CN207408101U - A kind of inlet total pressure and the generator that distorts to vortex flow coupling - Google Patents
A kind of inlet total pressure and the generator that distorts to vortex flow coupling Download PDFInfo
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- CN207408101U CN207408101U CN201721264125.0U CN201721264125U CN207408101U CN 207408101 U CN207408101 U CN 207408101U CN 201721264125 U CN201721264125 U CN 201721264125U CN 207408101 U CN207408101 U CN 207408101U
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Abstract
Distortion generator is coupled the utility model discloses a kind of inlet total pressure and to vortex flow, including by the sequentially connected flow measuring section of flange, eddy flow segment occurred and distortion developed regime, distortion net is respectively arranged with before and after the eddy flow segment occurred.The utility model aims to solve the problem that current stagnation pressure and swirl flow distortion generator can only be simulated for one of which distorted version, the coupling effect of two kinds of distortion can't be simulated, and vane type and cavate rotational flow generator are also complex there are fabrication design, and swirl strength adjusts the problems such as difficulty is big.The utility model can sunykatuib analysis inlet total pressure and the coupling that distorts on vortex flow engine or compressor/fan are influenced, while distortion for inlet total pressure distortion and to vortex flow or independent simulate provides easy and low-cost solution.
Description
Technical field
The utility model is related to a kind of inlet distortion generators, are especially a kind of inlet total pressure and vortex flow are coupled abnormal
Become generator, belong to aerospace field.
Background technology
Modern advanced fighter, stealth bomber and unmanned plane is improve radar invisible performance, mostly using S curved intake ports,
Such as F-22, F-117 and " neuron " unmanned fighter.S curved intake ports are while aircraft Stealth Fighter is improved, unavoidably
Form total pressure distortion and to whirlpool type swirl flow distortion in engine intake, it is abundant that the presence of inlet distortion can reduce engine stabilizer
Degree or even initiation surge/stall, threaten flight safety.
It is to assess inlet total pressure distortion and swirl flow distortion to engine performance and the influence stablized, the SAE S16 committees are first
After published the standards such as AIR1419 and AIR5686, be respectively used to instruct the evaluation of engine charge stagnation pressure and swirl flow distortion.I
State GJB/Z64A-2004 (K) standard provides aeroturbine jet and turbofan inlet distortion evaluation guide,
But there are no relevant criterion guides to the evaluation of swirl flow distortion.
Under conditions of air inlet/engine Collaborative experiment is lacked, inlet distortion must be by distorting what generating means generated
Uneven inlet air conditions are simulated.Simulation for total pressure distortion, SAE AIR1419 recommend distortion net, China
GJB/Z64A-2004 (K) then recommends plate and is simulated.Whole whirlpool, concentration are commonly divided into for swirling inlet distortion
Whirlpool, to whirlpool and horizontal four kinds of whirlpool, swirl flow distortion generator is generally classified as vane type, wingtip vortex formula and eddy flow in AIR5686
Cavate three classes.Foreign countries, Germany Fottner in 1987 etc. propose that two kinds generate swirl flow distortion mode, Yi Zhongshi in ground experiment
Using guide vane, whole whirlpool and the swirl flow distortion form to whirlpool can be generated, another kind is to be generated using dalta wing to vortex flow,
Swirl strength is adjusted by changing the dalta wing angle of attack.2008, Sheoran etc. developed a kind of cavate rotational flow generator, passes through
Whole whirlpool can be simulated, to the even circumferential two groups of eddy flows to volute formula in whirlpool by changing the intake method of vortex chamber.The country, Peng Cheng
First, Jiang Jian, Ye Fei, Tu Bao Feng etc. successively devise associated vanes formula rotational flow generator, high by adjusting blade angle, blade
The modes such as degree, the number of blade, blade bent angle realize the adjustment of swirl strength and form.
Existing stagnation pressure and swirl flow distortion generator can only be simulated for single stagnation pressure or swirl flow distortion, it is impossible to mould
Intend coupling effect of two kinds of distortion to engine, influence the science and accuracy of inlet distortion analyzing evaluation.Correlation rotation
Stream distortion generator, complicated there are organization plan, design difficulty of processing is big, and swirl strength adjusts the problems such as inconvenient, influences to test
Efficiency and cost.
The content of the invention
The shortcomings that the utility model is overcome in the prior art provides a kind of inlet total pressure and vortex flow is coupled and distort
Generator, it is intended to which solving current stagnation pressure and swirl flow distortion generator can only be simulated for one of which distorted version, also
The coupling effect of two kinds of distortion cannot be simulated, and vane type and cavate rotational flow generator are also more multiple there are fabrication design
Miscellaneous, swirl strength adjusts the problems such as difficulty is big.The utility model being capable of sunykatuib analysis inlet total pressure and the coupling that distorts to vortex flow
Effect influences engine or compressor/fan, simulates while being inlet total pressure distortion and distort to vortex flow or individually and carries
Easy and low-cost solution is supplied.
