the precision of free jet test data, determine the test capability of free jet and the operational efficiency in cabin.
Transonic jet pipe adopts to receive and expands structure, air-flow is made evenly to accelerate to the velocity of sound by the low pressure velocity of sound at contraction section, then air-flow (expansion arc) evenly constant entropy accelerated expansion by venturi, reaches required Mach number to nozzle exit, and forms Mach Number Distribution even test rhomboid.The area ratio of test section and venturi determines the Mach number that will reach.
Whether can transfer from jet pipe Mach number, early stage jet pipe mostly is fixing jet pipe, but along with the development of altitude simulation design and running technology, jet pipe Mach number regulative mode is from initial symmetrical plug and grating type, slide block type finally, and Grazing condition, half flexible and rigidity three kinds of forms of progressively developing into current main use.Owing to being subject to flow field uniformity and the restriction that can obtain test Mach number scope, the structure of domestic main employing flexible plate nozzle, its schematic diagram as shown in Figure 1.
To the Mach number continuously adjustabe jet pipe of this type of two-dimensional symmetric, domestic and international research mainly concentrates on flexible joint nozzle version.But be subject to the restriction of rigidity jet pipe Mach number range of adjustment and the continuous adjustment structure of Mach number, its research lacks relatively, the defects such as existing rigidity jet pipe has nozzle exit square-section to be difficult to ensure to some extent, the poor repeatability that the interval limited and rigid type panel deformation of test Mach number causes.
Herein for the Mach number continuously adjustabe jet pipe of this type of two-dimensional symmetric, propose a kind of open type free jet transonic speed jet pipe based on fixed-area, this nozzle structure is simple, easy to operate, take into account synchronism and subsonic speed, transonic speed, supersonic trial stretch, ensure that the flow quality that test site is excellent, operational efficiency improves greatly.
Summary of the invention:
Simplicity of design, reliably Mach number can regulate admission gear continuously, under ensureing high-quality flow field prerequisite, the continuous range of adjustment of jet pipe Mach number is made to expand subsonic speed/supersonic speed to, simultaneously by fixing profile end half circular shaft Rotation Design, guarantee that open type nozzle exit area is constant, and it is even, regular to realize nozzle exit air velocity distribution.Improve its service efficiency and practicality.
The invention provides a kind of free jet transonic speed rigidity jet pipe of variable Mach number, comprise symmetrical left side wall (1), right side wall (10), upper support plate (4) and lower support plate (5), left side wall (1) and right side wall (10) carry out position by the upper backup pad (4) that is arranged symmetrically with and lower supporting plate (5) to it to be fixed and support and connection form the jet pipe framework of open type; Upper profile mechanism (2) is arranged in jet pipe framework with lower profile mechanism (3) is laterally zygomorphic, it is characterized in that, also comprises right semi-circle bearing (6), upper left semicircle bearing (7),
Wherein go up profile mechanism (2) and comprise mo(u)ld top half panel (2-1), upper right semi-circle axle ear (2-4), upper left semicircle axle ear (2-5), upper right semi-circle axle ear (2-4), upper left semicircle axle ear (2-5) are positioned at the left and right sides of mo(u)ld top half panel (2-1) endpiece;
Lower profile mechanism (3) comprises mo(u)ld bottom half panel (3-1), lower right semi-circle axle ear (3-4), lower left semicircle axle ear (3-5); Lower right semi-circle axle ear (3-4), lower left semicircle axle ear (3-5) are positioned at the left and right sides of mo(u)ld bottom half panel (3-1) endpiece;
Wherein go up right semi-circle axle ear (2-4), upper left semicircle axle ear (2-5) carries out rotary support with left side wall (1) and right side wall (10) respectively respectively by upper right semi-circle bearing (6), upper left semicircle bearing (7) and be connected; Wherein descend right semi-circle axle ear (3-4), lower left semicircle axle ear (3-5) carries out rotary support with left side wall (1) and right side wall (10) be connected respectively by lower right semi-circle bearing (8), lower left semicircle bearing (9).
