CN111520253B - Jet engine structure for airplane based on wind power change - Google Patents
Jet engine structure for airplane based on wind power change Download PDFInfo
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- CN111520253B CN111520253B CN202010359736.3A CN202010359736A CN111520253B CN 111520253 B CN111520253 B CN 111520253B CN 202010359736 A CN202010359736 A CN 202010359736A CN 111520253 B CN111520253 B CN 111520253B
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- injection cylinder
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Wind Motors (AREA)
Abstract
The invention provides a jet engine structure for an airplane based on wind power change, and relates to the technical field of jet engines. This jet engine structure for aircraft based on wind-force changes, which comprises a housin, the inside fixed mounting of casing has the jet cylinder, leave outer duct between casing and the jet cylinder, interior duct has been seted up to the inside of jet cylinder, the intake duct has been seted up to the left end of casing, the right-hand member of intake duct rotates and is connected with the compressor. This jet engine structure for aircraft based on wind-force changes for jet engine's gas outlet can carry out corresponding regulation according to the size that produces the air current, when guaranteeing that the current collector piece does not receive the high-speed air current damage, can carry out effectual utilization to little air current, has improved jet engine output efficiency, can strike off automatically to the dust of the inboard accumulation of gas outlet, has avoided regularly clean to the gas outlet inboard, labour saving and time saving more.
Description
Technical Field
The invention relates to the technical field of jet engines, in particular to a jet engine structure for an airplane based on wind power change.
Background
Jet engines, which are engines that directly produce reaction thrust by means of the airflow ejected at high speed from a nozzle, are widely used as power units of aircrafts, fuel and oxidant react chemically in a combustion chamber to release heat energy, and then the heat energy is converted into the function of adjusting the airflow in the nozzle.
And the size of the gas outlet of traditional air transportation aircraft jet engine nozzle department is fixed unchangeable, can't carry out automatically regulated according to the size of nozzle department blowout air current, when the air current is great, can cause the damage to the gas outlet, and when the air current is less, just can't carry out the efficient utilization to the air current, consequently, jet engine output efficiency has been reduced, and jet engine's export is in long-time the back of using, because with the contact of flue gas, can accumulate the dust, need carry out regularly clearance, waste time and energy.
In order to solve the problems, the inventor provides a jet engine structure for an airplane based on wind power change, so that an air outlet of the jet engine can be correspondingly adjusted according to the size of generated air flow, a flow collecting piece is not damaged by high-speed air flow, small air flow can be effectively utilized, the output efficiency of the jet engine is improved, dust accumulated on the inner side of the air outlet can be automatically scraped, the inner side of the air outlet is prevented from being cleaned regularly, and time and labor are saved.
Disclosure of Invention
In order to achieve the purpose, the invention is realized by the following technical scheme: a jet engine structure for an airplane based on wind power change comprises a shell, a jet cylinder, an outer duct, an inner duct, an air inlet channel, an air compressor, a turbine, a combustion chamber, a nozzle, a mandrel, a current collecting piece, a wind shield, a spring and magnetic sheets.
Wherein:
the utility model discloses a gas turbine engine, including casing, gas nozzle, inner duct, air inlet duct, turbine, fixed mounting has a nozzle, the inside fixed mounting of casing has the gas nozzle, leave outer duct between casing and the gas nozzle, inner duct has been seted up to the inside of gas nozzle, the air inlet duct has been seted up to the left end of casing, the right-hand member of air inlet duct rotates and is connected with the compressor, the right side of the inside compressor of gas nozzle rotates and is connected with the turbine, fixed mounting has the combustion chamber between compressor and the turbine, the spout has been seted up on the right side of gas nozzle, the right-hand member of casing rotates through the dabber and is connected with the current collector, the left end fixed mounting of current collector has the deep bead, one side fixedly connected with spring at casing center is kept away from to the deep bead, the inside and outside both sides fixed mounting of current collector has the magnetic sheet.
Preferably, the shell and the air injection cylinder and the rotating shaft inside the air injection cylinder are fixedly connected through hollow supports, so that air can circulate between the shell and the air injection cylinder and inside the air injection cylinder.
Preferably, the inside rotation of intake duct is connected with the fan, and the center fixed mounting of fan left end has the toper piece for the air can enter into the jet-propelled section of thick bamboo better from the intake duct.
Preferably, the compressor and the turbine are respectively connected to the left side and the right side of the interior of the air injection cylinder in a rotating mode, the combustion chamber is located between the compressor and the turbine, and the conical block is fixedly mounted in the center of the right end of the turbine, so that air can be pressurized firstly when entering the interior of the air injection cylinder, and then the air is ejected out through the turbine after combustion.
