CN110630382A - Internal/external compression integrated adjustable variable-geometry air inlet and design method - Google Patents
Internal/external compression integrated adjustable variable-geometry air inlet and design method Download PDFInfo
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- CN110630382A CN110630382A CN201910921304.4A CN201910921304A CN110630382A CN 110630382 A CN110630382 A CN 110630382A CN 201910921304 A CN201910921304 A CN 201910921304A CN 110630382 A CN110630382 A CN 110630382A
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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 provides an internal/external compression integrated adjustable variable geometry air inlet, which is characterized in that a compression surface capable of rotating around a shaft is designed on the basis of a supersonic air inlet structure, the deflection position of the adjustable compression surface is adjusted according to flight conditions, the incoming flow Mach number range of the air inlet is widened, the aerodynamic performance of the air inlet is improved, and the simple realizability of a time-varying geometry mechanism in practical engineering application is considered. The invention also provides a design method of the air inlet.
Description
Technical Field
The invention belongs to the technical field of engines, and particularly relates to an ultrasonic speed-variable geometric air inlet and a design method thereof.
Background
The ramjet has a series of characteristics of simple structure, large thrust and the like, and is widely applied to the aspect of being used as a high-performance propelling device of a supersonic aircraft. The supersonic air inlet duct is one of the key pneumatic components of the ramjet, and the quality of the performance of the supersonic air inlet duct directly influences the comprehensive performance of a propulsion system and even the whole aircraft. For supersonic air inlet channels working in a wide mach number range, the air inlet channels are required to have self-starting capability under a low flight mach number and also required to have high flow coefficient, total pressure recovery and back pressure resistance capability in the wide range, and conventional fixed geometry air inlet channels cannot meet the requirement of further improvement of engine performance under the wide mach number range, so that the variable geometry air inlet channels with actively adjusted profiles are necessary to be designed for the air inlet channels in the wide speed range.
Aiming at the contradiction between the self-starting capability under low Mach number and the performance of the air inlet channel under high Mach number in the wide-speed-range work of the ramjet, French researchers change the flow capture area and the internal contraction ratio of the air inlet channel by actively rotating the variable geometry design of the lip cover so as to realize the purposes of adjusting the flow coefficient and improving the compression efficiency under high Mach number; sanders realizes the design of a variable geometry air inlet in a wide speed range of Mach number 0-7 by linkage adjustment between a compression surface and a high/low speed channel lip cover. However, the rotation of the lip shroud can cause the external resistance of the aircraft to be obviously increased, and the problem of aircraft trim caused by the external resistance is difficult to effectively solve, and the variable geometry air inlet in the Sanders design achieves better performance in theory, but the complex control mechanism of the variable geometry air inlet makes the profile coordination and continuity difficult to guarantee under actual operation.
The method that lip rotation expansion and contraction and compression surface rotation are achieved through the adjusting mechanism to optimize the variable-geometry profile can obviously improve the pneumatic performance of the air inlet in a wide Mach number range, but if the mechanical adjusting mechanism is too complex in control means and too many movable parts are adopted, the feasibility of practical application of the mechanical adjusting mechanism is reduced.
Therefore, a new technical solution is needed to solve the above problems.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides an internal/external compression integrated adjustable variable geometry air inlet, which can widen the incoming flow Mach number range of the air inlet, improve the aerodynamic performance of the air inlet and simultaneously give consideration to the simple realizability of a time-varying geometry mechanism in practical engineering application.