Further, upper profile mechanism (2) also comprises the upper bogie (2-2), the upper sealing support plate (2-3) that are fixed on mo(u)ld top half panel (2-1), upper sealing support plate (2-3) and upper backup pad (4) rigid contact, lower profile mechanism (3) also comprises the lower bogie (3-2), lower seal support plate (3-3), lower seal support plate (3-3) and lower supporting plate (5) rigid contact that are fixed on mo(u)ld bottom half panel (3-1).
Further, also comprise profile driving mechanism (11) and lower profile driving mechanism (12), upper profile driving mechanism (11) comprises pivot pin (11-4), upper bracket (11-5) on pivot pin (11-2) on driving cylinder (11-1), first, upper connecting rod (11-3), second; Lower profile driving mechanism (12) comprises lower driving cylinder (12-1), the first lower shaft pin (12-2), lower link (12-3), the second lower shaft pin (12-4), undersetting (12-5),
Upper bogie (2-2) is fixedly connected with upper bracket (11-5) bolt, lower bogie (3-2) is fixedly connected with undersetting (12-5) bolt, upper driving cylinder (11-1) is fixed in air-stable room, be connected with upper connecting rod (11-3) by pivot pin (11-2) on first, upper connecting rod (11-3) is connected with upper bracket (11-5) by pivot pin (11-4) on second; Lower driving cylinder (12-1) is symmetrical in driving cylinder (11-1) and is fixed in air-stable room, be connected with lower link (12-3) by the first lower shaft pin (12-2), lower link (12-3) is connected with undersetting (12-5) by the second lower shaft pin (12-4).
For the free jet jet pipe that outlet is open type, the design of its semicircle oblique crank Z ear effectively ensure that rigidity profile rotary middle spindle is nozzle contour outlet sideline, thus effectively ensure that in Mach number adjustment process, the sectional area of nozzle exit and its venturi control the unifying datum of height.Upper and lower profile driving mechanism can realize jet pipe Mach number wider subsonic speed, supersonic range effective, fast regulate.
Advantage:
A) half circular shaft design solves rigidity jet pipe Mach number and regulates the impact limited its exit flow quality continuously.
B) mode of profile mechanism adjustment is simple, reliable up and down.
C) achieve Mach number continuously adjustabe, range of adjustment can cover subsonic speed, transonic speed, supersonic speed.
Effect:
This variable Mach number free jet transonic speed rigidity jet pipe aerodynamics is excellent, reasonable design method.Rigidity profile end half circular shaft designs, and guarantee that open type nozzle exit area is constant, and it is even, regular to realize nozzle exit air velocity distribution.An obvious even test region can be obtained in outside nozzle, meet testing requirements, respond well in HIGHER ALTITUDE TEST FACILITY blowing test.
Accompanying drawing illustrates:
Fig. 1 is jet pipe fragmentary three-dimensional view figure;
Fig. 2 jet pipe upper and lower rigidity profile mechanism front elevation;
Fig. 3 jet pipe front elevational schematic.
1, left side wall; 2, upper profile mechanism; 3, lower profile mechanism; 4, upper backup pad; 5, lower supporting plate; 6, upper right semi-circle bearing; 7, upper left semicircle bearing; 8, lower right semi-circle bearing; 9, lower left semicircle bearing; 10, right side wall; 11, upper profile driving mechanism; 12, lower profile driving mechanism; 2-1, mo(u)ld top half panel; 2-2, upper bogie; 2-3, upper sealing support plate; 2-4, upper right semi-circle axle ear; 2-5, upper left semicircle axle ear; 3-1, mo(u)ld bottom half panel; 3-2, lower bogie; 3-3, lower seal support plate; 3-4, lower right semi-circle axle ear; ; 3-5, lower left semicircle axle ear; 11-1, upper driving cylinder; Pivot pin on 11-2, first; 11-3, upper connecting rod; Pivot pin on 11-4, second; 11-5, upper bracket; 12-1, lower driving cylinder; 12-2, the first lower shaft pin; 12-3, lower link; 12-4, the second lower shaft pin; 12-5, undersetting.
