CN101750204A - Engine simulator for dynamic simulation test in high-speed wind tunnel - Google Patents
Engine simulator for dynamic simulation test in high-speed wind tunnel Download PDFInfo
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- CN101750204A CN101750204A CN200910220572A CN200910220572A CN101750204A CN 101750204 A CN101750204 A CN 101750204A CN 200910220572 A CN200910220572 A CN 200910220572A CN 200910220572 A CN200910220572 A CN 200910220572A CN 101750204 A CN101750204 A CN 101750204A
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Abstract
The invention discloses an engine simulator for a dynamic simulation test in a high-speed wind tunnel. An air inlet is disposed above an outer shell, the lower end of the air inlet is communicated with a gas collecting ring, a plurality of jet pipes are uniformly arranged at the inner wall of the outer shell, and the front end of each jet pipe is communicated with the gas collecting ring; a plurality of sheets are longitudinally and transversely arranged on a circular supporting ring to form a supporting frame, a mesh is arranged on the supporting frame to form a rectifier, a total pressure measuring harrow is composed of a plurality of total pressure measuring tubes and a plurality of cantilever supporting plates, the total pressure measuring tubes are supported by the cantilever supporting plates, the cantilever supporting plates are uniformly distributed along the inner circumference of an intake duct from the front part to the back part in an interlacing manner, the total pressure measuring harrow and the pressure measuring tubes of static pressure measuring holes are gathered to be a beam along a pressure measuring tube channel and then are guided out from the upper part at the back of the outer shell, and the static pressure measuring holes and the total pressure measuring harrow are arranged at the back of the rectifier. The invention has compact structure, each parameter is strictly calculated, each component can be conveniently detached and assembled, the test performance is stable and reliable, the precision of the test is high, and the data of the test is exact.
Description
Technical field
What the present invention relates to is experiment simulator, and what be specifically related to is the engine simulator that the experiment of aviation aerodynamic force the time is used for the experiment of high-speed wind tunnel represent dynamically.
Background technology
The propulsion system of modern high-speed aircraft/aircraft adopt turbojet or turbofan mostly.The air inlet of these engines, exhaust have different influences to aerodynamic characteristics such as the lift of the aircraft/aircraft of different layouts, resistance, flight stabilities.When the purpose of engine power simulated experiment will be measured engine operation exactly, the engine inlet and outlet were to the influence of aircraft/aerodynamic characteristics of vehicle.
For using the represent dynamically experiment that the injection simulator carries out, at low-speed wind tunnel, no matter be that testing equipment or the design of injection simulator, experimental technique and external gap are little, the represent dynamically experiment of high-speed wind tunnel but has great difficulty.The general experimental section size of high-speed wind tunnel is little, causes contracting than very big of model, can be very limited for the space of design; Act on aerodynamic loading on the simulator simultaneously than big many of low-speed wind tunnel, total system will have enough intensity, rigidity; The air supply system of engine simulator will bear the pressure of high pressure draught, needs enough intensity, rigidity, and for guaranteeing the air inflow of experiment demand, air supply system also will have enough air inlet sectional areas; The device that fairing, measurement flow parameter will be arranged in the inside of engine simulator simultaneously.Therefore, under the condition of high pressure and big aerodynamic loading, realize functions such as air feed, injection, rectification, pressure measurement in the limited space of simulator, the measurement of design, processing and correlation parameter is difficulty all.
Summary of the invention
The objective of the invention is provides a kind of energy reasonable distribution simulator inner limited space at the difficulty in the design of high-speed wind tunnel engine power simulator, have functions such as the air feed of optimization, injection, rectification and pressure measurement, thereby satisfy the engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically that service condition has complete function again.
The objective of the invention is to be achieved through the following technical solutions:
The engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically comprises shell body (simulating complete engine) and is installed in shell body interior induction apparatus, fairing and pressure tester; Described induction apparatus comprises oval type air intake opening, collector ring and a plurality of jet pipe; Air intake opening is positioned at the last end face of the front portion of shell body, the lower end of air intake opening is connected with collector ring, collector ring is ring cavity and the inwall that is positioned at shell body, and on a plurality of jet pipes inwall that is laid in shell body symmetrically, the front end of a plurality of jet pipes communicates with collector ring;
Described fairing comprises support ring, a plurality of thin plate and stainless (steel) wire, and a plurality of thin plates evenly are laid on the support ring of circular ring type in length and breadth, and the windward side of thin plate is a spliting type, reduces the resistance of air-flow.Support ring is fixedlyed connected with shell body, and stainless (steel) wire is laid on the bracing frame that a plurality of thin plates set up; Rectifier is positioned at the back of jet pipe;
Air-flow enters jet pipe from collector ring, and after the jet pipe ejection, the rectifier of flowing through makes the more even of air-flow change.
