CN112392600B - Axisymmetric adjustable intake passage center cone boundary layer sucking structure - Google Patents
Axisymmetric adjustable intake passage center cone boundary layer sucking structure Download PDFInfo
- Publication number
- CN112392600B CN112392600B CN202011285444.6A CN202011285444A CN112392600B CN 112392600 B CN112392600 B CN 112392600B CN 202011285444 A CN202011285444 A CN 202011285444A CN 112392600 B CN112392600 B CN 112392600B
- Authority
- CN
- China
- Prior art keywords
- cavity
- cone
- central
- rod
- suction
- 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.)
- Active
Links
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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of aircrafts, and particularly relates to an axisymmetric suction structure for a central cone boundary layer of an adjustable air inlet channel. In the structure, the center cone is arranged on the center cone rod and can slide back and forth along the axial direction; the central cone rod is fixed on the shell through a hollow support plate; the whole air inlet channel is divided into a main channel, a support plate cavity, a central cone rod cavity, a suction cavity and an actuating mechanism cavity; in the working process, after the incoming air enters the air inlet channel, the boundary layer sequentially passes through the boundary layer suction hole, the suction cavity, the guide hole, the central cone rod cavity and the support plate cavity, and finally is discharged into the atmosphere at the outlet. The invention solves the difficulty of leading out the boundary layer gas at the central cone of the axisymmetric adjustable air inlet channel, and the design of the sucking cavity can naturally discharge the high-temperature air entering from the gap between the tail part of the central cone and the central cone rod to the atmosphere, does not need to design a special sealing structure or process by adopting a close fit process, and greatly reduces the processing precision and cost.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to an axisymmetric suction structure for a central cone boundary layer of an adjustable air inlet channel.
Background
The air inlet duct plays roles in capturing, compressing and rectifying incoming air, and is one of key components of the air suction type engine. The flight package line of the aerospace vehicle is extremely wide, so that the advantages of various propulsion systems are integrated, and a combined power engine is often needed. Under different flight Mach numbers, the requirement difference of the combined engine on the compression amount of the air inlet channel is extremely large: the internal shrinkage ratio of the air inlet channel designed according to the high Mach number is large, and the problem of no starting is easy to occur under the low Mach number; the total shrinkage of the air inlet channel designed according to the low Mach number is smaller, the critical total pressure recovery coefficient under the high Mach number is extremely low, and the working requirement of the combined engine is difficult to meet, so that the geometric adjustable design is often required.
As shown in fig. 1, the axisymmetric adjustable intake passage is a typical adjustable intake passage, and the capturing area and the throat area are changed by the forward and backward translation of the center cone, so that the wide-range adjustment of the total contraction ratio is realized. In the figures 101, 102 respectively show two positions of the front-back translation of the central cone.
Fig. 2 shows a typical flow field distribution for this type of inlet compression section: the external compression amount of the air inlet is limited, cone tip shock waves 202 emitted by the front tip of the center cone 201 are weaker, and lip shock waves 204 emitted by the front edge of the lip plate 203 are stronger; the development of the center cone boundary layer 206 is more complete, and the lip shock wave 204 easily induces the boundary layer separation 205 at the shoulder of the air inlet, which easily causes the bad conditions of non-starting or unstable flow field of the air inlet.
In order to eliminate the wall separation induced by the lip shock, it is a common means to suck off the boundary layer. Because the central cone where the boundary layer is located is surrounded by the main flow channel, a special suction channel can only be designed to discharge suction air flow into the atmosphere through the cavity inside the central cone support plate. For axisymmetric adjustable air inlet channels, if a special air suction pipeline design is adopted, a high-elasticity heat-resistant material is required to be adopted so as to adapt to the geometric length change caused by the forward and backward movement of the central cone.
In addition, the total incoming air temperature increases rapidly with increasing flight Mach number, and the adjustable intake air passage requires measures to isolate the incoming air to protect the internal actuation mechanism.
The wide-area axisymmetric adjustable air inlet channel which is successfully applied abroad is few, and boundary layer suction measures are also adopted at the shoulder part of the central cone, but the internal structure of the wide-area axisymmetric adjustable air inlet channel is not published, and only the sucked boundary layer air flow can be discharged into the atmosphere through the cavity in the central cone support plate.