The technical scheme is as follows: in order to achieve the purpose, the invention can adopt the following technical scheme:
an internal/external compression integrated adjustable variable geometry air inlet comprises a first-stage compression surface, a lip cover and side plates positioned on the outer sides of the first-stage compression surface and the lip cover; the adjustable compression surface comprises a base, an adjustable compression surface main body and an expansion section, wherein the adjustable compression surface main body is positioned between the base and the lip cover; an inner channel of the air inlet channel is formed between the adjustable compression surface main body and the lip cover; the first-stage compression surface is positioned at the front end of the base, and the front end of the adjustable compression surface main body is hinged with the base at the rear end of the first-stage compression surface through a rotating shaft; through the rotating shaft, the rear end of the adjustable compression surface main body moves towards the lip cover side or the base side; when the adjustable compression surface main body moves towards the base side, a rear discharge groove is formed by the interval between the rear end of the adjustable compression surface main body and the expansion section, and when the adjustable compression surface main body moves towards the lip cover side, the adjustable compression surface main body is connected with the expansion section, and the rear discharge groove is closed.
Furthermore, the main body of the adjustable compression surface comprises a main body front section, a main body rear section and a connecting section for connecting the main body front section and the main body rear section; the surface of the front section of the main body is a second-stage compression surface, a groove is formed among the front section of the main body, the rear section of the main body and the connecting section, the front wall surface and the rear wall surface of the groove are both cambered surfaces which are convex backwards, the bottom of the groove is the connecting section, and the top of the groove penetrates through and is communicated with a channel in the air inlet channel; and the side plate is provided with a drainage cavity communicated with the outside, and the drainage cavity is always communicated with the groove.
The plane four-bar mechanism comprises two rocking bars, a horizontal actuating rod which bears the rocking bars and extends from front to back, and a driving device which drives the horizontal actuating rod to move back and forth; the driving device is fixed on the base, and the base is simultaneously provided with a sliding rail for the horizontal actuating rod to move back and forth; one ends of the two rocking bars are hinged below the adjustable compression surface main body, and the other ends of the two rocking bars are hinged with the horizontal actuating rod.
Has the advantages that: the variable geometry air inlet channel remarkably improves the problem that the compression amount of a fixed geometry air inlet channel is insufficient under high Mach number, and reduces the Mach number of a throat, thereby reducing the total pressure loss when air flow passes through a tail shock wave.
The invention also provides a design method of the air inlet channel, which can adopt the following technical scheme:
a design method of an air inlet comprises the following steps:
(1) the air inlet channel reference scheme comprises two stages of outer compression surfaces, namely a first stage compression surface and a second stage compression surface, when the Mach number Ma is 2.0, the bottom end of an adjustable compression surface main body of the air inlet channel abuts against a bottommost base, at the moment, the opening of a rear discharge groove is the largest, and the outer compression strength and the inner contraction ratio of the air inlet channel are both the smallest;
(2) under the condition that the Mach number Ma of a design point is 3.0, the main body of the adjustable compression surface of the air inlet channel rotates anticlockwise around the rotation center, and the intersection of two external compression oblique shock waves of the two-stage external compression surface and a lip mouth is ensured under the design state;
(3) in order to ensure the compression efficiency of the air inlet channel under high Mach number, when the Mach number Ma is 4.0, the adjustable compression surface main body of the air inlet channel further rotates anticlockwise to a position where a rear discharge chute is completely closed, and the internal contraction ratio and the external compression strength reach the maximum;
(4) the utility model discloses a lateral plate, the lateral plate is equipped with the adjustable compression face main part, set up preceding discharge chamber on the lateral plate, discharge passage before forming, be equipped with the recess in the adjustable compression face main part, because the adjustable compression face main part is rotatory around the axis of rotation of first order and second level compression wedge surface intersection department, for guaranteeing that the actual discharge area of discharge passage is not influenced by the compression face main part is rotatory, the recess all adopts the circular arc curve transition in both sides about the lateral plate discharge chamber, and regard as the last profile in discharge chamber before the lateral plate with projection shape on the lateral plate of adjustable compression face main part recess top when mach number Ma 2.0, regard as the lower profile in discharge chamber before the lateral plate with projection shape of adjustable compression face main part recess bottom under the design status on the lateral plate.