The technical solution of the utility model is：A kind of inlet total pressure and the generator that distorts to vortex flow coupling, including passing through
The sequentially connected flow measuring section of flange, eddy flow segment occurred and distortion developed regime, are set respectively before and after the eddy flow segment occurred
There is distortion net；The flow measuring section include into air bell mouth and a diameter of D, length be 1.5D etc. straight cylinders；The eddy flow hair
Raw section waits straight cylinders and the tablet being arranged in cylinder including a diameter of D, and trailing edge and the round bar of the tablet are connected, the circle
Bar both ends are hinged respectively with the sliding block in the sliding slot of cylinder rear, and leading edge center and the nut of the tablet are hinged, described
Nut is arranged on the screw rod being connected with stepper motor；The distortion developed regime is the grade straight cylinders that length and diameter is D.
Compared with prior art, the utility model has the advantages that：
(1) the utility model can both realize stagnation pressure and the list to vortex flow distortion by net and the adjustable angle of attack tablet of distorting
Solely simulation, and can realize stagnation pressure and the coupled simulation to vortex flow distortion, analysis is contributed to solve stagnation pressure and distort to vortex flow
Coupling effect is to the affecting laws of engine performance and stability；
(2) by the adjusting to the tablet angle of attack, realization can be facilitated to continuously adjust vortex intensity of flow, the tablet angle of attack is got over
Greatly, generation is bigger to vortex intensity of flow；
(3) swirl strength can be increased by reasonable set to front and rear distortion net fine-structure mesh blocked-off region, realizes higher eddy flow
The simulation of intensity；
(4) for fixed distortion net and the tablet angle of attack, when experiment charge flow rate changes, distortion generator generates
Swirl angle is held essentially constant, and can conveniently determine the size of swirl angle under various inlet flow test operating mode；
(5) tablet angle of attack driving structure is simple and reliable, is controlled in real time using stepper motor, can simulate and distort to vortex flow
Influence of the dynamic changing process of intensity to engine；
(6) the utility model segment design, organization plan is simple, and processing and manufacturing is easy, can complete various form and strong
Engine test under the distorting to vortex flow of the total pressure distortion of degree and varying strength, advantageously reduces experimentation cost and time,
Improve test efficiency；
(7) the utility model not only can be directly used for aero-engine stagnation pressure and to vortex flow distortion coupling test, may be used also
Research and experiment applied to compressor/fan inlet stagnation pressure and to vortex flow distortion coupling rule.
Description of the drawings
The utility model will illustrate by example and with reference to the appended drawing, wherein：
Fig. 1 is the structure diagram of this distortion generator；
Fig. 2 is the structure diagram of flow measuring section；
Fig. 3 is the structure diagram of eddy flow segment occurred；
Fig. 4 is the structure diagram of distortion net.
Specific embodiment
A kind of inlet total pressure and the generator that distorts to vortex flow coupling, as shown in Figure 1, being sent out including flow measuring section 1, eddy flow
Raw section 2, distortion net 3 and distortion developed regime 4, each section are connected with each other by the identical flange of interface form.By flow measuring section 1
The smaller uniform inlet air conditions of pitot loss are obtained, and realize the measurement of charge flow rate；Eddy flow segment occurred 2 is realized miscarries to being vortexed
Raw and intensity adjusting；Two distortion nets 3 are separately mounted to the front and rear of eddy flow developed regime 2, realize the simulation of total pressure distortion, and can
It is further enhanced by the reasonable Arrangement of fine-structure mesh to vortex intensity of flow；The distortion effect of developed regime 4 is that distortion net 3 and eddy flow occurs
The stagnation pressure and can obtain stable development to vortex flow distortion that section 2 generates, rear passes through flange and Distorted Flow Field measuring device
Or engine intake connection, to carry out related inlet airflow distortion test and research work.
As shown in Fig. 2, flow measuring section into air bell mouth 1-1 and grade straight cylinders 1-2 by forming.Into air bell mouth 1-1 using double
Line style air inlet quasi spline is turned round, ensure air inlet uniformity and reduces pitot loss, circumferential uniformly distributed several hydrostatic measuring points are used in its outlet
In the measurement of charge flow rate.The length of straight cylinders 1-2 is waited as 1.5 times of drum diameter D, ensures static pressure measurement section airflow homogeneity
From the influence of downstream pressure distortion.