Above-mentioned pressure tester comprises total pressure measurement rake, a plurality of static bole, piezometric tube passage, piezometric tube channel cover and a plurality of static pressure piezometric tube; Above-mentioned a plurality of static bole is positioned on the inwall of shell body back segment and along the shell body inner periphery evenly to be laid.The total pressure measurement rake passes for a plurality of stagnation pressure piezometric tube parallel with air intake duct and cantilever support plate formation, stagnation pressure piezometric tube default position from the cantilever support plate, and the arrangement position of stagnation pressure piezometric tube is determined through calculating.Each cantilever support plate supports a plurality of stagnation pressure piezometric tube.The air intake opening of all stagnation pressure piezometric tube and static bole are on the same cross section of air intake duct, and the cantilever support plate is staggered front to back even laying along the shell body inner periphery, are staggered front to back to lay the blockage percentage that effectively reduces the air intake duct correspondence position.The front and rear edge of cantilever support plate is arranged to circular arc, reduces the resistance of air-flow.A plurality of stagnation pressure piezometric tube and static pressure piezometric tube are drawn from the top of shell body back segment after the piezometric tube passage collects the gathering bunchy, and piezometric tube links to each other with the data acquisition system (DAS) of outside, obtains the correlation parameter of mixed airflow, is used for the processing of experimental data.Total pressure measurement rake and static bole are positioned at the rear portion of rectifier, near the nozzle of simulator.The piezometric tube passage is ring channel structures and the outside that is positioned at back segment.There is the piezometric tube channel cover outside of piezometric tube passage, makes the profile of engine complete.Pressure tester is positioned at the back of rectifier, near the nozzle of engine.
Above-mentioned collector ring has the width and 3-5mm thickness (determining by calculating when designing according to different concrete conditions) of 30-40mm, and injection air-flow YS can distribute after entering collector ring comparatively uniformly.
The windward side of a plurality of thin plates of above-mentioned rectifier is a spliting type, reduces the resistance of air-flow.
The cantilever support plate of above-mentioned a plurality of total pressure measurement rakes is staggered front to back even distribution along the inner periphery of shell body.
The air intake opening of the stagnation pressure piezometric tube of above-mentioned a plurality of static bole and total pressure measurement rake is on the same cross section of air intake duct.
There is the piezometric tube channel cover outside of above-mentioned piezometric tube passage.
The course of work of the present invention and principle:
1, high pressure injection air communication is crossed wing, hanger enters in the simulator, and piezometric tube also will be drawn in hanger and wing.
2, high pressure injection air-flow enters collector ring from air intake opening, be full of collector ring rapidly after, enter jet pipe, through behind the venturi of jet pipe, the injection gas velocity presses off the beginning to be increased, and increases the blow down ratio of simulator exhaust.
3, behind the mixed airflow process rectifier of jet pipe injection air-flow that sprays and the tunnel airstream formation that enters simulated engine, more be tending towards even.The piezometric tube of total pressure measurement rake, static bole links to each other with data acquisition system (DAS), obtains the parameter of simulator nozzle place mixed airflow.
4, in experiment, introduce high pressure draught as the injection air-flow from independent supply air line, the injection air-flow enters collector ring from oval type air intake opening, collector ring is a ring cavity, has certain width and thickness, the injection air-flow can distribute therein comparatively uniformly, is the jet pipe air feed that distributes along the air intake duct inner periphery.
5, air-flow ram compression when jet pipe sprays increases, and with the rectifier of flowing through after the tunnel airstream that enters simulated engine mixes, it is even that rectifier helps mixed airflow.The outlet of jet pipe and the distance between rectifier are through calculating.
6, mixed air-flow is through arriving total pressure measurement rake and static bole place behind the rectifier, and the piezometric tube of total pressure measurement rake and static bole is connected with the acquisition system of outside, obtains the correlation parameter of mixed airflow, is used for the processing of the experimental data in later stage.
Characteristics of the present invention are: compact conformation, and the parameter of each element obtains through calculating, and interelement distance determines that as calculated the design science of whole engine simulator is rigorous.Each zero, parts easy accessibility, experimental performance is stable, reliable, precision height, experimental data are accurate.
Description of drawings
Fig. 1 is a general structure synoptic diagram of the present invention.
Fig. 2 is the position view of the present invention on model.
Fig. 3 is that synoptic diagram is looked on the left side of Fig. 2.
Fig. 4 is that the A-A of Fig. 2 is to cross-sectional schematic.