Drawings
Fig. 1 is an isometric view of a wide-speed-range variable-geometry air inlet channel provided by the invention.
FIG. 2 is a schematic view of the main body of the adjustable compression surface in the variable geometry inlet of the present invention.
FIG. 3 is a schematic view of a variable geometry inlet center shroud according to the present invention.
FIG. 4 is a schematic view of a planar four bar linkage cooperating with a base and an adjustable compression surface body.
FIG. 5 is a graph comparing constant/variable geometry inlet performance curves provided by the present invention.
Detailed Description
The detailed description of the embodiments of the present invention is provided in conjunction with the accompanying drawings.
Referring to fig. 1 and 2, the present invention provides an internal/external compression integrated adjustable variable geometry air intake duct, which includes a first stage compression surface 3, a lip cover 2, a side plate 7 located outside the first stage compression surface 3 and the lip cover 2, a base 6, an adjustable compression surface main body 1 located between the base 6 and the lip cover 2, and an expansion section 16 located at the rear end of the adjustable compression surface main body 1. An air inlet channel is formed between the adjustable compression surface main body 1 and the lip cover 2. The first stage compression face 3 is located at the front end of the base 6. The front end of the adjustable compression surface main body 1 is hinged with a base 6 at the rear end of the first-stage compression surface 3 through a rotating shaft 5. In the present embodiment, the extending direction of the rotating shaft 5 is perpendicular to the side plate 7. The rear end of the adjustable compression surface main body 1 is moved to the lip cover 2 side or the base 6 side by the rotation shaft 5. When the adjustable compression surface main body 1 moves towards the base 6 side, the interval between the rear end of the adjustable compression surface main body 1 and the expansion section 16 forms a rear drainage groove 9. When the adjustable compression surface main body 1 moves towards the lip cover 2 side, the adjustable compression surface main body 1 is connected with the expansion section 16, and the rear drainage groove 9 is closed. The rear chute 9 is positioned behind the throat of the inner channel of the air inlet channel. And the size of the discharge flow of the rear discharge groove 9 is changed because the adjustable compression surface main body 1 rotates around the rotating shaft 5 according to different flight conditions. In order to avoid the body-shedding shock wave generated at the front end side plate 7 of the first-stage compression wedge surface 3 and influence the pneumatic performance of the air inlet channel, chamfering processing is carried out on the outer side end surface of the side plate 7 which does not influence the air flow of the inner channel. And the rear end of the base 6 is provided with a rear discharge outlet 10 communicated with the outside for discharging the airflow flowing out through the rear discharge groove 9.
As shown in fig. 2 and 3, the adjustable compression surface main body 1 includes a main body front section 12, a main body rear section 13, and a connecting section 14 connecting the main body front section 12 and the main body rear section 13. The surface of the front body section 12 is a second stage compression surface 4. A groove 8 is formed among the front main body section 12, the rear main body section 13 and the connecting section 14, and the groove 8 is positioned in the front of the throat of the air inlet channel. The preceding wall and the back wall of this recess 8 are the cambered surface of backward protrusion, and the bottom of recess 8 is the linkage segment, and the top of recess 8 runs through and communicates with the interior passageway of intake duct. And a drainage cavity 15 communicated with the outside is arranged on the side plate 7, and the drainage cavity 15 is always communicated with the groove 8. Because the adjustable compression surface main body 1 rotates around the rotating shaft 5 by a certain angle according to the Mach number of the incoming flow, in order to ensure that the actual discharge area of the discharge channel is not influenced by the rotation of the compression surface main body, the left end surface and the right end surface of the groove both need to adopt circular arc curve transition, and the intersection point of the rotating shaft 5 and the outer side of the adjustable compression surface main body 1 is the circular arc circle center; because the existence of the groove 8 can weaken the anti-deformation capability of