With reference to fig. 3, the structural scheme of using the air guide pipeline to guide the central cone attachment surface layer to the central cone support plate cavity is only applicable to axisymmetric air inlets with fixed molded surfaces. If the adjustable air inlet channel is used, the pipeline is required to be made of high-elasticity high-temperature-resistant materials, the implementation difficulty is high, and the movement distance is limited by the elasticity of the materials.
Disclosure of Invention
First, the technical problem to be solved
The invention aims to solve the technical problems that: how to provide an axisymmetric adjustable air inlet channel center cone boundary layer and inhale and remove structural scheme, after center cone position changes, all can be smooth and easy with the leading-in atmosphere of center cone boundary layer air current of inhaling that removes, have advantages such as simple structure, low cost.
(II) technical scheme
In order to solve the technical problems, the invention provides an axisymmetric adjustable air inlet channel center cone boundary layer sucking structure, the axisymmetric adjustable air inlet channel main body structure comprises: a center cone 1, a center cone rod 3 and a shell 5;
the center cone 1 is arranged on the center cone rod 3 and can slide back and forth along the axial direction; the central cone rod 3 is fixed on the shell 5 through a plurality of hollow support plates 6; the whole air inlet channel is divided into a plurality of spaces of the main channel 8, the support plate cavity 9, the central cone rod cavity 10, the suction cavity 11 and the actuating mechanism cavity 13 by the structure;
wherein the main runner 8 is arranged between the central cone 1, the central cone rod 3 and the shell 5;
the support plate cavity 9 is formed by the plurality of hollow support plates 6 and the outer surface of the central cone rod 3; the support plate cavity 9 is provided with an outlet 7 which is communicated with the atmosphere; the support plate cavity 9 is communicated with the central cone rod cavity 10 through a hollow opening on the support plate 6;
the central cone rod cavity 10 is formed by the inner wall of the central cone rod 3, and the central cone rod cavity 10 is communicated with the suction cavity 11 through a diversion hole 12 formed in the head of the central cone rod 3;
the suction cavity 11 is formed by a central cone 1 and a central cone rod 3, and the suction cavity 11 is communicated with the main runner 8 through an auxiliary surface layer suction hole 4 arranged on the central cone 1;
the inside of the head of the center cone 1 forms the actuating mechanism cavity 13;
in the working process, after the incoming air enters the air inlet channel, the surface layer on the outer surface of the central cone 1 sequentially passes through the surface layer suction hole 4, the suction cavity 11, the flow guide hole 12, the central cone rod cavity 10 and the support plate cavity 9, and finally is discharged into the atmosphere at the outlet 7 of the support plate cavity 9.
Wherein the center cone 1 is arranged on a center cone rod 3 by a sliding bearing 2.
Wherein, the center cone 1 is a thin-wall structure center cone.
Wherein the central taper rod 3 is a central taper rod with a thin-wall structure.
When the center cone 1 slides back and forth along the center cone rod 3, the suction cavity 11 is always communicated with the center cone rod cavity 10 through the guide hole 12, so that the back and forth movement of the center cone 1 does not affect the connectivity of the suction channel.
Wherein, the center cone 1 and the center cone rod 3 are in a coaxial structure.
Wherein, a certain clearance channel 14 is allowed to exist between the tail part of the center cone 1 and the center cone rod 3; because of the higher pressure downstream of the inlet primary flow passage 8, air in the primary flow passage 8 will also enter the suction chamber 11 via the clearance passage 14 and be discharged into the atmosphere together with the boundary layer air flow entering from the boundary layer suction hole 4.
Wherein, there is not clearance between central awl 1 afterbody and the central awl pole 3.
(III) beneficial effects
Compared with the prior art, the invention has the following distinguishing technical characteristics:
(1) The invention discloses a central cone surface layer sucking structure, which consists of a thin-wall structure central cone 1 with a surface layer sucking hole 4, a thin-wall structure central cone rod 3 with a guide hole 12 at the head, a hollow support plate structure 6 and other parts, and a sucking cavity 11, a central cone cavity 10, a support plate cavity 9 and other spaces which are formed by the structures;
(2) The central cone 1 and the central cone rod 3 are of coaxial axisymmetric structures, and the central cone can slide back and forth along the central cone rod, so that the tail clearance between the central cone and the central cone rod is not restricted or specially designed;
(3) In the front-back sliding process of the center cone, the suction cavity 11 and the center cone rod cavity 10 are always communicated through the diversion hole 12 at the front part of the center cone rod 3;
(4) The invention does not restrict the cross-section shapes of the suction hole 4, the diversion hole 12 and the support plate cavity 9, and does not restrict the shapes of the suction cavity 11 and the central taper rod cavity 10.