Embodiment
Shown in accompanying drawing 1～4, engine simulator of the present invention is connected in screw on the hanger 20 of model 19, and what link to each other with hanger 20 is preceding point of fixity 2 and back point of fixity 8; Tunnel airstream FT enters from front end of the present invention.
The engine simulator that is used for high-speed wind tunnel represent dynamically experiment comprises (simulate complete engine) shell body 1 and is installed in shell body 1 interior induction apparatus, fairing and pressure tester; Described shell body 1 is the complete engine body of simulation, and above-mentioned induction apparatus comprises air intake opening 3, collector ring 5 and a plurality of jet pipe 4; Air intake opening 3 is positioned at the last end face of the front portion of shell body 1, the lower end of air intake opening 3 is connected with collector ring 5, collector ring 5 is ring cavity and the inwall that is positioned at shell body 1, and on a plurality of jet pipes 4 inwall that is laid in shell body 1 symmetrically, the front end of a plurality of jet pipes 4 communicates with collector ring 5;
Fairing, comprise support ring 7, a plurality of thin plate 18 and stainless (steel) wire, a plurality of thin plates 18 evenly are laid in length and breadth on the support ring 7 of circular ring type and constitute bracing frame, the windward side of thin plate 18 is a spliting type, support ring 7 is fixedlyed connected with shell body 1, and stainless (steel) wire is laid on the bracing frame that a plurality of thin plates 18 set up; Rectifier 6 is positioned at the back of jet pipe 4;
Injection air-flow YS enters jet pipe 4 from collector ring 5, and after jet pipe 4 ejections, the rectifier 6 of flowing through makes the more even of air-flow change.
Pressure tester comprises total pressure measurement rake 12, a plurality of static bole 14, piezometric tube passage 9, piezometric tube channel cover 15 and a plurality of static pressure piezometric tube 10; Above-mentioned a plurality of static bole 14 is positioned on the inwall of shell body 1 back segment 16 and along shell body 1 inner periphery evenly to be laid, and static bole 14 links to each other with the data acquisition system (DAS) of outside by static pressure piezometric tube 10.Total pressure measurement rake 12 be that a plurality of stagnation pressure piezometric tube 11 and the cantilever support plate 13 parallel with air intake duct 17 constitutes, and stagnation pressure piezometric tube 11 default position from cantilever support plate 13 is passed, and the arrangement position of stagnation pressure piezometric tube 11 is definite through calculating.Each cantilever support plate 13 supports a plurality of stagnation pressure piezometric tube 11.The air intake opening of all stagnation pressure piezometric tube 11 and static bole 14 are on the same cross section of air intake duct 17, but cantilever support plate 13 is staggered front to back even laying along shell body 1 inner periphery, effectively reduces the blockage percentage of air intake duct 17 correspondence positions.The front and rear edge of cantilever support plate 13 is arranged to circular arc, reduces the resistance of air-flow.A plurality of stagnation pressure piezometric tube 11 are drawn from the upper back of shell body 1 after piezometric tube passage 9 collects the gathering bunchy with static pressure piezometric tube 10.
Total pressure measurement rake 12 and static bole 14 are positioned at the rear portion of rectifier 6, near the nozzle of simulator.Piezometric tube passage 9 is ring channel structures and the outside that is positioned at shell body 1 back segment 16.
A plurality of stagnation pressure piezometric tube 11 link to each other with the data acquisition system (DAS) of outside with static pressure piezometric tube 10, obtain the correlation parameter of mixed airflow, are used for the processing of experimental data.
There is piezometric tube channel cover 15 outside of piezometric tube passage 9, makes the profile of engine complete.
Apparatus of the present invention have complete air supply system, ejection system, measuring system, by the limited simulator space of rational distribution, optimize the design of function element such as air feed, injection, rectification, pressure measurement, under the condition of high pressure, big aerodynamic loading, designed the engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically with complete function.