the material of the whole main body 1 with the adjustable compression surface, for this purpose, a reinforcing support plate 14 with a certain thickness is required to be reserved between the front section 12 of the main body and the rear section 13 of the main body according to the rigidity performance of the material selected according to the specific experiment, the upper end surface of the reinforcing support plate 14 is the bottom end surface of the groove 8, and the section of the groove 8 dug out between the front section 12 of the main body and the rear section 13 of the main body is called as the top end of the groove. For the side plate drainage cavity 15, the left end and the right end of the side plate drainage cavity are in arc transition, and the radii of the arcs at the left end and the right end correspond to the grooves 8 one by one; for the positions of the upper end and the lower end of the bleed cavity 15, when the mach number Ma is 2.0, the projection of the upper end surface of the groove 8 on the side plate 7 corresponds to the upper end of the side plate bleed cavity 15, and the projection of the lower end surface of the groove in a mach number state on the side plate 7 corresponds to the lower end of the side plate bleed cavity 15. In order to enable the adjustable compression surface body 1 to rotate about the axis of rotation 5, a planar four-bar linkage is provided. As shown in fig. 1 and 4, the planar four-bar linkage includes two rocking bars 17, a horizontal actuating rod 18 which carries the rocking bars 17 and extends from front to back, and a driving device 19 (e.g., a motor) which drives the horizontal actuating rod 18 to move back and forth. The drive device 19 is fixed to the base 6. The base 6 is also provided with a slide rail 20 for the horizontal actuating rod 18 to move back and forth. One ends of the two rocking bars 17 are hinged below the adjustable compression surface main body 1, and the other ends of the two rocking bars 17 are hinged with the horizontal actuating rod 18. By moving the horizontal actuating rod 18 back and forth, the rocker 17 can be driven to rotate relative to the horizontal actuating rod 18, so that the adjustable compression surface main body 1 rotates around the rotating shaft 5.
Fig. 5 is a graph showing a comparison between the pressure ratio and total pressure recovery coefficient curve of the integrated adjustable variable geometry inlet provided by the present invention and the fixed geometry inlet in the prior art with better overall performance under the critical back pressure condition. It can be seen that the constant/variable geometry air inlet has equivalent performance under low Mach number, and the advantage of variable geometry performance gradually shows out along with the increase of the Mach number of the incoming flow. When Ma ∞ ═ 4.0, the critical pressure ratio of the variable geometry air inlet is improved by 20.2% and the total pressure recovery coefficient is improved by 22.9% compared with the fixed geometry air inlet. To sum up, this become geometry intake duct is showing and is improving the problem that the volume of compression is not enough under high mach number for fixed geometry intake duct, has reduced throat mach number to total pressure loss when the air current has reduced the end laser.
The above embodiment is an illustration of a general technical solution of a supersonic velocity wide-speed-range variable geometry air inlet proposed by the present invention, and the following adopts the above design method to explain in detail the design steps of a preferred embodiment of the present invention:
(1) designs a two-stage compression and Mach number MadAnd 3, the speed range Ma is 2-4. The wedge angle of the first-stage compression surface is 8 degrees, the wedge angle of the second-stage compression surface is 9 degrees in the design state, the throat height is 51.14mm, and the throat internal contraction ratio ICR is 1.5.
(2) The expansion ratio of the whole expansion section is 1.4 by adopting a change rule of firstly gradual and then quick according to a TBCC turbine channel expansion section design method (reference document: Zhang Huajun, Liuxing, Guo Wei, et al. And a point is taken in the expansion section of the inner channel passing through the throat, so that the distance from the standing position of the throat to the point accounts for 1/3 of the whole expansion section, and the rest 2/3 expansion sections are integrally moved upwards by 5mm along the transverse direction to ensure that a rear leakage channel exists between the integral rear edge of the adjustable compression surface and the rest expansion sections, thereby improving the pneumatic performance.