Accordingly, the invention has the following beneficial effects:
(1) The invention provides a simple and effective central cone boundary layer sucking and removing structure scheme, solves the difficulty of guiding out boundary layer gas at the central cone of an axisymmetric adjustable air inlet channel, and has more reliable structure by only using common metal materials for conventional processing compared with the solution of an elastic air guide pipeline;
(2) The design of the suction cavity can naturally discharge high-temperature air entering from the gap between the tail part of the center cone and the center cone rod to the atmosphere, a special sealing structure is not required to be designed or a tight fit process is adopted for processing, and the processing precision and cost are greatly reduced;
(3) The cavity of the boundary layer absorbing structure is naturally isolated from the cavity of the actuating mechanism, so that the influence and damage of high-temperature air on the actuating mechanism are greatly reduced.
Drawings
Fig. 1 to 3 are prior art schematic diagrams.
Fig. 4 is a schematic diagram of the technical scheme of the present invention.
Detailed Description
For the purposes of clarity, content, and advantages of the present invention, a detailed description of the embodiments of the present invention will be described in detail below with reference to the drawings and examples.
In order to solve the problems in the prior art, the invention provides an axisymmetric suction structure for removing the boundary layer of the central cone of the adjustable air inlet channel.
As shown in fig. 4, the main structure of the axisymmetric adjustable air inlet channel provided by the invention comprises: a center cone 1, a center cone rod 3 and a shell 5;
the center cone 1 is arranged on the center cone rod 3 and can slide back and forth along the axial direction; the central cone rod 3 is fixed on the shell 5 through a plurality of hollow support plates 6; the whole air inlet channel is divided into a plurality of spaces of the main channel 8, the support plate cavity 9, the central cone rod cavity 10, the suction cavity 11 and the actuating mechanism cavity 13 by the structure;
wherein the main runner 8 is arranged between the central cone 1, the central cone rod 3 and the shell 5;
the support plate cavity 9 is formed by the plurality of hollow support plates 6 and the outer surface of the central cone rod 3; the support plate cavity 9 is provided with an outlet 7 which is communicated with the atmosphere; the support plate cavity 9 is communicated with the central cone rod cavity 10 through a hollow opening on the support plate 6;
the central cone rod cavity 10 is formed by the inner wall of the central cone rod 3, and the central cone rod cavity 10 is communicated with the suction cavity 11 through a diversion hole 12 formed in the head of the central cone rod 3;
the suction cavity 11 is formed by a central cone 1 and a central cone rod 3, and the suction cavity 11 is communicated with the main runner 8 through an auxiliary surface layer suction hole 4 arranged on the central cone 1;
the inside of the head of the center cone 1 forms the actuating mechanism cavity 13;
in the working process, after the incoming air enters the air inlet channel, the surface layer on the outer surface of the central cone 1 sequentially passes through the surface layer suction hole 4, the suction cavity 11, the flow guide hole 12, the central cone rod cavity 10 and the support plate cavity 9, and finally is discharged into the atmosphere at the outlet 7 of the support plate cavity 9.
Wherein the center cone 1 is arranged on a center cone rod 3 by a sliding bearing 2.
Wherein, the center cone 1 is a thin-wall structure center cone.
Wherein the central taper rod 3 is a central taper rod with a thin-wall structure.
When the center cone 1 slides back and forth along the center cone rod 3, the suction cavity 11 is always communicated with the center cone rod cavity 10 through the guide hole 12, so that the back and forth movement of the center cone 1 does not affect the connectivity of the suction channel.
Wherein, the center cone 1 and the center cone rod 3 are in a coaxial structure.
Wherein, a certain clearance channel 14 is allowed to exist between the tail part of the center cone 1 and the center cone rod 3; because of the higher pressure downstream of the inlet primary flow passage 8, air in the primary flow passage 8 will also enter the suction chamber 11 via the clearance passage 14 and be discharged into the atmosphere together with the boundary layer air flow entering from the boundary layer suction hole 4.
Wherein, there is not clearance between central awl 1 afterbody and the central awl pole 3.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and variations could be made by those skilled in the art without departing from the technical principles of the present invention, and such modifications and variations should also be regarded as being within the scope of the invention.