Claims (6)
1. the engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically comprises shell body (1) and is installed in shell body (1) interior induction apparatus, fairing and pressure tester; It is characterized in that:
Described induction apparatus comprises oval type air intake opening (3), collector ring (5) and a plurality of jet pipe (4); Air intake opening (3) is positioned at the last end face of the front portion of shell body (1), the lower end of air intake opening (3) is connected with collector ring (5), collector ring (5) is ring cavity and the inwall that is positioned at shell body (1), on a plurality of jet pipes (4) inwall that is laid in shell body (1) symmetrically, the front end of a plurality of jet pipes (4) communicates with collector ring (5);
Described fairing, comprise the support ring (7) of circular ring type, a plurality of thin plate (18) and stainless (steel) wire, a plurality of thin plates (18) are evenly laid support ring (7) in length and breadth and are gone up the formation bracing frame, support ring (7) is fixedlyed connected with shell body (1), and stainless (steel) wire is laid on the bracing frame that a plurality of thin plates (18) set up; Rectifier (6) is positioned at the back of jet pipe (4);
Above-mentioned pressure tester comprises total pressure measurement rake (12), a plurality of static bole (14), piezometric tube passage (9), piezometric tube channel cover (15) and a plurality of static pressure piezometric tube (10); Above-mentioned a plurality of static bole (14) is positioned on the inwall of shell body (1) back segment (16) and along shell body (1) inner periphery evenly to be laid; Total pressure measurement rake (12) is that a plurality of stagnation pressure piezometric tube (11) and the cantilever support plate (13) parallel with air intake duct (17) constitutes, and stagnation pressure piezometric tube (11) default position from cantilever support plate (13) is passed; Each cantilever support plate (13) supports a plurality of stagnation pressure piezometric tube (11); The air intake opening of all stagnation pressure piezometric tube (11) and static bole (14) are on the same cross section of air intake duct (17), and cantilever support plate (13) is staggered front to back even laying along shell body (1) inner periphery; The front and rear edge of cantilever support plate (13) is arranged to circular arc; A plurality of stagnation pressure piezometric tube (11) are drawn from the top of shell body (1) back segment (16) after piezometric tube passage (9) collects the gathering bunchy with static pressure piezometric tube (10); Total pressure measurement rake (12) and static bole (14) are positioned at the rear portion of rectifier (6), near the nozzle of simulator; Piezometric tube passage (9) is ring channel structures and the outside that is positioned at back segment (16).
2. the engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically according to claim 1, it is characterized in that: above-mentioned collector ring (5) has width and the 3-5mm thickness of 30-40mm.
3. the engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically according to claim 1, it is characterized in that: the windward side of a plurality of thin plates (18) of above-mentioned rectifier (6) is a spliting type.
4. the engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically according to claim 1 is characterized in that: the cantilever support plate (13) of above-mentioned a plurality of total pressure measurement rakes (12) is staggered front to back even distribution along the inner periphery of shell body.
5. the engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically according to claim 1 is characterized in that: above-mentioned a plurality of static boles (14) are on the same cross section of air intake duct (17) with the air intake opening of the stagnation pressure piezometric tube (11) of total pressure measurement rake (12).
6. the engine simulator that is used for the experiment of high-speed wind tunnel represent dynamically according to claim 1, it is characterized in that: there is piezometric tube channel cover (15) outside of above-mentioned piezometric tube passage (9).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910220572XA CN101750204B (en) | 2009-12-08 | 2009-12-08 | Engine simulator for dynamic simulation test in high-speed wind tunnel |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910220572XA CN101750204B (en) | 2009-12-08 | 2009-12-08 | Engine simulator for dynamic simulation test in high-speed wind tunnel |
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| CN101750204A true CN101750204A (en) | 2010-06-23 |
| CN101750204B CN101750204B (en) | 2012-07-18 |
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| CN200910220572XA Expired - Fee Related CN101750204B (en) | 2009-12-08 | 2009-12-08 | Engine simulator for dynamic simulation test in high-speed wind tunnel |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102519704A (en) * | 2011-11-08 | 2012-06-27 | 中国科学院力学研究所 | Pulse wind tunnel thermal jet flow experiment gas source feed platform |
| 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 |