(3) In order to ensure that the actual discharge area of the discharge channel is not influenced by the rotation of the compression surface main body, the left end surface and the right end surface of the groove are in arc curve transition, the intersection point of the rotating shaft 5 and the outer side of the adjustable compression surface main body 1 is an arc circle center, the arc radius of the right end surface of the groove is 280mm, the arc radius of the left end surface of the groove is 306mm, and the thickness of the reinforcing support plate is 8mm in order to ensure the rigidity of the adjustable compression surface main body after slotting.
(4) The distance from the horizontal end face of the trapezoid base to the ground is 15.137mm obtained by the conversion relation that the wedge face at the front end of the trapezoid base is the first-stage compression face, in order to guarantee the flow capturing and self-starting capacity of the air inlet when the incoming flow Mach number Ma is 2.0, the adjustable compression face main body is abutted against the horizontal base, the rear discharge chute reaches the maximum opening, and the external compression strength and the internal compression ratio of the air inlet are both minimum. At this time, the second-stage compression surface wedge angle was 4 °, the throat height was 86.3mm, and the throat internal contraction ratio was 1.09.
(5) And (4) obtaining the position of the side plate drainage cavity according to the corresponding relation between each end surface of the grooves and the side plate drainage cavity in the step (3) and (4) Ma being 2.0 and Ma being 3.0.
(6) In order to ensure the compression efficiency of the air inlet channel when Ma is 4.0, the adjustable compression surface main body rotates anticlockwise around the rotating shaft to a position enabling the rear discharge channel to be completely closed, at the moment, the wedge angle of the second-stage compression surface is 10 degrees, the height of the throat is 43.695mm, the inner contraction ratio of the throat is ICR 1.68, and the inner contraction ratio and the outer compression strength reach the maximum.
Various other modifications and changes may be made by those skilled in the art based on the above-described technical solutions and concepts, and all such modifications and changes should fall within the scope of the claims of the present invention.
Claims (6)
1. An internal/external compression integrated adjustable variable geometry air inlet comprises a first-stage compression surface, a lip cover and side plates positioned on the outer sides of the first-stage compression surface and the lip cover; the lip mask is characterized by further comprising a base, an adjustable compression surface main body and an expansion section, wherein the adjustable compression surface main body is positioned between the base and the lip mask; an inner channel of the air inlet channel is formed between the adjustable compression surface main body and the lip cover; the first-stage compression surface is positioned at the front end of the base, and the front end of the adjustable compression surface main body is hinged with the base at the rear end of the first-stage compression surface through a rotating shaft; through the rotating shaft, the rear end of the adjustable compression surface main body moves towards the lip cover side or the base side; when the adjustable compression surface main body moves towards the base side, a rear discharge groove is formed by the interval between the rear end of the adjustable compression surface main body and the expansion section, and when the adjustable compression surface main body moves towards the lip cover side, the adjustable compression surface main body is connected with the expansion section, and the rear discharge groove is closed.
2. The air scoop according to claim 1, wherein: the main body of the adjustable compression surface comprises a main body front section, a main body rear section and a connecting section for connecting the main body front section and the main body rear section; the surface of the front section of the main body is a second-stage compression surface, a groove is formed among the front section of the main body, the rear section of the main body and the connecting section, the front wall surface and the rear wall surface of the groove are both cambered surfaces which are convex backwards, the bottom of the groove is the connecting section, and the top of the groove penetrates through and is communicated with a channel in the air inlet channel; and the side plate is provided with a drainage cavity communicated with the outside, and the drainage cavity is always communicated with the groove.
3. The intake duct of claim 1 or 2, wherein: the plane four-bar linkage mechanism comprises two rocking bars, a horizontal actuating rod which bears the rocking bars and extends from front to back, and a driving device which drives the horizontal actuating rod to move back and forth; the driving device is fixed on the base, and the base is simultaneously provided with a sliding rail for the horizontal actuating rod to move back and forth; one ends of the two rocking bars are hinged below the adjustable compression surface main body, and the other ends of the two rocking bars are hinged with the horizontal actuating rod.