Claims (1)
1. The utility model provides a structure is absorbed to axisymmetric adjustable intake passage center cone boundary layer which characterized in that, axisymmetric adjustable intake passage's major structure includes: the device comprises a central cone (1), a central cone rod (3) and a shell (5);
the center cone (1) is arranged on the center cone rod (3) and can slide back and forth along the axial direction; the central cone rod (3) is fixed on the shell (5) through a plurality of hollow support plates (6); the whole air inlet channel is divided into a plurality of spaces of a main channel (8), a support plate cavity (9), a central cone rod cavity (10), a suction cavity (11) and an actuating mechanism cavity (13) by the structure;
wherein the main flow channel (8) is arranged between the central cone (1), the central cone rod (3) and the shell (5);
the support plate cavity (9) is formed by the hollow support plates (6) and the outer surfaces of the central conical rods (3); the support plate cavity (9) is provided with an outlet (7) which is communicated with the atmosphere; the support plate cavity (9) is communicated with the central cone rod cavity (10) through a hollow opening on the support plate (6);
the central cone rod cavity (10) is formed by the inner wall of the central cone rod (3), and the central cone rod cavity (10) is communicated with the suction cavity (11) through a diversion hole (12) formed in the head of the central cone rod (3);
the suction cavity (11) is formed by a central cone (1) and a central cone rod (3), and the suction cavity (11) is communicated with the main runner (8) through an auxiliary surface layer suction hole (4) arranged on the central cone (1);
the interior of the head of the center cone (1) forms the actuating mechanism cavity (13);
in the working process, after the incoming air enters the air inlet channel, the surface layer on the outer surface of the central cone (1) sequentially passes through the surface layer suction hole (4), the suction cavity (11), the flow guide hole (12), the central cone rod cavity (10) and the support plate cavity (9), and finally is discharged into the atmosphere at the outlet (7) of the support plate cavity (9);
the center cone (1) is arranged on the center cone rod (3) through a sliding bearing (2);
the center cone (1) is of a thin-wall structure;
the central conical rod (3) is of a thin-wall structure;
when the center cone (1) slides forwards and backwards along the center cone rod (3), the suction cavity (11) is always communicated with the center cone rod cavity (10) through the guide hole (12), so that the forward and backward movement of the center cone (1) does not influence the connectivity of the suction channel;
the center cone (1) and the center cone rod (3) are of a coaxial structure;
a clearance channel (14) is formed between the tail part of the center cone (1) and the center cone rod (3); because the downstream pressure of the main channel (8) of the air inlet channel is higher, air in the main channel (8) can enter the suction cavity (11) through the clearance channel (14) and is discharged into the atmosphere together with the boundary layer airflow entering from the boundary layer suction hole (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011285444.6A CN112392600B (en) | 2020-11-17 | 2020-11-17 | Axisymmetric adjustable intake passage center cone boundary layer sucking structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011285444.6A CN112392600B (en) | 2020-11-17 | 2020-11-17 | Axisymmetric adjustable intake passage center cone boundary layer sucking structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112392600A CN112392600A (en) | 2021-02-23 |
| CN112392600B true CN112392600B (en) | 2023-10-13 |
Family
ID=74600907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011285444.6A Active CN112392600B (en) | 2020-11-17 | 2020-11-17 | Axisymmetric adjustable intake passage center cone boundary layer sucking structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112392600B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB747705A (en) * | 1953-02-06 | 1956-04-11 | Rene Leduc | Improvements in and relating to aero-thermodynamic ducts adapted to operate at supersonic speeds |
| GB915941A (en) * | 1959-03-12 | 1963-01-16 | English Electric Co Ltd | Improvements in and relating to air intakes for air-consuming propulsion engines of supersonic aircraft |
| US4007891A (en) * | 1975-09-12 | 1977-02-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Jet engine air intake system |
| FR2533969A1 (en) * | 1982-10-01 | 1984-04-06 | Deutsche Forsch Luft Raumfahrt | Supersonic inlet for reaction propulsion unit |
