CN113153531A - Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft - Google Patents
Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft Download PDFInfo
- Publication number
- CN113153531A CN113153531A CN202110588076.0A CN202110588076A CN113153531A CN 113153531 A CN113153531 A CN 113153531A CN 202110588076 A CN202110588076 A CN 202110588076A CN 113153531 A CN113153531 A CN 113153531A
- Authority
- CN
- China
- Prior art keywords
- adjusting plate
- adjusting
- rack
- variable
- overflow groove
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 46
- 230000001105 regulatory effect Effects 0.000 claims abstract description 21
- 230000008859 change Effects 0.000 claims abstract description 4
- 230000006835 compression Effects 0.000 claims description 20
- 238000007906 compression Methods 0.000 claims description 20
- 230000007704 transition Effects 0.000 claims description 20
- 239000003638 chemical reducing agent Substances 0.000 claims description 12
- 239000002243 precursor Substances 0.000 claims description 6
- 230000008901 benefit Effects 0.000 abstract description 7
- 238000002485 combustion reaction Methods 0.000 abstract description 4
- 238000000926 separation method Methods 0.000 description 8
- 230000006872 improvement Effects 0.000 description 7
- 230000033001 locomotion Effects 0.000 description 6
- 238000010521 absorption reaction Methods 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 5
- 238000013519 translation Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 238000013459 approach Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 108091053398 TRIM/RBCC family Proteins 0.000 description 1
- 102000011408 Tripartite Motif Proteins Human genes 0.000 description 1
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005574 cross-species transmission Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008571 general function Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Images
Classifications
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Transmission Devices (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a variable overflow groove adjusting mechanism, a scramjet engine and a hypersonic aircraft, which are suitable for an air inlet channel of a wide-speed-domain aircraft, wherein the variable overflow groove mechanism comprises an adjusting plate and an adjusting mechanism; the regulating plate is provided with a regulating plate bottom, a plurality of regulating plugs are arranged at the regulating plate bottom, and the regulating plugs are inserted into an overflow groove of the scramjet engine; the adjusting mechanism is connected with the adjusting plate and used for driving the adjusting plate to move relative to the overflow groove so as to change the size of the opening of the overflow groove. Compared with the mode of adopting a front body/upper air inlet channel surface variable structure and the traditional mode of adopting a fixed opening size overflow trough, the starting Mach number can be effectively reduced, the quality of air flow entering the combustion chamber can be adjusted, and the structure has the advantages of large adjusting range, simple structure, small mass, high engineering application realizability and convenience in implementation.
Description
Technical Field
The invention relates to the technical field of aircraft air inlet channel design, in particular to a variable overflow trough adjusting mechanism, a scramjet engine and a hypersonic aircraft.
Background
The main types of hypersonic aircrafts are reusable vehicles, hypersonic missiles and the like. At present, the hypersonic aircraft cannot directly take off from the ground only by means of the scramjet engine, and other power devices must be combined under low Mach number, so that combined power such as rocket-based combined cycle or turbine-based combined cycle is often adopted, the rocket engine or the turbine engine works at low speed, and the scramjet engine starts to work after the aircraft is accelerated to a certain speed. The starting Mach number of the air inlet channel not only influences the realization of combined power, but also determines the proportion of boosting power in the whole propulsion system under low Mach number, thereby influencing the cost of hypersonic flight. Therefore, the research on how to effectively reduce the starting Mach number of the hypersonic inlet channel has important practical significance.
Currently, the approach taken by the inlet to reduce the starting mach number is primarily a variable geometry approach or an increase in the spill over tank. The study of RBCC binary inlet channel variable geometry scheme by Liu Xiao Wei of the university of northwest industries describes a variable geometry structure which reduces the starting Mach number of an inlet by controlling the rotation of an inlet compression plate to discharge low-speed fluid of a boundary layer out of the inlet. The influence of the position of the overflow groove on the starting Mach number of the air inlet is researched by a paper 'the influence of the suction position on the starting performance of the hypersonic air inlet channel' published by the king satellite of the university of aerospace in Nanjing. In both the two modes, the starting Mach number of the air inlet channel is fixed in a certain state, so that the automatic adjustment cannot be carried out according to different requirements, and the absorption removing amount of the overflow trough cannot be controlled according to different boundary layer thicknesses in different flight states.