| CN104807610A (en) * | 2015-05-19 | 2015-07-29 | 中国航天空气动力技术研究院 | Sprayer nozzle used for tail jet flow interference test |
| CN105424309A (en) * | 2015-11-03 | 2016-03-23 | 南京航空航天大学 | Testing stand for dynamic airflow response in single/double duct mode switching process |
| CN106338399A (en) * | 2016-08-16 | 2017-01-18 | 中国航空工业集团公司沈阳发动机设计研究所 | Transonic and ultrasonic total static pressure probe measurement truth value calculation method |
| CN107470821A (en) * | 2017-07-25 | 2017-12-15 | 武汉冶钢结构有限责任公司 | Assembling fixture and its installation Nozzle methods for wind tunnel ejector |
| CN112197294A (en) * | 2020-09-21 | 2021-01-08 | 中国航发沈阳发动机研究所 | Rectifying plate |
| CN112432759A (en) * | 2020-11-10 | 2021-03-02 | 北京动力机械研究所 | Axial-symmetry double-channel air inlet channel outlet back pressure adjusting and flow field measuring device |
| CN112432760A (en) * | 2020-11-10 | 2021-03-02 | 北京动力机械研究所 | Axial-symmetry double-channel air inlet channel outlet back pressure adjusting and flow field measuring method |
| CN112729853A (en) * | 2020-12-24 | 2021-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Method for correcting resistance of main engine air inlet of propeller aircraft |
| CN112985822A (en) * | 2021-04-20 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet channel test device for simulating coupling effect of air inlet channel and fan |
| CN114199497A (en) * | 2021-10-29 | 2022-03-18 | 东风商用车有限公司 | Wind field environment simulation wind tunnel structure for engine bench test |
| CN116399546A (en) * | 2023-06-07 | 2023-07-07 | 中国航空工业集团公司沈阳空气动力研究所 | Low-blocking-degree large-attack-angle driving mechanism and driving method for aircraft model |
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2009
- 2009-12-08 CN CN200910220572XA patent/CN101750204B/en not_active Expired - Fee Related
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102519704A (en) * | 2011-11-08 | 2012-06-27 | 中国科学院力学研究所 | Pulse wind tunnel thermal jet flow experiment gas source feed platform |
| 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 |
| CN103115747B (en) * | 2012-12-21 | 2015-07-08 | 中国飞行试验研究院 | Large-size composite material air inlet passage measuring rake |
| CN104807610A (en) * | 2015-05-19 | 2015-07-29 | 中国航天空气动力技术研究院 | Sprayer nozzle used for tail jet flow interference test |
| CN105424309A (en) * | 2015-11-03 | 2016-03-23 | 南京航空航天大学 | Testing stand for dynamic airflow response in single/double duct mode switching process |
| CN105424309B (en) * | 2015-11-03 | 2017-12-15 | 南京航空航天大学 | A kind of mono-/bis-duct mode transition procedure air-flow dynamic rerponse test stand |
| CN106338399A (en) * | 2016-08-16 | 2017-01-18 | 中国航空工业集团公司沈阳发动机设计研究所 | Transonic and ultrasonic total static pressure probe measurement truth value calculation method |
| CN106338399B (en) * | 2016-08-16 | 2019-03-08 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of calculation method across the total static probe measurement true value of supersonic speed |
| CN107470821A (en) * | 2017-07-25 | 2017-12-15 | 武汉冶钢结构有限责任公司 | Assembling fixture and its installation Nozzle methods for wind tunnel ejector |
| CN107470821B (en) * | 2017-07-25 | 2019-06-25 | 武汉一冶钢结构有限责任公司 | Assembling fixture and its installation Nozzle methods for wind tunnel ejector |
| CN112197294A (en) * | 2020-09-21 | 2021-01-08 | 中国航发沈阳发动机研究所 | Rectifying plate |
| CN112197294B (en) * | 2020-09-21 | 2022-04-01 | 中国航发沈阳发动机研究所 | Rectifying plate |
| CN112432759A (en) * | 2020-11-10 | 2021-03-02 | 北京动力机械研究所 | Axial-symmetry double-channel air inlet channel outlet back pressure adjusting and flow field measuring device |
| CN112432760A (en) * | 2020-11-10 | 2021-03-02 | 北京动力机械研究所 | Axial-symmetry double-channel air inlet channel outlet back pressure adjusting and flow field measuring method |
| CN112432760B (en) * | 2020-11-10 | 2023-05-12 | 北京动力机械研究所 | Axisymmetric double-channel inlet channel outlet counter pressure adjustment and flow field measurement method |
| CN112432759B (en) * | 2020-11-10 | 2023-06-02 | 北京动力机械研究所 | Axisymmetric double-channel inlet channel outlet counter-pressure adjusting and flow field measuring device |
| CN112729853A (en) * | 2020-12-24 | 2021-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Method for correcting resistance of main engine air inlet of propeller aircraft |
| CN112985822A (en) * | 2021-04-20 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet channel test device for simulating coupling effect of air inlet channel and fan |
| CN112985822B (en) * | 2021-04-20 | 2021-08-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet channel test device for simulating coupling effect of air inlet channel and fan |
| CN114199497A (en) * | 2021-10-29 | 2022-03-18 | 东风商用车有限公司 | Wind field environment simulation wind tunnel structure for engine bench test |
| CN116399546A (en) * | 2023-06-07 | 2023-07-07 | 中国航空工业集团公司沈阳空气动力研究所 | Low-blocking-degree large-attack-angle driving mechanism and driving method for aircraft model |
| CN116399546B (en) * | 2023-06-07 | 2023-09-12 | 中国航空工业集团公司沈阳空气动力研究所 | Low-blocking-degree large-attack-angle driving mechanism and driving method for aircraft model |
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