| RU2015941C1 (en) * | 1991-10-14 | 1994-07-15 | Научно-производственное предприятие "Триумф" | Method to control boundary layer on aerodynamic surface of aircraft |
| 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 |
| CN102817716A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Binary mixed pressure intake duct applied to supersonic solid ramjet |
| CN104481700A (en) * | 2014-09-25 | 2015-04-01 | 南京航空航天大学 | Combined dynamic axisymmetric variable geometry inlet, engine and air inlet control method |
| CN107091158A (en) * | 2017-06-08 | 2017-08-25 | 南京航空航天大学 | Low extrernal resistance is super/hypersonic inlet and Shock/Boundary-Layer interference control method |
-
2020
- 2020-11-17 CN CN202011285444.6A patent/CN112392600B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB747705A (en) * | 1953-02-06 | 1956-04-11 | Rene Leduc | Improvements in and relating to aero-thermodynamic ducts adapted to operate at supersonic speeds |
| GB915941A (en) * | 1959-03-12 | 1963-01-16 | English Electric Co Ltd | Improvements in and relating to air intakes for air-consuming propulsion engines of supersonic aircraft |
| US4007891A (en) * | 1975-09-12 | 1977-02-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Jet engine air intake system |
| FR2533969A1 (en) * | 1982-10-01 | 1984-04-06 | Deutsche Forsch Luft Raumfahrt | Supersonic inlet for reaction propulsion unit |
| RU2015941C1 (en) * | 1991-10-14 | 1994-07-15 | Научно-производственное предприятие "Триумф" | Method to control boundary layer on aerodynamic surface of aircraft |
| 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 |
| CN102817716A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Binary mixed pressure intake duct applied to supersonic solid ramjet |
| CN104481700A (en) * | 2014-09-25 | 2015-04-01 | 南京航空航天大学 | Combined dynamic axisymmetric variable geometry inlet, engine and air inlet control method |
| CN107091158A (en) * | 2017-06-08 | 2017-08-25 | 南京航空航天大学 | Low extrernal resistance is super/hypersonic inlet and Shock/Boundary-Layer interference control method |
Non-Patent Citations (1)
| Title |
|---|
| 张红军 ; 忻贤钧 ; 白葵 ; 沈清 ; .超声速进气道边界层吸除方案设计及实验.《实验流体力学》.2008,第22卷(第1期),第88-91页. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112392600A (en) | 2021-02-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9027583B2 (en) | Low shock strength inlet | |
| CN103696873B (en) | A kind of axisymmetric vectoring exhaust nozzle with good stealthy function | |
| CN104908975B (en) | Aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method | |
| US7690595B2 (en) | System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines | |
| CN109606707A (en) | A kind of wide area Supersonic Inlet based on plasma flow control | |
| US3982696A (en) | Jet noise suppressor nozzle | |
| CN102673793A (en) | Exhaust ejector system of airplane auxiliary power unit | |
| CN113062800B (en) | Environment-friendly bleed air structure of aircraft engine and aircraft | |
| CN203925778U (en) | The jet apparatus of turbofan engine | |
| CN105156212A (en) | Variable geometry side pressure type air inlet passage of rocket-based-combined-cycle (RBCC) engine | |
| CN113120244A (en) | Design method for improving performance of backpack parallel double-engine double-S-bend air inlet passage | |
| CN112392600B (en) | Axisymmetric adjustable intake passage center cone boundary layer sucking structure | |
| CN104975984A (en) | Turbofan engine structurally integrated with aircraft | |
| KR102572482B1 (en) | Trailing edge core compartment vent for an aircraft engine | |
| CN113104198A (en) | Wave-rider precursor self-adaptive boundary layer displacement inward-transfer air inlet channel integrated design method | |
| CN206012946U (en) | A kind of aircraft precursor whirlpool flow control apparatus | |
| CN110030112B (en) | Fixed-geometry axisymmetric air inlet with double design points | |
| CN113022858A (en) | Nacelle air inlet and exhaust device | |
| CN113879512A (en) | Course synergistic system and wing body fusion layout aircraft with same | |
| GB1211192A (en) | Improvements in low drag exhaust nozzle and nacelle arrangement for turbofan engines | |
| CN203558213U (en) | Disassembling device for boundary layer of airplane air intake duct | |
| CN106218865A (en) | A kind of aircraft precursor eddy current dynamic control device | |
| CN208186339U (en) | Venturi burner with decrease of noise functions | |
| CN103562068B (en) | For the inlet structure of turbojet engine nacelle | |
| CN115743566A (en) | Double-channel embedded air inlet channel |
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 |