Therefore, there is a need for a novel mechanism with a variable overflow trough size, which not only has the general functions of absorbing and removing the boundary layer, reducing the shock wave/boundary layer interference, suppressing the development and separation of the boundary layer of the inlet channel, increasing the effective throat area, and enabling the inlet channel to start smoothly at a lower mach number, but also can enable the starting mach number of the inlet channel to be controlled as required, and control the overflow trough absorption amount according to the flight state.
Disclosure of Invention
The invention provides a variable overflow groove adjusting mechanism, a scramjet engine and a hypersonic aircraft. When the air inlet channel is not started under different flight Mach numbers, the flow of low-pressure air flow at the transition position of the throat channel and the compression surface is different, and the structure can control the suction flow, so that the starting Mach number of the air inlet channel is controlled within a certain range.
In order to achieve the above object, the present invention provides the following technical solutions.
A variable overflow groove adjusting mechanism comprises an adjusting plate and an adjusting mechanism;
the regulating plate is provided with a regulating plate bottom, a plurality of regulating plugs are arranged at the regulating plate bottom, and the regulating plugs are inserted into an overflow groove of the scramjet engine;
the adjusting mechanism is connected with the adjusting plate and used for driving the adjusting plate to move relative to the overflow groove so as to change the size of the opening of the overflow groove.
As a further improvement of the present invention, the adjusting mechanism includes a rack block, a driving unit, and a rack and pinion mechanism;
one end of the adjusting plate is provided with a driven gear, and the other end of the adjusting plate is provided with an adjusting plate rear rack;
the rack block is provided with a limiting rack, and the driven gear is meshed with the limiting rack;
the driving unit is provided with a driving gear meshed with the adjusting plate rear rack, and the driving unit drives the driving gear to rotate.
As a further improvement of the present invention, the adjusting mechanism includes a rack block, a driving unit, and a rack and pinion mechanism;
one end of the adjusting plate is provided with a limiting rack, and the other end of the adjusting plate is provided with an adjusting plate rear rack;
the rack block is provided with a driven gear, and the driven gear is meshed with the limiting rack;
the driving unit is provided with a driving gear meshed with the adjusting plate rear rack, and the driving unit drives the driving gear to rotate.
As a further improvement of the present invention, the driving unit includes a motor base, a stepping motor and a speed reducer, the stepping motor is mounted on the motor base, and the stepping motor drives the driving gear through the speed reducer.
As a further improvement of the present invention, the tuning plug is matched to the dimensions of the isopipe.
As a further improvement of the invention, the curved surface corresponding to the bottom of the adjusting plate is matched with the curved surface of the transition surface where the overflow groove is located; the rack block and the driving unit are both installed on the transition surface, and the adjusting plate is arranged between the rack block and the driving unit.
As a further improvement of the invention, the overflow groove is an inverted trapezoidal groove; the mounting surface of the limiting rack, the surfaces where the axes of the two driven gears are located, the AC surface of the adjusting plug, the BD surface of the overflow groove and the mounting surface of the adjusting plate rear rack are parallel to each other.
As a further improvement of the invention, in the air inlet channel with the variable overflow chute adjusting mechanism, at least two gear blocks, at least two adjusting plate rear racks and at least two driving gears meshed with the adjusting plate rear racks are arranged at symmetrical positions on two sides of the adjusting plate; each side of the driven gear is at least provided with two driven gears, and the two sides of each driven gear are also located at the symmetrical positions of the adjusting plates.
The scramjet engine comprises an air inlet, wherein the air inlet comprises a three-stage precursor compression surface, a throat surface, an engine base plate and an engine expansion section which are sequentially connected, a transition surface is formed between the three-stage precursor compression surface and the throat surface, and an overflow groove is formed in the transition surface; the transition surface is provided with the variable overflow groove adjusting mechanism.
A hypersonic aerocraft comprises an aerocraft fuselage and the scramjet engine.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a variable overflow trough mechanism suitable for an air inlet channel of a wide-speed-range aircraft. The size of the opening of the overflow groove can be changed through the adjusting plate, the thickness of the boundary layer at the joint of the air inlet compression surface and the throat of the hypersonic aircraft is controlled, the starting Mach number of the air inlet is adjusted, and the hypersonic aircraft has the advantages of improving the air flow quality of the air inlet under different Mach numbers, considering the pneumatic performance under different Mach numbers, obtaining higher engine performance, stable transition of different modes, lower quality punishment and the like. Compared with the mode of adopting a front body/upper air inlet channel surface variable structure and the traditional mode of adopting a fixed opening size overflow trough, the starting Mach number can be effectively reduced, the quality of air flow entering the combustion chamber can be adjusted, and the structure has the advantages of large adjusting range, simple structure, small mass, high engineering application realizability and convenience in implementation.