As shown in figure 3, eddy flow segment occurred is by waiting straight cylinders 2-1, tablet 2-2, sliding block 2-3, round bar 2-4, stepper motor 2-
5th, the components such as screw rod 2-6 and nut 2-7 form.Tablet 2-2 trailing edges are connected with round bar 2-4, and round bar 2-4 both ends are cut with scissors with sliding block 2-3
Even, sliding block 2-3 is mounted in the sliding slot waited on straight cylinders, and thus tablet 2-2 trailing edges can realize rotation and horizontal shifting；It is flat
Plate 2-2 leading edges center is hinged with nut 2-7, by stepper motor 2-5 vertically-mounted screw rod is driven to rotate and is driven nut 2-7,
It realizes moving up and down for tablet 2-2 leading edges, the adjustment that the tablet 2-2 angles of attack can be achieved is acted by said mechanism.When tablet is with coming
When stream forms positive incidence, tablet lower surface is met to air-flow, and tablet low pressure is higher than upper pressure, the pressure differential above and below tablet
Under, tablet lower stream of airflow can bypass tablet both sides of the edge upwards, inwardly roll to form wingtip vortex, so as to fulfill abnormal to whirlpool type eddy flow
The simulation of change.Swirl strength is adjusted by the tablet angle of attack, when the tablet angle of attack is 0 °, is not generated to vortex flow, the increase of the tablet angle of attack,
Swirl strength increases, but the general tablet angle of attack is maximum no more than 15 °, and the tablet angle of attack crosses conference and causes stall event, causes and does not wish
The pitot loss of prestige and unstable eddy flow.The shape of tablet 2-2 is not limited to simple rectangle shown in Fig. 3, can also use
Triangle, trapezoidal or other are special-shaped, and plate section also can be replaced lift aerofoil profile to enhance wingtip vortex effect, to optimize to being vortexed
Flow the simulation of distortion.
As shown in figure 4, distortion net is made of supporting rack 3-1, supporting network 3-2 and fine-structure mesh.Supporting rack 3-1 and supporting network 3-2
Effect be that fine-structure mesh is supported, supporting network 3-2 be 360 ° of the whole networks, be welded on supporting rack 3-1, supporting network 3-2 select net
Hole and the larger stainless (steel) wire of mesh wire diameter, ensure it with relatively low airflow obstruction degree and enough structural strengths.Fine-structure mesh
Specification and shape needs reasonably selected according to the total pressure distortion situation of simulation.The present invention is respectively set before and after rotational flow generator
It is also gentle to the blocking action of air-flow before net using fine-structure mesh while the effect of one distortion net is realization total pressure distortion simulation
Circulate the pressure loss generated later, to increase tablet top and the bottom air-flow differential, and then enhances to vortex intensity of flow.Such as
The online half portion of front-distortion sets fine-structure mesh blocked-off region, and air-flow can be reduced by rear plate upper air static pressure, in rear distortion off the net half
Portion sets fine-structure mesh blocked-off region, and due to fine-structure mesh blocking action, tablet lower part static pressure can raise before net, is thus distorted using former and later two
The distribution of net fine-structure mesh position can also generate tablet pressure difference up and down.
Distortion developed regime is the straight cylinders that wait that length is 1D, and effect is the stagnation pressure for forming distortion net and eddy flow segment occurred
Stable development can be obtained with to vortex flow distortion.
The present invention can complete independent total pressure distortion experiment, individually to vortex flow aberration test and stagnation pressure and to vortex flow
Distort coupling test.
When only carrying out total pressure distortion experiment, the tablet angle of attack can be adjusted to 0 °, simulated and required according to total pressure distortion, design is thin
Network planning lattice and shape, and it is online to be disposed at one of distortion.To reduce interference of the other structures to experiment, also can remove
Eddy flow segment occurred and a distortion net, total pressure distortion examination is carried out using flow measuring section, a distortion net and distortion developed regime
It tests.
When only carrying out to vortex flow aberration test, two distortion nets can be removed or using be not added with the distortion net of fine-structure mesh into
Row experiment, can be according to vortex flow be formed direction requirement, preceding to be further enhanced by the net that distorts to vortex intensity of flow
The semicircle fine-structure mesh of same size is set respectively under latter two distortion is online.It is flat to be controlled remotely by a computer stepper motor adjustment
The plate angle of attack is realized and the real-time dynamic of vortex intensity of flow is adjusted.