Embodiment:
Accompanying drawings 1 to 3, the free jet transonic speed rigidity jet pipe of a kind of variable Mach number of the present invention, comprise symmetrical left side wall 1, right side wall 10, upper support plate 4 and lower support plate 5, left side wall 1 and right side wall 10 carry out position by the upper backup pad 4 that is arranged symmetrically with and lower supporting plate 5 to it to be fixed and support and connection form the jet pipe framework of open type; Upper profile mechanism 2 is arranged in jet pipe framework with lower profile mechanism 3 is laterally zygomorphic, it is characterized in that, also comprises right semi-circle bearing 6, upper left semicircle bearing 7,
Wherein go up profile mechanism 2 and comprise mo(u)ld top half panel 2-1, upper right semi-circle axle ear 2-4, upper left semicircle axle ear 2-5, upper right semi-circle axle ear 2-4, upper left semicircle axle ear 2-5 are positioned at the left and right sides of mo(u)ld top half panel 2-1 endpiece;
Lower profile mechanism 3 comprises mo(u)ld bottom half panel 3-1, lower right semi-circle axle ear 3-4, lower left semicircle axle ear 3-5; Lower right semi-circle axle ear 3-4, lower left semicircle axle ear 3-5 are positioned at the left and right sides of mo(u)ld bottom half panel 3-1 endpiece;
Wherein go up right semi-circle axle ear 2-4, upper left semicircle axle ear 2-5 carries out rotary support with left side wall 1 and right side wall 10 respectively respectively by upper right semi-circle bearing 6, upper left semicircle bearing 7 and be connected; Right semi-circle axle ear 3-4, lower left semicircle axle ear 3-5 is wherein descended to carry out rotary support with left side wall 1 and right side wall 10 be connected respectively by lower right semi-circle bearing 8, lower left semicircle bearing 9.
Further, upper profile mechanism 2 also comprises the upper bogie 2-2 being fixed on mo(u)ld top half panel 2-1, upper sealing support plate 2-3, upper sealing support plate 2-3 and upper backup pad 4 rigid contact, lower profile mechanism 3 also comprise be fixed on mo(u)ld bottom half panel 3-1 lower bogie 3-2, lower seal support plate 3-3, lower seal support plate 3-3 and lower supporting plate 5 rigid contact.
Further, also comprise profile driving mechanism 11 and lower profile driving mechanism 12, upper profile driving mechanism 11 comprises pivot pin 11-4, upper bracket 11-5 on pivot pin 11-2 on driving cylinder 11-1, first, upper connecting rod 11-3, second; Lower profile driving mechanism 12 comprises lower driving cylinder 12-1, the first lower shaft pin 12-2, lower link 12-3, the second lower shaft pin 12-4, undersetting 12-5,
Upper bogie 2-2 is fixedly connected with upper bracket 11-5 bolt, lower bogie 3-2 is fixedly connected with undersetting 12-5 bolt, upper driving cylinder 11-1 is fixed in air-stable room, be connected with upper connecting rod 11-3 by pivot pin 11-2 on first, upper connecting rod 11-3 is connected with upper bracket 11-5 by pivot pin 11-4 on second; Lower driving cylinder 12-1 is symmetrical in driving cylinder 11-1 and is fixed in air-stable room, is connected with lower link 12-3 by the first lower shaft pin 12-2, and lower link 12-3 is connected with undersetting 12-5 by the second lower shaft pin 12-4.