Furthermore, the front and the back of the upper air inlet are respectively connected with the front body of the aircraft and the throat of the air inlet, and the upper air inlet is a main bearing part of the adjusting mechanism. The adjusting plate is a key part of the structure, controls the up-and-down translation of the adjusting plate, and can conveniently adjust the size of the opening of the overflow groove, thereby controlling the suction flow. The motor is a power source of the structure, transmits force to the driving gear through the speed reducer, and drives the adjusting plate to move by means of gear and rack transmission.
The invention controls the thickness of the boundary layer at the connection part of the compression surface and the throat of the air inlet of the hypersonic aircraft, and realizes the adjustment of the starting Mach number of the air inlet and the control of the absorption removal amount of the overflow launder. Compared with the mode of adopting a variable structure to reduce starting Mach number, the structure has the advantages of larger adjusting range, simple structure, smaller mass and convenient realization.
Drawings
The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way. In addition, the shapes, the proportional sizes, and the like of the respective members in the drawings are merely schematic for facilitating the understanding of the present invention, and do not specifically limit the shapes, the proportional sizes, and the like of the respective members of the present invention. Those skilled in the art, having the benefit of the teachings of this invention, may choose from the various possible shapes and proportional sizes to implement the invention as a matter of case. In the drawings:
FIG. 1 is a diagram of the installation location of a scramjet engine in a typical hypersonic aircraft.
FIG. 2 is a sectional view of a typical hypersonic aircraft profile.
FIG. 3 is an isometric view of an intake duct self-priming feature.
FIG. 4 is a front, right, top, and bottom view of the self-starting structure of the air scoop; wherein (a) is a top view, (b) is a front view, (c) is a right view, and (d) is a bottom view.
FIG. 5 is an enlarged front view of the self-starting structure of the air inlet.
Fig. 6 is an enlarged view of the front of the adjustment plate.
Fig. 7 is a schematic view of the adjusting plate at the highest point.
FIG. 8 is a cross-sectional view of the isopipe with the regulating plate in the uppermost position.
The names of the components corresponding to the labels in the figure are as follows: 1. an aircraft fuselage; 2. a scramjet engine; 3. a first stage compression surface; 4. a second stage compression surface; 5. a third stage of compression surface; 6. a transition surface; 7. a laryngeal surface; 8. an engine bedplate; 9. an engine expansion section; 10. a rack block; 11. an adjusting plate; 12. adjusting the rear rack of the plate; 13. a gear key; 14. a rotating shaft; 15. a driving gear; 16. a speed reducer; 17. a stepping motor; 18. a limit rack; 19. a driven gear; 20. an overflow trough; 21. the bottom of the adjusting plate; 22. the plug is adjusted.
Detailed Description
In order to make those skilled in the art better understand the technical solution of the present invention, the technical solution in the embodiment of the present invention will be described below in detail and completely with reference to the drawings in the embodiment of the present invention, and it is obvious that the described embodiment is only a part of the embodiment of the present invention, and not a whole embodiment. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, shall fall within the scope of protection of the present invention.
It will be understood that when an element is referred to as being "disposed on" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only and do not denote a single embodiment.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
As shown in figures 1 and 2, the hypersonic aircraft is characterized in that a scramjet engine 2 is arranged on the belly of a fuselage 1 of the hypersonic aircraft, and the degree of integration between the engine structure and the fuselage 1 of the hypersonic aircraft is high.
The air inlet channel of the scramjet engine 2 mainly comprises four parts, namely a three-stage precursor compression surface (consisting of a first-stage compression surface 3, a second-stage compression surface 4 and a third-stage compression surface 5), a throat surface 7, an engine base plate 8 and an engine expansion section 9, wherein the three-stage precursor compression surface is simultaneously used as a part of an aircraft fuselage for bearing aerodynamic loads. In the flight process, a separation area appears at the transition position of the compression surface facing the throat section, and the lower the Mach number is, the larger the separation area is. When the separation zone is too large, the airflow may become blocked at the inlet and may not enter the combustion chamber, thereby causing the engine to fail. Therefore, the area of the throat section close to the separation area is provided with the opening, so that low-pressure airflow can be sucked, the area of the separation area is reduced, and the airflow can normally circulate.