Preferably, the current collecting pieces are connected to the right end of the shell in a surrounding and rotating mode, and adjacent current collecting pieces are crossed and staggered, so that good wrapping performance of the current collecting pieces can be kept in the opening and closing process.
Preferably, the wind shield extends leftwards to an outer duct between the shell and the air injection cylinder, and one end of the wind shield close to the inner wall of the shell is fixedly connected with the inner wall of the raised part of the shell through a spring, so that air passing through the inner duct can blow the wind shield.
Preferably, the magnetic sheets are symmetrically distributed on the inner side and the outer side of the current collecting sheets, and in the staggered distribution process of the current collecting sheets, the magnetic poles on the joint surfaces of the two current collecting sheets are synonym magnetic poles, so that the adjacent current collecting sheets can be better attached.
The invention provides a jet engine structure for an airplane based on wind power change. The method has the following beneficial effects:
1. this jet engine structure for aircraft based on wind-force changes, rotate the design of the current collector piece of connection through the casing right-hand member, cooperation current collector piece left end extends to the inside deep bead of outer duct, when the air current grow of production, can make the left end of current collector piece expand, increase the area that gaseous passes through, and when the air current is little, the current collector piece can contract, reduce the area that gaseous passes through, consequently, when guaranteeing that the current collector piece does not receive the high velocity air stream damage, can carry out effectual utilization to the little air current, jet engine output efficiency has been improved.
2. This jet engine structure for aircraft based on wind-force changes, encircle the design of dislocation connection through the current collector piece, the magnetic sheet of the inside and outside both sides of cooperation current collector piece, can make adjacent current collector piece attached each other, guarantee the good parcel nature of current collector piece while, at jet engine stop operation, when current collector piece shrinks substantially, attached current collector piece can strike off the dust that exposes originally accumulation on the inboard surface mutually, and blow off when starting next time, avoided being inboard to the gas outlet regularly clean, save time and save effort more.
Drawings
FIG. 1 is a sectional view of the configuration of the air outlet of the present invention when expanded;
FIG. 2 is a sectional view of the construction of the air outlet of the present invention as it contracts;
FIG. 3 is a cross-sectional view of the structure of FIG. 1 taken along line A-A thereof in accordance with the present invention;
FIG. 4 is a cross-sectional view of the structure of FIG. 1 at B-B in accordance with the present invention;
FIG. 5 is a schematic structural view of a current collector of the present invention;
fig. 6 is a top view of a current collector structure according to the present invention.
In the figure: 1. a housing; 2. an air injector; 3. an outer duct; 4. an inner duct; 5. an air inlet channel; 6. a compressor; 7. a turbine; 8. a combustion chamber; 9. a spout; 10. a mandrel; 11. a current collector; 12. a wind deflector; 13. a spring; 14. a magnetic sheet.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
An example of the structure of the jet engine for the airplane based on the wind power change is as follows:
referring to fig. 1-6, a jet engine structure for an airplane based on wind power change comprises a housing 1, a jet cylinder 2, an outer duct 3, an inner duct 4, an air inlet duct 5, an air compressor 6, a turbine 7, a combustion chamber 8, a nozzle 9, a mandrel 10, a flow collecting plate 11, a wind deflector 12, a spring 13 and a magnetic sheet 14.
Wherein:
an air injection cylinder 2 is fixedly arranged in a shell 1, the shell 1 and the air injection cylinder 2 and a rotating shaft in the shell are fixedly connected by hollow supports, so that air can circulate between the shell 1 and the air injection cylinder 2 and between the air injection cylinder 2 and the rotating shaft in the shell, an outer duct 3 is left between the shell 1 and the air injection cylinder 2, an inner duct 4 is arranged in the air injection cylinder 2, an air inlet channel 5 is arranged at the left end of the shell 1, a fan is rotatably connected in the air inlet channel 5, a conical block is fixedly arranged at the center of the left end of the fan, so that air can better enter the air injection cylinder 2 from the air inlet channel 5, a compressor 6 is rotatably connected at the right end of the air inlet channel 5, a turbine 7 is rotatably connected at the right side of the compressor 6 in the air injection cylinder 2, the compressor 6 and the turbine 7 are respectively rotatably connected at the left side and the right side in the air injection cylinder 2, and a combustion chamber 8 is positioned between the compressor 6 and the turbine 7, the center of the right end of the turbine 7 is fixedly provided with a conical block, so that when air enters the air injection cylinder 2, can pressurize firstly, and then is ejected out through a turbine 7 after combustion, a combustion chamber 8 is fixedly arranged between a compressor 6 and the turbine 7, the right side of an ejection barrel 2 is provided with a nozzle 9, the right end of a shell 1 is rotatably connected with a current collecting piece 11 through a mandrel 10, through the design of the collecting piece 11 which is rotatably connected with the right end of the shell 1, the wind shield 12 which extends to the inner part of the outer duct 3 from the left end of the collecting piece 11 is matched, when the generated gas flow is increased, the left end of the collecting sheet 11 can be unfolded to increase the area through which the gas passes, when the gas flow becomes small, the manifold 11 is contracted to reduce the area through which the gas passes, and therefore, the collector plate 11 is not damaged by high-speed airflow, small airflow can be effectively utilized, and the output efficiency of the jet engine is improved.