Claims (3)
1. the free jet of a variable Mach number transonic speed rigidity jet pipe, comprise symmetrical left side wall (1), right side wall (10), upper support plate (4) and lower support plate (5), left side wall (1) and right side wall (10) carry out position by the upper backup pad (4) that is arranged symmetrically with and lower supporting plate (5) to it to be fixed and support and connection form the jet pipe framework of open type; Upper profile mechanism (2) is arranged in jet pipe framework with lower profile mechanism (3) is laterally zygomorphic, it is characterized in that, also comprises right semi-circle bearing (6), upper left semicircle bearing (7),
Wherein go up profile mechanism (2) and comprise mo(u)ld top half panel (2-1), upper right semi-circle axle ear (2-4), upper left semicircle axle ear (2-5), upper right semi-circle axle ear (2-4), upper left semicircle axle ear (2-5) are positioned at the left and right sides of mo(u)ld top half panel (2-1) endpiece;
Lower profile mechanism (3) comprises mo(u)ld bottom half panel (3-1), lower right semi-circle axle ear (3-4), lower left semicircle axle ear (3-5); Lower right semi-circle axle ear (3-4), lower left semicircle axle ear (3-5) are positioned at the left and right sides of mo(u)ld bottom half panel (3-1) endpiece;
Wherein go up right semi-circle axle ear (2-4), upper left semicircle axle ear (2-5) carries out rotary support with left side wall (1) and right side wall (10) respectively respectively by upper right semi-circle bearing (6), upper left semicircle bearing (7) and be connected; Wherein descend right semi-circle axle ear (3-4), lower left semicircle axle ear (3-5) carries out rotary support with left side wall (1) and right side wall (10) be connected respectively by lower right semi-circle bearing (8), lower left semicircle bearing (9).
2. the free jet of variable Mach number according to claim 1 transonic speed rigidity jet pipe, it is characterized in that, upper profile mechanism (2) also comprises the upper bogie (2-2), the upper sealing support plate (2-3) that are fixed on mo(u)ld top half panel (2-1), upper sealing support plate (2-3) and upper backup pad (4) rigid contact, lower profile mechanism (3) also comprises the lower bogie (3-2), lower seal support plate (3-3), lower seal support plate (3-3) and lower supporting plate (5) rigid contact that are fixed on mo(u)ld bottom half panel (3-1).
3. the free jet of variable Mach number according to claim 2 transonic speed rigidity jet pipe, it is characterized in that, also comprise profile driving mechanism (11) and lower profile driving mechanism (12), upper profile driving mechanism (11) comprises pivot pin (11-4), upper bracket (11-5) on pivot pin (11-2) on driving cylinder (11-1), first, upper connecting rod (11-3), second; Lower profile driving mechanism (12) comprises lower driving cylinder (12-1), the first lower shaft pin (12-2), lower link (12-3), the second lower shaft pin (12-4), undersetting (12-5),
Upper bogie (2-2) is fixedly connected with upper bracket (11-5) bolt, lower bogie (3-2) is fixedly connected with undersetting (12-5) bolt, upper driving cylinder (11-1) is fixed in air-stable room, be connected with upper connecting rod (11-3) by pivot pin (11-2) on first, upper connecting rod (11-3) is connected with upper bracket (11-5) by pivot pin (11-4) on second; Lower driving cylinder (12-1) is symmetrical in driving cylinder (11-1) and is fixed in air-stable room, be connected with lower link (12-3) by the first lower shaft pin (12-2), lower link (12-3) is connected with undersetting (12-5) by the second lower shaft pin (12-4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410776293.2A CN104483093A (en) | 2014-12-15 | 2014-12-15 | Variable mach number transonic rigid free jet nozzle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410776293.2A CN104483093A (en) | 2014-12-15 | 2014-12-15 | Variable mach number transonic rigid free jet nozzle |
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| CN104483093A true CN104483093A (en) | 2015-04-01 |