As shown in fig. 3 to 6, in particular, the present invention provides a variable overflow chute adjusting mechanism, which comprises an adjusting plate 11 and an adjusting mechanism; the regulating plate 11 is provided with a regulating plate bottom 21 which is provided with a plurality of regulating plugs 22, and the regulating plugs 22 are inserted into an overflow groove 20 of the scramjet engine 2; the adjusting mechanism is connected with the adjusting plate 11 and is used for driving the adjusting plate 11 to move relative to the overflow groove 20 so as to change the size of the opening of the overflow groove 20. Specifically, the adjusting plate makes a linear movement, and the adjusting plug 22 and the overflow chute 20 realize relative sliding.
The adjusting mechanism comprises a rack block 10, a driving unit and a gear rack mechanism; one end of the adjusting plate 11 is provided with a driven gear 19, and the other end is provided with an adjusting plate rear rack 12; the rack block 10 is provided with a limiting rack 18 meshed with the driven gear 19, the driving unit is provided with a driving gear 15 meshed with the adjusting plate rear rack 12, and the driving unit drives the driving gear 15 to rotate.
The described embodiments are only some embodiments of the invention, not all embodiments. For the same purpose, a limit rack 18 may be provided at the front end of the adjusting plate 11, and a driven gear 19 may be provided on the rack block 10.
In a preferred embodiment, the driving unit comprises a motor base, a stepping motor 17 and a speed reducer 16, wherein the stepping motor 17 is mounted on the motor base, and the stepping motor 17 drives the driving gear through the speed reducer 16. An input shaft of the stepping motor 17 is inserted into an input hole of the worm gear reducer 16 and is fixed by a key against circumferential rotation, and the gear 15 is inserted into the rotating shaft 14 through a shaft hole in a fitting manner and is fixed by a key against circumferential rotation. The power provided by the stepping motor 17 drives the rotating shaft 14 to rotate after passing through the reducer 16, so as to drive the driving gear 15 to rotate, and the driving gear 15 is in meshing transmission with the adjusting plate rear rack 12, so that the gear rotating motion is converted into rack translation motion, and the adjusting plate 11 fixed with the rack is driven to perform fixed direction translation. The front end of the adjusting plate is provided with a driven gear 19 which can rotate freely up and down respectively, and the straight up and down movement of the adjusting plate 11 is ensured by meshing with a rack 18 on the rack block 10.
Preferably, the regulator plug 22 is dimensionally matched to the isopipe 20. The regulator plug 22 achieves a complete seal and seal with the overflow trough 20 as the regulator plate moves to the bottom, with a double mechanical fit without the need for additional sealing structures.
The curved surface corresponding to the bottom 21 of the adjusting plate is matched with the curved surface of the transition surface 6 where the overflow groove 20 is located; the rack block 10 and the drive unit are both mounted on the transition surface 6, and the adjusting plate 11 is arranged between the rack block 10 and the drive unit. The overflow groove 20 is an inverted trapezoidal groove; the mounting surface of the limiting rack 18, the surfaces where the axes of the two driven gears 19 are located, the AC surface of the adjusting plug 22, the BD surface of the overflow groove 20 and the mounting surface of the adjusting plate rear rack 12 are parallel to each other.
In order to ensure that the movement of the adjusting plate keeps stable linear movement, each air inlet channel with the variable overflow chute adjusting mechanism is provided with at least two gear rack blocks 10, an adjusting plate rear gear rack 12 and a driving gear 15 meshed with the adjusting plate rear gear rack 12, and the two driving gears are arranged at symmetrical positions on two sides of the adjusting plate 11; at least two driven gears 19 are arranged on each side, and the two sides are also at the symmetrical positions of the adjusting plate 11.
As shown in fig. 7, the mach number at the time of starting the operation of the scramjet engine is referred to as the starting mach number, and the lower the starting mach number is, the larger the operating range of the engine is. When the flying speed does not reach the starting Mach number, a larger separation area is generated at the transition position of the compression surface of the air inlet channel and the throat channel, so that the air flow cannot pass through. At the moment, the control system drives the adjusting plate to move upwards by starting the stepping motor, and discharges the low-speed boundary layer airflow gathered at the inlet of the throat so that the air inlet can be started. The thickness of the boundary layer is different and the size of the separation area is different under different speeds, so that the flow of the air flow to be sucked is different, the opening size of the overflow groove can be conveniently controlled by controlling the rotating speed and the number of turns of the stepping motor and controlling the adjusting plate to move up and down, the sucking flow is controlled, the starting Mach number is controlled within a certain range, and the engine can be started in a wider speed range.