When carrying out stagnation pressure and coupling aberration test to vortex flow, the real-time dynamic adjustment of generation and intensity to vortex flow is still
The stepper motor adjustment tablet angle of attack is controlled remotely by a computer to realize.It is simulated and required according to total pressure distortion, design fine-structure mesh rule
Lattice and shape, when simulation by tablet positive incidence formed to vortex flow when, if fine-structure mesh is distributed in upper semi-circle, be disposed at
The first half of front-distortion net；If fine-structure mesh is distributed in lower half circle, the lower half for the net that distorts after being disposed at；If fine-structure mesh is in circle
The top and the bottom of shape are distributed, then the fine-structure mesh in upper semi-circle are arranged on front-distortion net, and the fine-structure mesh in lower half circle is arranged on
After distort net, it is similar simulation by tablet negative angle of attack formed to vortex flow when, then in the lower half of front-distortion net and rear abnormal
The first half for becoming net sets fine-structure mesh, can so be significantly increased again while the simulation of total pressure distortion collection of illustrative plates is realized strong to vortex flow
Spend simulation context.
Claims (6)
1. a kind of inlet total pressure and the generator that distorts to vortex flow coupling, it is characterised in that：Including sequentially connected by flange
Flow measuring section, eddy flow segment occurred and distortion developed regime, distortion net is respectively arranged with before and after the eddy flow segment occurred；The stream
Measurement section include into air bell mouth and a diameter of D, length be 1.5D etc. straight cylinders；The eddy flow segment occurred includes a diameter of D
Wait straight cylinders and the tablet that is arranged in cylinder, trailing edge and the round bar of the tablet are connected, the round bar both ends respectively with peace
Sliding block in the sliding slot of cylinder rear is hinged, and leading edge center and the nut of the tablet are hinged, and the nut is arranged on and walks
On the screw rod of stepper motor connection；The distortion developed regime is the grade straight cylinders that length and diameter is D.
2. a kind of inlet total pressure according to claim 1 and the generator that distorts to vortex flow coupling, it is characterised in that：It is described
Into air bell mouth using twisted-pair cable type air inlet type face, several hydrostatic measuring points are circumferentially being evenly distributed with into the outlet of air bell mouth.
3. a kind of inlet total pressure according to claim 1 and the generator that distorts to vortex flow coupling, it is characterised in that：It is described
Tablet is rectangle, triangle or trapezoidal.
4. a kind of inlet total pressure according to claim 1 and the generator that distorts to vortex flow coupling, it is characterised in that：It is described
Plate section is rectangle or lift aerofoil profile.
5. a kind of inlet total pressure according to claim 1 and the generator that distorts to vortex flow coupling, it is characterised in that：It is described
Distortion net includes supporting rack and the supporting network being welded on supporting rack.
6. a kind of inlet total pressure according to claim 5 and the generator that distorts to vortex flow coupling, it is characterised in that：Institute
It states and fine-structure mesh is provided on supporting network.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721264125.0U CN207408101U (en) | 2017-09-29 | 2017-09-29 | A kind of inlet total pressure and the generator that distorts to vortex flow coupling |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721264125.0U CN207408101U (en) | 2017-09-29 | 2017-09-29 | A kind of inlet total pressure and the generator that distorts to vortex flow coupling |
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| CN207408101U true CN207408101U (en) | 2018-05-25 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107687948A (en) * | 2017-09-29 | 2018-02-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of inlet total pressure and distorted to vortex flow coupling generator and aberration test method |
| CN110595788A (en) * | 2019-10-24 | 2019-12-20 | 中国科学院工程热物理研究所 | Distortion generator bearing frame for compressor |
| CN111346528A (en) * | 2020-04-29 | 2020-06-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Preparation method of cold jet flow mixed gas with variable specific heat ratio |
| CN112665863A (en) * | 2020-11-10 | 2021-04-16 | 西安交通大学 | Radial rotating plate type adjustable total pressure distortion generator |
-
2017
- 2017-09-29 CN CN201721264125.0U patent/CN207408101U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107687948A (en) * | 2017-09-29 | 2018-02-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of inlet total pressure and distorted to vortex flow coupling generator and aberration test method |
| CN107687948B (en) * | 2017-09-29 | 2023-09-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet total pressure and vortex flow coupling distortion generator and distortion test method |
| CN110595788A (en) * | 2019-10-24 | 2019-12-20 | 中国科学院工程热物理研究所 | Distortion generator bearing frame for compressor |
| CN111346528A (en) * | 2020-04-29 | 2020-06-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Preparation method of cold jet flow mixed gas with variable specific heat ratio |
| CN112665863A (en) * | 2020-11-10 | 2021-04-16 | 西安交通大学 | Radial rotating plate type adjustable total pressure distortion generator |
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