CN110173354B - Fixed-geometry binary supersonic air inlet with pneumatic compression molded surface - Google Patents
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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Abstract
The invention discloses a fixed geometry binary supersonic air inlet with a pneumatic compression profile, which comprises an upper wall surface, a lower wall surface and two side wall surfaces, wherein the upper wall surface and the lower wall surface are symmetrically arranged, the upper wall surface, the lower wall surface and the two side wall surfaces are symmetrically arranged, and the upper wall surface, the lower wall surface and the two side wall surfaces jointly enclose an inner channel and an expansion section which extends backwards from the inner channel; and the rear part of the auxiliary air inlet channel is provided with a flow discharge air slit communicated with the inner channel. Introducing a small amount of low-speed high-pressure gas into a main channel of the air inlet channel through the auxiliary air inlet channel to form a pneumatic compression surface and a pneumatic throat; along with the increase of the mach number of the incoming flow, the pressure of the gas introduced by the auxiliary gas inlet channel is increased, and the aerodynamic throat formed at low mach number is large; the pneumatic throat is small when the Mach number is high, and the automatic adjustment of the pneumatic profile of the air inlet in the working range is realized. Therefore, the self-starting Mach number of the air inlet channel can be greatly reduced, and a high-flow coefficient and symmetrical outlet flow field under different incoming flow conditions is realized.
Description
Technical Field
The invention relates to the field of aircraft design, in particular to a binary supersonic air inlet channel.
Background
The air inlet channel provides low-speed high-pressure gas for the combustion chamber of the engine, and the kinetic energy of the high-speed air flow is converted into pressure potential energy. The supersonic air inlet is one of three major components of a ramjet engine, and the performance and the normal working range of the engine are directly influenced by the performance of the supersonic air inlet. The main parameters for evaluating the starting performance of the air inlet channel comprise self-starting Mach number, flow coefficient, total pressure recovery coefficient, external resistance, outlet flow field distortion degree and the like; in addition, the requirement of wide Mach number working range of the supersonic air inlet is also considered.
The existing binary supersonic air inlet can be divided into three types according to the position relation of a supersonic air flow stagnation process relative to an air inlet lip: external pressure type air inlet channel, internal pressure type air inlet channel and mixed pressure type air inlet channel. The internal surface of the internal pressure type air inlet channel is an ideal inverted Laval nozzle, the external surface is straight, all compression is realized in an internal channel, and the internal pressure type air inlet channel has the advantages of small external additional resistance, symmetrical outlet flow field, small loss and the like, but the throat area required by low Mach number is larger than that of the designed Mach number, so that the serious starting problem exists, and the engineering application is difficult to realize; the stagnation process of the airflow of the external pressure type air inlet is completely finished before the lip, so that the starting problem does not exist, but the external compression amount of the lip is large, the external resistance of the air inlet is increased, shock wave separation can be caused even under the condition of low incoming flow Mach number, and meanwhile, the flow coefficient is lower under the condition of low incoming flow Mach number due to the large compression amount before the lip; the air current stagnation process of mixed compression formula intake duct comprises partial external compression and partial internal compression, and external compression formula intake duct and internal compression formula are intake the major and minor shortcoming and have been traded off, but when wide mach number during operation, the low flow coefficient of mach number just has the start-up problem, and high throat mach number leads to the big scheduling problem of total pressure loss under the high mach number. And all air inlets are difficult to realize high-efficiency work in a wide Mach number range under the condition of fixed geometry. Therefore, the self-starting problem of the supersonic air inlet channel, the improved flow coefficient and total pressure recovery coefficient, the reduced outlet flow field distortion, the reduced external resistance and the like are important factors which must be considered for realizing the high-efficiency work of the supersonic air inlet channel under the wide work Mach number. In order to solve these problems, researchers have conducted extensive research, wherein variable geometry inlets are optimized to improve inlet startup, broaden operating mach numbers, and improve inlet aerodynamics by adjusting inlet geometry. However, the conventional variable geometry inlet is realized by adding variable geometry accessories on the solid wall surface of the inlet, the accessories increase the structural weight and complexity of the inlet and reduce the reliability of the inlet, so that the design of a novel profile-adjusted variable geometry supersonic inlet is significant.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a fixed-geometry binary supersonic air inlet with a pneumatic compression profile under the condition of not using a variable-geometry mechanical structure in order to reduce the self-starting Mach number of the supersonic air inlet, widen the working Mach number range, improve the flow coefficient, obtain a symmetrical outlet flow field and the like.