As shown in fig. 8, the air flow enters the variable overflow trough from the DE of the transition region of the upper air inlet duct, flows out from the HI, and then flows out to the overflow trough opening of the aircraft sidewall through the flow passage of HJKL. Wherein the regulating plug 22 of the regulating plate 11 can be simplified to a quadrilateral ACFJ which is identical to the simplified rear quadrilateral BIED of the overflow launder of the upper inlet channel transition zone. And taking an auxiliary line FG at the point F as a vertical EI to the point G, and taking an auxiliary line FE, wherein the angle of the angle FEI is alpha. It should be noted that, since the minimum channel width of the overflow channel outlet airflow of the variable overflow mechanism is FG, it can be known from the pythagorean theorem that: FG is FE · sin α, where FE is CD, is the moving distance of the regulating plug 22, so it is not desirable to be too small because this would result in too small a real overflow tank opening and a reduction in the actual stripping effect.
The invention relates to a variable overflow trough mechanism suitable for an air inlet of a wide-speed-range aircraft, wherein the front part and the rear part of an upper air inlet are respectively connected with a front body of the aircraft and a throat of the air inlet and are main bearing parts of an adjusting mechanism. The adjusting plate is a key part of the structure, controls the up-and-down translation of the adjusting plate, and can conveniently adjust the size of the opening of the overflow groove, thereby controlling the suction flow. The motor is the power source of the structure, transmits force to the gear through the speed reducer, and drives the adjusting plate to move by means of gear and rack transmission.
The control of the mechanism of the invention requires the following preparation:
according to Computational Fluid Dynamics (CFD) analysis of the overall design stage of the aircraft, the thickness of the boundary layer of the aircraft under the conditions of different flight heights, flight Mach numbers and the like is determined, and therefore the size of the absorption removal amount and the adjustment height required by the adjustment plate are determined. Furthermore, the control system can determine the required air flow quality of the air inlet channel and the thickness of the boundary layer by interpolation according to the flying condition of the aircraft during flying, and controls and adjusts the height of the adjusting plate through the motor, the speed reducer and the gear rack structure, namely controls the size of the opening of the overflow chute.
The size of the opening of the overflow groove can be changed through the adjusting plate, the thickness of the boundary layer at the joint of the air inlet compression surface and the throat of the hypersonic aircraft is controlled, the starting Mach number of the air inlet is adjusted, and the hypersonic aircraft has the advantages of improving the air flow quality of the air inlet under different Mach numbers, considering the pneumatic performance under different Mach numbers, obtaining higher engine performance, stable transition of different modes, lower quality punishment and the like.
The invention controls the thickness of the boundary layer at the connection part of the compression surface and the throat of the air inlet of the hypersonic aircraft, and realizes the adjustment of the starting Mach number of the air inlet and the control of the absorption removal amount of the overflow launder. Compared with the mode of adopting a front body/upper air inlet channel surface variable structure and the traditional mode of adopting a fixed opening size overflow trough, the starting Mach number can be effectively reduced, the quality of air flow entering the combustion chamber can be adjusted, and the structure has the advantages of large adjusting range, simple structure, small mass, high engineering application realizability and convenience in implementation.
It should be noted that, in the description of the present invention, the terms "first", "second", and the like are used for descriptive purposes only and for distinguishing similar objects, and no precedence between the two is considered as indicating or implying relative importance. In addition, in the description of the present invention, "a plurality" means two or more unless otherwise specified.
It is to be understood that the above description is intended to be illustrative, and not restrictive. Many embodiments and many applications other than the examples provided would be apparent to those of skill in the art upon reading the above description. The scope of the present teachings should, therefore, be determined not with reference to the above description, but should instead be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. The disclosures of all articles and references, including patent applications and publications, are hereby incorporated by reference for all purposes. The omission in the foregoing claims of any aspect of subject matter that is disclosed herein is not intended to forego such subject matter, nor should the applicant consider that such subject matter is not considered part of the disclosed subject matter.