4. The intake duct of claim 3, wherein: when the incoming flow Mach number is 2.0, the opening of the rear drainage groove is the largest; when the incoming flow Mach number is 4.0, the rear drainage groove is completely closed.
5. A method for designing an intake duct according to any one of claims 1 to 4, comprising the steps of:
(1) the air inlet channel reference scheme comprises two stages of outer compression surfaces, namely a first stage compression surface and a second stage compression surface, when the Mach number Ma is 2.0, the bottom end of an adjustable compression surface main body of the air inlet channel abuts against a bottommost base, at the moment, the opening of a rear discharge groove is the largest, and the outer compression strength and the inner contraction ratio of the air inlet channel are both the smallest;
(2) under the condition that the Mach number Ma of a design point is 3.0, the main body of the adjustable compression surface of the air inlet channel rotates anticlockwise around the rotation center, and the intersection of two external compression oblique shock waves of the two-stage external compression surface and a lip mouth is ensured under the design state;
(3) in order to guarantee the compression efficiency of the air inlet channel under high Mach number, when Mach number Ma is 4.0, the adjustable compression surface main body of the air inlet channel further rotates anticlockwise to the position where the rear discharge chute is completely closed, and the inner contraction ratio and the outer compression strength reach the maximum.
6. The design method as claimed in claim 5, wherein the side plate is provided with a front discharge cavity to form a front discharge channel, the adjustable compression surface body is provided with a groove, the adjustable compression surface body rotates around a rotation axis at the intersection of the first stage compression wedge surface and the second stage compression wedge surface, in order to ensure that the actual discharge area of the discharge channel is not affected by the rotation of the compression surface body, the left side and the right side of the groove and the side plate discharge cavity both adopt circular arc curve transition, the projection shape of the top end of the groove of the adjustable compression surface body on the side plate when Mach number Ma is 2.0 is used as the upper profile of the front discharge cavity of the side plate, and the projection shape of the bottom end of the groove of the adjustable compression surface body on the side plate in the design state is used as the lower profile of the front discharge cavity of the side plate.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112591134A (en) * | 2020-12-24 | 2021-04-02 | 中国航空工业集团公司西安飞机设计研究所 | Design method for section of air inlet of nacelle |
| CN113076610A (en) * | 2021-04-07 | 2021-07-06 | 南京航空航天大学 | Design method of binary adjustable air inlet channel |
| CN113153530A (en) * | 2021-05-28 | 2021-07-23 | 西北工业大学 | Hypersonic variable structure air inlet mechanism and wide-area combined power aircraft |
| CN113153529A (en) * | 2021-04-21 | 2021-07-23 | 厦门大学 | Wide-speed-range air inlet channel design method based on double-incidence bending shock wave |
| CN113915004A (en) * | 2021-10-29 | 2022-01-11 | 南京航空航天大学 | TBCC becomes that geometric inlet channel gets rid of boundary layer and compromise curb plate chute of startability |
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| CN110043367A (en) * | 2019-04-22 | 2019-07-23 | 南京航空航天大学 | A kind of super/hypersonic inlet of side plate openings |
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| US3011307A (en) * | 1955-12-15 | 1961-12-05 | Gen Electric | Variable throat supersonic diffuser |
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| CN113153529A (en) * | 2021-04-21 | 2021-07-23 | 厦门大学 | Wide-speed-range air inlet channel design method based on double-incidence bending shock wave |
| CN113153530A (en) * | 2021-05-28 | 2021-07-23 | 西北工业大学 | Hypersonic variable structure air inlet mechanism and wide-area combined power aircraft |
| CN113915004A (en) * | 2021-10-29 | 2022-01-11 | 南京航空航天大学 | TBCC becomes that geometric inlet channel gets rid of boundary layer and compromise curb plate chute of startability |
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|---|---|
| CN110630382B (en) | 2020-09-25 |
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