The technical scheme is as follows: a fixed geometry binary supersonic speed air inlet with a variable pneumatic compression profile comprises an upper wall surface, a lower wall surface, two side wall surfaces, an upper wall surface, a lower wall surface and an expansion section, wherein the upper wall surface and the lower wall surface are symmetrically arranged, the two side wall surfaces, the upper wall surface, the lower wall surface and the two side wall surfaces are symmetrically arranged to form an inner channel and the expansion section extends backwards from the inner channel; the rear part of the upper auxiliary air inlet channel and the rear part of the lower auxiliary air inlet channel are both provided with a flow discharge air slit communicated with the inner channel.
Has the advantages that: the invention designs two auxiliary air inlet channels which are symmetrically arranged on the upper wall surface and the lower wall surface and correspond to the upper wall surface and the lower wall surface, utilizes the stamping effect of high-speed incoming flow to convert the incoming flow of a high-speed low-pressure air inlet channel into high-pressure low-speed air flow in the auxiliary channel, then introduces the high-pressure low-speed air inlet channel into a main flow channel of the air inlet channel through the auxiliary channel, forms a separation bag consisting of high-pressure low-speed air in the main flow channel, forms an aerodynamic surface in the main flow channel to compress the air in the main flow channel, and achieves the purposes of speed reduction and pressure increase. In addition, under different incoming flow Mach numbers, the size of the wedge angle at the front ends of the upper wall surface and the lower wall surface is unchanged, so that the compression degree of incoming flow of the auxiliary air inlet channel is improved along with the increase of the incoming flow Mach number, the gas pressure ratio introduced into the main flow channel of the air inlet channel is also improved, the size of a separation bag formed in the main flow channel is increased, the compression strength of air flow in the main flow channel is increased by the formed pneumatic profile, and meanwhile, the size of the separation bag is increased to ensure that the size of a pneumatic throat formed in the main flow channel of the air inlet channel is also reduced. When the Mach number is low, the pneumatic molded surface is compressed less, and the pneumatic throat of the air inlet channel is larger; the compression of the aerodynamic profile is enhanced and the throat of the air inlet is reduced at high Mach number, namely the aerodynamic profile of the air inlet and the sectional area of the throat are automatically adjusted at different working Mach numbers. The advantages of such an adjustment are: 1. the actual circulation profile of the air inlet channel adapts to the self-starting requirement of the air inlet channel, and the self-starting Mach number is reduced; 2. different operating Mach number states correspond to different actual circulation profiles of the air inlet duct, so that the performance of the air inlet duct in each different state is improved.
And the air inlet channel is subjected to primary compression through the front edges of the upper wall surface and the lower wall surface which are symmetrically distributed, and the whole air inlet channel is symmetrically distributed, so that the air inlet channel has the advantage of symmetrical outlet flow fields, and the flow coefficient of the air inlet channel is basically kept to be 1.0 after the air inlet channel is started.
Furthermore, the upper auxiliary air inlet channel and the lower auxiliary air inlet channel are symmetrically arranged.
Furthermore, the foremost ends of the upper wall surface and the lower wall surface are provided with only one stage of compression angle, and no other compression angle is arranged after the stage of compression angle.
Furthermore, the compression angles at the foremost ends of the upper wall surface and the lower wall surface are both compressed at the upper side and the lower side and are in an arrow shape.
Furthermore, the fixed-geometry binary supersonic air inlet is of an overall symmetrical structure.