Claims (10)
1. The variable overflow groove adjusting mechanism is characterized by comprising an adjusting plate (11) and an adjusting mechanism;
the adjusting plate (11) is provided with an adjusting plate bottom (21), the adjusting plate bottom (21) is provided with a plurality of adjusting plugs (22), and the adjusting plugs (22) are inserted into an overflow groove (20) of the scramjet engine (2);
the adjusting mechanism is connected with the adjusting plate (11) and used for driving the adjusting plate (11) to move relative to the overflow groove (20) so as to change the size of the opening of the overflow groove (20).
2. The variable isopipe adjusting mechanism of claim 1, wherein the adjusting mechanism comprises a rack block (10), a drive unit, and a rack and pinion mechanism;
one end of the adjusting plate (11) is provided with a driven gear (19), and the other end is provided with an adjusting plate rear rack (12);
a limiting rack (18) is arranged on the rack block (10), and the driven gear (19) is meshed with the limiting rack (18);
the driving unit is provided with a driving gear (15) meshed with the adjusting plate rear rack (12), and the driving unit drives the driving gear (15) to rotate.
3. The variable isopipe adjusting mechanism of claim 1, wherein the adjusting mechanism comprises a rack block (10), a drive unit, and a rack and pinion mechanism;
one end of the adjusting plate (11) is provided with a limiting rack (18), and the other end of the adjusting plate is provided with an adjusting plate rear rack (12);
a driven gear (19) is arranged on the rack block (10), and the driven gear (19) is meshed with the limiting rack (18);
the driving unit is provided with a driving gear (15) meshed with the adjusting plate rear rack (12), and the driving unit drives the driving gear (15) to rotate.
4. The variable overflow chute adjusting mechanism as claimed in claim 1 or 2, wherein the driving unit comprises a motor base, a stepping motor (17) and a speed reducer (16), the stepping motor (17) is mounted on the motor base, and the stepping motor (17) drives the driving gear through the speed reducer (16).
5. A variable isopipe regulating mechanism as claimed in claim 1 or claim 2, wherein said regulating plug (22) matches the size of the isopipe (20).
6. The variable overflow chute adjusting mechanism as claimed in claim 1 or 2, wherein the curved surface corresponding to the bottom (21) of the adjusting plate is matched with the curved surface of the transition surface (6) where the overflow chute (20) is located; the rack block (10) and the driving unit are both installed on the transition surface (6), and the adjusting plate (11) is arranged between the rack block (10) and the driving unit.
7. A variable isopipe regulating mechanism as claimed in claim 1 or claim 2, wherein said isopipe (20) is an inverted trapezoidal groove; the mounting surface of the limiting rack (18), the surfaces where the axes of the two driven gears (19) are located, the AC surface of the adjusting plug (22), the BD surface of the overflow groove (20) and the mounting surface of the adjusting plate rear rack (12) are parallel to each other.
8. The variable overflow chute adjusting mechanism is characterized in that in an air inlet channel with the variable overflow chute adjusting mechanism, at least two of the rack block (10), the adjusting plate rear rack (12) and the driving gear (15) meshed with the adjusting plate rear rack (12) are arranged and are arranged at two symmetrical positions on two sides of the adjusting plate (11); at least two driven gears (19) are arranged on each side, and the two sides are also positioned at the symmetrical positions of the adjusting plate (11).
9. The scramjet engine is characterized by comprising an air inlet, wherein the air inlet comprises a three-stage precursor compression surface, a throat surface (7), an engine base plate (8) and an engine expansion section (9) which are sequentially connected, a transition surface (6) is formed between the three-stage precursor compression surface and the throat surface (7), and an overflow groove (20) is arranged on the transition surface (6); the transition surface (6) is provided with a variable overflow trough adjustment mechanism according to any one of claims 1 to 8.