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| CN201410776293.2A Pending CN104483093A (en) | 2014-12-15 | 2014-12-15 | Variable mach number transonic rigid free jet nozzle |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104819302A (en) * | 2015-04-17 | 2015-08-05 | 中国科学院力学研究所 | Sealing system of variable mach number spraying pipe |
| CN106596032A (en) * | 2016-12-21 | 2017-04-26 | 中国燃气涡轮研究院 | Variable Mach number nozzle mechanism having large-stroke range and high precision |
| CN108195547A (en) * | 2017-12-29 | 2018-06-22 | 重庆大学 | A kind of half soft adjustable contraction block of wall of continous way transonic wind tunnel nozzle section and larynx block sealing system |
| CN108195548A (en) * | 2017-12-29 | 2018-06-22 | 重庆大学 | The vertical forced synchronism formula fluid pressure drive device of half soft wall larynx block of continous way transonic wind tunnel nozzle section |
| CN108195546A (en) * | 2017-12-29 | 2018-06-22 | 重庆大学 | For the electric drive integrated unit of half soft wall of continous way transonic wind tunnel jet pipe |
| CN108362464A (en) * | 2017-12-29 | 2018-08-03 | 重庆大学 | Hydraulic-driven integrated unit for half soft wall of continous way transonic wind tunnel jet pipe |
| CN114034461A (en) * | 2021-11-18 | 2022-02-11 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Follow-up locking mechanism for adjusting sheet |
| CN114414197A (en) * | 2022-03-28 | 2022-04-29 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Variable Mach number spray pipe of flexible wallboard of prebending |
| CN115371938A (en) * | 2022-07-28 | 2022-11-22 | 中国航天空气动力技术研究院 | Spray pipe suitable for hypersonic continuous variable Mach number |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104819302A (en) * | 2015-04-17 | 2015-08-05 | 中国科学院力学研究所 | Sealing system of variable mach number spraying pipe |
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| CN106596032A (en) * | 2016-12-21 | 2017-04-26 | 中国燃气涡轮研究院 | Variable Mach number nozzle mechanism having large-stroke range and high precision |
| CN108362464A (en) * | 2017-12-29 | 2018-08-03 | 重庆大学 | Hydraulic-driven integrated unit for half soft wall of continous way transonic wind tunnel jet pipe |
| CN108195548A (en) * | 2017-12-29 | 2018-06-22 | 重庆大学 | The vertical forced synchronism formula fluid pressure drive device of half soft wall larynx block of continous way transonic wind tunnel nozzle section |
| CN108195546A (en) * | 2017-12-29 | 2018-06-22 | 重庆大学 | For the electric drive integrated unit of half soft wall of continous way transonic wind tunnel jet pipe |
| CN108195547A (en) * | 2017-12-29 | 2018-06-22 | 重庆大学 | A kind of half soft adjustable contraction block of wall of continous way transonic wind tunnel nozzle section and larynx block sealing system |
| CN108195548B (en) * | 2017-12-29 | 2021-02-19 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Vertical forced synchronous hydraulic driving device for semi-flexible wall throat block of continuous transonic wind tunnel jet pipe section |
| CN108195546B (en) * | 2017-12-29 | 2021-02-19 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Electric drive integrated unit for continuous transonic wind tunnel nozzle semi-flexible wall |
| CN108195547B (en) * | 2017-12-29 | 2021-07-30 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Semi-flexible wall contraction block and throat block sealing system of continuous transonic wind tunnel jet pipe section |
| CN108362464B (en) * | 2017-12-29 | 2021-11-09 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Hydraulic drive integrated unit for continuous transonic wind tunnel nozzle semi-flexible wall |
| CN114034461A (en) * | 2021-11-18 | 2022-02-11 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Follow-up locking mechanism for adjusting sheet |
| CN114034461B (en) * | 2021-11-18 | 2024-03-29 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Follow-up locking mechanism for adjusting plate |
| CN114414197A (en) * | 2022-03-28 | 2022-04-29 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Variable Mach number spray pipe of flexible wallboard of prebending |
| CN115371938A (en) * | 2022-07-28 | 2022-11-22 | 中国航天空气动力技术研究院 | Spray pipe suitable for hypersonic continuous variable Mach number |
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