Drawings
FIG. 1(a) is a schematic cross-sectional view of a fixed geometry binary supersonic inlet having a variable aerodynamic compression profile according to the present invention;
FIG. 1(b) is an enlarged partial view of a fixed geometry binary supersonic inlet auxiliary inlet of the present invention with a variable aerodynamic compression profile;
FIG. 2(a) is a Mach number equivalent diagram of the case where the Mach number of the incoming flow is 3.5 (the outlet back pressure is one time of the incoming flow pressure) in the present invention
FIG. 2(b) is a flow chart of the aerodynamic profile of the present invention at an incoming flow Mach number of 3.5 through-flow (outlet back pressure is one time incoming flow pressure)
FIG. 3(a) is a Mach number equivalent diagram of the case where the incoming flow Mach number is 3.5 (the outlet back pressure is 15 times the incoming flow pressure) according to the present invention
FIG. 3(b) is a flow chart of the aerodynamic profile of the present invention at an incoming flow Mach number of 3.5 (15 times the incoming flow pressure at the outlet back pressure)
FIG. 4 is a distribution diagram of the Mach number of the inlet exit under the condition that the Mach number of the incoming flow is 3.5 (the exit back pressure is 15 times of the incoming flow pressure) according to the invention
FIG. 5(a) is a Mach number equivalent diagram of the case where the incoming flow Mach number is 1.5 (outlet back pressure is one time of incoming flow pressure) in the present invention
FIG. 5(b) is a Mach number equivalent diagram of the case where the incoming flow Mach number is 1.8 (outlet back pressure is one time of incoming flow pressure) in the present invention
FIG. 5(c) is a Mach number equivalent diagram of the case where the incoming flow Mach number is 1.9 (outlet back pressure is one time of incoming flow pressure) in the present invention
FIG. 6(a) is a flow chart of the aerodynamic profile of the present invention with through-flow at an incoming flow Mach number of 1.9 (outlet back pressure is one time incoming flow pressure)
FIG. 6(b) is a flow chart of the aerodynamic profile of the present invention with a through flow Mach number of 2.5 (outlet back pressure is one time of the incoming flow pressure)
FIG. 6(c) is a flow chart of the aerodynamic profile of the present invention at an incoming flow Mach number of 3.5 through-flow (outlet back pressure is one time incoming flow pressure)
FIG. 6(d) is a flow chart of the aerodynamic profile of the present invention at an incoming flow Mach number of 4.5 through-flow (outlet back pressure is one time incoming flow pressure)
FIG. 6(e) is a flow chart of the aerodynamic profile of the present invention at an incoming flow Mach number of 5 through flows (outlet back pressure is one time incoming flow pressure)
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in figure 1(a) (b),
the invention provides a fixed geometry binary supersonic air inlet with a variable pneumatic compression profile, which comprises an upper wall surface, a lower wall surface (an upper wall surface 11 and a lower wall surface 12) which are symmetrically arranged, two side wall surfaces (not shown) which are symmetrically arranged, an inner channel 21 which is formed by the upper wall surface, the lower wall surface and the two side wall surfaces and an expansion section 22 which extends backwards from the inner channel 21. The outer side of the upper wall surface forms an upper auxiliary inlet duct 4 which extends from the front to the rear together with the inner passage. The upper auxiliary intake duct 4 is surrounded by an upper auxiliary wall surface 13 located above the upper wall surface 11 together with the upper wall surface 11. The outer side of the lower wall surface 12 forms a lower auxiliary intake duct 5 extending from the front to the rear in common with the inner passage 3. The lower auxiliary intake duct 5 is enclosed by a lower auxiliary wall surface 14 located below the lower wall surface 12 and the lower wall surface 12.
In order to let the intake duct main entrance produce the compression profile, the rear portion of two auxiliary intake ducts 4, 5 in the upper and lower wall outside all is equipped with the earial drainage gas slit 7, 8 with the inner channel intercommunication, through earial drainage gas slit 7, 8, earial drainage gas slit 7 run through upper wall 4, earial drainage gas slit 7 be used for with last auxiliary intake duct 4 and inner channel 21 UNICOM, earial drainage gas slit 8 will be under auxiliary intake duct 5 and inner channel 21 UNICOM. The auxiliary air inlet channel introduces the captured low-speed high-pressure gas into the main flow channel 21 of the air inlet channel through the flow discharge air gap, and because the compression degree of the gas in the main flow channel is smaller than that of the auxiliary air inlet channel, the gas introduced into the main flow channel can form a pneumatic compression surface and a pneumatic throat in the main flow channel.
The main flow gas of the air inlet channel is in a straight channel without a compression angle and cannot be compressed, so that the aim of speed reduction and increase cannot be achieved; the auxiliary air inlet channel is ingeniously utilized, so that the gas of the main flow channel forms a shock wave at a compression surface formed by introducing the gas into the auxiliary air inlet channel, the gas of the main flow channel is compressed to a certain degree, the gas flow flows backwards until the front end of the expansion section 22, a positive shock wave is formed at the front end of the expansion section 22 under the condition that back pressure is applied to the outlet of the air inlet channel, the supersonic gas flow is changed into subsonic gas flow after being subjected to the positive shock wave, and the subsonic gas flow is further decelerated and pressurized in the expansion section 22 until reaching the outlet of the air inlet channel and reaching the state required by a combustion chamber.