10. Hypersonic aircraft, characterised in that it comprises an aircraft fuselage (1) and a scramjet engine (2) according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110588076.0A CN113153531B (en) | 2021-05-28 | 2021-05-28 | Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110588076.0A CN113153531B (en) | 2021-05-28 | 2021-05-28 | Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113153531A true CN113153531A (en) | 2021-07-23 |
| CN113153531B CN113153531B (en) | 2022-09-27 |
Family
ID=76877948
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110588076.0A Expired - Fee Related CN113153531B (en) | 2021-05-28 | 2021-05-28 | Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113153531B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB777570A (en) * | 1952-12-31 | 1957-06-26 | Rene Leduc | Improvements in thermopropulsive ducts especially for aircraft |
| FR1552118A (en) * | 1967-11-17 | 1969-01-03 | ||
| US20070136032A1 (en) * | 2005-07-22 | 2007-06-14 | Lockheed Martin Corporation | System, method, and apparatus for diverterless hypersonic inlet for integrated turbojet and ram-scramjet applications |
| CN104632411A (en) * | 2015-01-28 | 2015-05-20 | 南京航空航天大学 | Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner |
| CN104863715A (en) * | 2015-04-16 | 2015-08-26 | 南京航空航天大学 | Binary hypersonic-velocity variable-geometry air inlet way with rectangular inlet, design method thereof and working method thereof |
| CN105971733A (en) * | 2016-06-30 | 2016-09-28 | 西北工业大学 | Two-dimensional supersonic inlet of enclosed variable structure |
| CN107013368A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | Turbine base double combustion chamber's punching press combined cycle engine control method |
-
2021
- 2021-05-28 CN CN202110588076.0A patent/CN113153531B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB777570A (en) * | 1952-12-31 | 1957-06-26 | Rene Leduc | Improvements in thermopropulsive ducts especially for aircraft |
| FR1552118A (en) * | 1967-11-17 | 1969-01-03 | ||
| US20070136032A1 (en) * | 2005-07-22 | 2007-06-14 | Lockheed Martin Corporation | System, method, and apparatus for diverterless hypersonic inlet for integrated turbojet and ram-scramjet applications |
| CN104632411A (en) * | 2015-01-28 | 2015-05-20 | 南京航空航天大学 | Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner |
| CN104863715A (en) * | 2015-04-16 | 2015-08-26 | 南京航空航天大学 | Binary hypersonic-velocity variable-geometry air inlet way with rectangular inlet, design method thereof and working method thereof |
| CN105971733A (en) * | 2016-06-30 | 2016-09-28 | 西北工业大学 | Two-dimensional supersonic inlet of enclosed variable structure |
| CN107013368A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | Turbine base double combustion chamber's punching press combined cycle engine control method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113153531B (en) | 2022-09-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP0743247B1 (en) | Passive cooling device and method for cooling an auxiliary power unit on an airoplane | |
| US5125597A (en) | Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system | |
| US9644535B2 (en) | Passive boundary layer bleed system for nacelle inlet airflow control | |
| EP1344915B1 (en) | A variable position intake for an aircraft mounted gas turbine engine | |
| US8839805B2 (en) | Passive boundary layer bleed system for nacelle inlet airflow control | |
| EP2597037A2 (en) | An Aircraft | |
| CA2012248A1 (en) | Hybrid laminar flow nacelle | |
| CN105971733B (en) | A kind of closed structure changes Two Dimensional Supersonic air intake duct | |
| EP2939929B1 (en) | Multi-axis accessory gearboxes of mechanical drive systems and gas turbine engines including the same | |
| EP2871131B1 (en) | Variable geometry helicopter engine inlet | |
| EP2272758B1 (en) | Ram door assemblies | |
| EP0778199A2 (en) | Ram air drive laminar flow control system | |
| EP3219606A1 (en) | Cross flow fan with exit guide vanes | |
| CN113153531B (en) | Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aircraft | |
| EP2617965A2 (en) | Gas turbine engine with pylon mounted accessory drive | |
| US5531406A (en) | Flow-vectored trailing-edge for airfoils and jets | |
| US20160108811A1 (en) | Gas turbine engine nacelle | |
| EP2340992B1 (en) | Method for propeller blade root flow control by airflow through spinner | |
| EP2610462A2 (en) | Gas turbine engine with low stage count low pressure turbine | |
| CN112780413B (en) | Design method of TBCC air inlet adjusting mechanism based on curved surface shutter principle | |
| CN112623237B (en) | Design method of TBCC (TBCC) air inlet adjusting mechanism based on shape memory alloy | |
| CN112796888B (en) | Design method of TBCC air inlet adjusting mechanism based on shutter principle | |
| CN114000958B (en) | Design method of TBCC tail nozzle adjusting mechanism based on double-plectrum type sliding block principle | |
| CN217348240U (en) | Open slot adjustable fan wing and cross flow fan rotor wing device composed of same | |
| RU47982U1 (en) | GAS-TURBINE ENGINE WITH REGULATED TURBINE ROTOR SPEEDS |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220927 |