Correspondingly, the leading edge compression angle and the channel size of the auxiliary air inlet channel are kept unchanged, along with the increase of the incoming flow Mach number, the air pressure obtained after the air flow passes through the same compression angle and the auxiliary air inlet channel is correspondingly increased, and then the angle of a compression surface formed after the air gap is discharged is increased, the throat is reduced (the pneumatic throat under the low Mach number is large, the air inlet channel is easy to start under the low Mach number, the pneumatic throat under the high Mach number is small, and the requirements of the air flow compression degree and the throat size under the high Mach number are met) so as to realize the self-adaption of the pneumatic profiles of the air inlet channel under different incoming flow Mach numbers.
Furthermore, the front edges of the upper wall surface and the lower wall surface of the air inlet channel are symmetrically designed, so that the flow capture coefficient of the air inlet channel is basically kept to be 1.0 under any incoming flow Mach number, and the whole structure (the upper wall surface, the lower wall surface and the backward extending expansion section) of the air inlet channel is symmetrically designed, so that the outlet flow field of the air inlet channel is also a symmetric flow field.
Next, in order to verify the present invention, the following air inlet was designed to carry out a numerical simulation experiment. In an experiment, the parameters of the novel air inlet channel designed by the invention are as follows, the compression angle of the front ends of the upper wall surface and the lower wall surface of the air inlet channel is 12 degrees, the length of the auxiliary channel is 201mm, the width of the auxiliary channel is 4mm, and the widths of three grooves for communicating the main channel and the auxiliary channel of the air inlet channel are respectively 3mm, 4mm and 3 mm. The inlet has a geometric throat height of 128mm, a throat discharge groove width of 15mm, and an inlet outlet height of 204mm, as shown in fig. 1(a) (b), and fig. 1(b) is a partial enlarged view of the auxiliary inlet in fig. 1 (a).
The first verification experiment (the basic function of reducing and boosting the speed of the inlet channel can be realized), the range of the workable mach number of the inlet channel design is 2-5, the intermediate mach number Ma is 3.5 for calculation, the calculation of the condition of through flow (the outlet pressure is the same as the incoming flow pressure) and the calculation of the condition of adding 15 times of the incoming flow pressure at the outlet of the inlet channel are carried out, and the result analysis is as follows:
as shown in fig. 2(a) and fig. 2(b), which are a mach number equivalent graph and a flow chart of an aerodynamic profile of the air inlet channel under the condition of through-flow, it can be found that under the condition of through-flow, supersonic incoming flow is divided into two parts, namely, a main flow channel and an auxiliary air inlet channel, the air flow of the auxiliary air inlet channel is compressed by a wedge at the front ends of the upper and lower wall surfaces to be changed into low-speed high-pressure air, then the low-speed high-pressure air enters the main flow channel through a main flow channel and an auxiliary channel communication channel, the upper and lower separation zones are formed in the main flow channel, a convergent and divergent aerodynamic channel is formed in the main flow channel, the aerodynamic profile at the front part of the separation zones further compresses the air of the main flow channel, the air flow is changed into low supersonic flow after passing through an aerodynamic throat channel, and then continues to accelerate through the aerodynamic divergent channel. FIGS. 3(a) and 3(b) show graphs of Mach number equivalent and aerodynamic profiles in the channel after 15 times of oncoming flow backpressure was applied to the inlet. By observing the attached figure 3(a), after the back pressure is added, the supersonic incoming flow is compressed by the pneumatic compression molded surface, and under the action of the back pressure, a normal shock wave is formed at the downstream of the throat of the air inlet channel, the air flow is changed into the subsonic flow from the supersonic flow, and the subsonic flow is further decelerated and diffused in the expanding channel. Under the condition of the back pressure, the static pressure at the outlet of the air inlet channel is increased by 14.5 times of the pressure of the incoming flow, and the Mach number of the outlet is 0.42, so that the basic function of the air inlet channel, namely speed reduction and pressurization, is realized. Observing fig. 3(b) shows that the flow pattern of the pneumatic profile after applying the counter-pressure is substantially the same as the through-flow situation (fig. 2(b)), which indicates that the pneumatic profile after applying the counter-pressure has little effect and remains effective. As shown in fig. 4, which is a mach number distribution diagram of the outlet of the inlet, it can be found that the outlet flow field of the inlet is a symmetric flow field, which is beneficial to organizing combustion.
And secondly, performing a numerical test on the self-starting capability of the air inlet by verifying the low-Mach-number starting capability of the air inlet and adopting a simulation method which is an accelerated starting mode, namely, researching a method for gradually increasing the incoming flow from the low Mach number. As shown in fig. 5(a), (b), and (c), which are graphs of mach numbers of the intake duct at mach numbers of 1.5, 1.8, and 1.9, respectively, it can be found that when the incoming flow mach number is ma1.5, there is a detached shock wave at the front end of the intake duct, the intake duct is in an un-started state, the incoming flow mach number is continuously increased, when the incoming flow mach number is ma1.8, a normal shock wave is pushed into the intake duct channel, and then the mach number is increased to 1.9, an oblique shock wave at the front end of the intake duct adheres to and is stable, and the intake duct realizes self-starting. Thus, the air inlet channel can realize low-Mach number starting.
Experiment three (verifying that the pneumatic profile can be automatically adjusted under different Mach numbers and the flow coefficient can be 1.0) to realize low-Mach-number starting is an important characteristic of the invention, and the invention has another important characteristic of being suitable for effective work under different working Mach numbers (namely, realizing the automatic adjustment of the pneumatic profile of the wide-range Mach-number working air inlet channel), as shown in the accompanying drawings 6(a) - (e), the aerodynamic profile flow diagram of the air inlet channel when the incoming flow Mach numbers are 1.9, 2.5, 3.5, 4.5 and 5 shows that with the increase of the incoming flow Mach number, the separation packet becomes larger, the aerodynamic throat of the air inlet channel is gradually reduced when the compression angle of the aerodynamic profile is increased, which just accords with the design criterion of the internal pressure type air inlet channel, and also achieves the purpose of realizing the profile adjustment of the air inlet channel under different working conditions.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that several deductions or substitutions can be made without departing from the spirit of the present invention, and all such deductions or substitutions should be considered as the protection scope of the present invention.
Claims (5)
1. A fixed geometry binary supersonic air inlet with a variable pneumatic compression profile comprises an upper wall surface, a lower wall surface and two side wall surfaces, wherein the upper wall surface and the lower wall surface are symmetrically arranged; the upper wall surface, the lower wall surface and the two side wall surfaces jointly enclose an inner channel and an expansion section extending backwards from the inner channel; the air conditioner is characterized in that an upper auxiliary air inlet channel which extends from front to back together with the inner channel is formed on the outer side of the upper wall surface, and a lower auxiliary air inlet channel which extends from front to back together with the inner channel is formed on the outer side of the lower wall surface; the rear part of the upper auxiliary air inlet channel and the rear part of the lower auxiliary air inlet channel are both provided with a flow discharge air slit communicated with the inner channel.
2. The fixed-geometry binary supersonic inlet with a variable aerodynamic compression profile as defined in claim 1, wherein said upper auxiliary inlet and said lower auxiliary inlet are symmetrically disposed.
3. The fixed geometry binary supersonic air inlet with a variable aerodynamic compression profile of claim 2, wherein said upper and lower wall surfaces each have only one compression angle at their forward most end, followed by no other compression angle.
4. The fixed geometry binary supersonic air intake duct having a variable aerodynamic compression profile of claim 3, wherein the compression angle of the foremost end of the upper and lower wall surfaces is both upper and lower side compression, and is arrow-shaped.
5. The fixed-geometry binary supersonic inlet with a variable aerodynamic compression profile of claim 4, wherein the fixed-geometry binary supersonic inlet is a monolithic symmetric structure.
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Citations (4)
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| CN101029597A (en) * | 2007-03-22 | 2007-09-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
| CN104890887A (en) * | 2015-04-20 | 2015-09-09 | 南京航空航天大学 | Supersonic-velocity hypersonic-velocity gas inlet duct adopting pneumatic unstart control method |
| CN107298180A (en) * | 2017-06-09 | 2017-10-27 | 南京航空航天大学 | A kind of aircraft and pneumatic adaptation design method for possessing one flowing control |
| CN107575309A (en) * | 2017-08-07 | 2018-01-12 | 南京航空航天大学 | A kind of high-performance dual rectangular channels loong shunt TBCC air intake ducts and design method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10233869B2 (en) * | 2015-08-27 | 2019-03-19 | Rolls Royce North American Technologies Inc. | System and method for creating a fluidic barrier from the leading edge of a fan blade |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101029597A (en) * | 2007-03-22 | 2007-09-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
| CN104890887A (en) * | 2015-04-20 | 2015-09-09 | 南京航空航天大学 | Supersonic-velocity hypersonic-velocity gas inlet duct adopting pneumatic unstart control method |
| CN107298180A (en) * | 2017-06-09 | 2017-10-27 | 南京航空航天大学 | A kind of aircraft and pneumatic adaptation design method for possessing one flowing control |
| CN107575309A (en) * | 2017-08-07 | 2018-01-12 | 南京航空航天大学 | A kind of high-performance dual rectangular channels loong shunt TBCC air intake ducts and design method |
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