The current-collecting plates 11 are connected to the right end of the shell 1 in a surrounding and rotating manner, and adjacent current-collecting plates 11 are staggered in a crossing manner, so that the current-collecting plates 11 can keep good wrapping property in the opening and closing process, a wind shield 12 is fixedly installed at the left end of the current-collecting plates 11, the wind shield 12 extends leftwards to an outer duct 3 between the shell 1 and the air injection cylinder 2, one end of the wind shield 12 close to the inner wall of the shell 1 is fixedly connected with the inner wall of the protruding part of the shell 1 through a spring 13, so that gas passing through the outer duct 3 can be blown to the wind shield 12, one side of the wind shield 12 far away from the center of the shell 1 is fixedly connected with the spring 13, magnetic sheets 14 are fixedly installed at the inner side and the outer side of the current-collecting plates 11, the magnetic sheets 14 are symmetrically distributed at the inner side and the outer side of the current-collecting plates 11, and magnetic poles on the joint surfaces of the two current-collecting plates 11 are different magnetic poles in the staggered distribution process, so that the adjacent current-collecting plates 11 can be better attached, through the design that current collector 11 encircles the dislocation connection, the magnetic sheet 14 of the inside and outside both sides of cooperation current collector 11 can make adjacent current collector 11 attached each other, guarantee the good parcel nature of current collector 11 simultaneously, at jet engine stop operation, when current collector 11 shrinks substantially, attached current collector 11 can strike off the dust that exposes originally and accumulate on the inboard surface mutually, and blow off when starting next time, avoided the inboard timing cleanness of gas outlet, labour saving and time saving more.
When in use, air enters the shell 1 from the air inlet 5, is pressurized by the compressor 6 and then enters the inner duct 4, high-temperature air flow generated by combustion of fuel in the combustion chamber 8 can be accelerated by the turbine 7 and then is sprayed out from the nozzle 9, and then reactive thrust is generated to push the aircraft, the speed of pushing the aircraft is increased as the generated air flow is larger, the air flow passing through the inner part of the outer duct 3 is increased, the stretching spring 13 of the wind deflector 12 can simultaneously move inwards by the action of the air flow in the outer duct 3 on the wind deflector 12, and the right side of the flow collecting piece 11 is simultaneously unfolded outwards, so that the outlet area of the flow collecting piece 11 is increased, the damage of high-speed air flow to the flow collecting piece 11 is avoided, and when the air flow is small, the traveling speed of the aircraft is also reduced, and therefore, the flow speed of the air flow in the outer duct 3 is also reduced, make deep bead 12 remove to the outside under the effect of spring 13 restoring force, and then drive the inward contraction of current collector 11 on right side, reduce the exit area of current collector 11 department, and then increased the thrust that produces under little air current state, improved the utilization efficiency to the air current, and when jet engine stopped operating, current collector 11 can concentrate to shrink to the centre, and then make crisscross current collector 11 carry out relative movement, make attached current collector 11 mutually can strike off the dust that originally exposes accumulation on the inboard surface.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. A jet engine structure for an aircraft based on wind power variation, comprising a casing (1), characterized in that: the inner fixed mounting of the shell (1) is provided with an air injection cylinder (2), an outer duct (3) is left between the shell (1) and the air injection cylinder (2), an inner duct (4) is arranged inside the air injection cylinder (2), an air inlet channel (5) is arranged at the left end of the shell (1), the right end of the air inlet channel (5) is rotatably connected with a gas compressor (6), the right side of the gas compressor (6) inside the air injection cylinder (2) is rotatably connected with a turbine (7), a combustion chamber (8) is fixedly mounted between the gas compressor (6) and the turbine (7), a nozzle (9) is arranged at the right side of the air injection cylinder (2), the right end of the shell (1) is rotatably connected with a current collecting sheet (11) through a mandrel (10), the left end of the current collecting sheet (11) is fixedly mounted with a wind shield (12), and the wind shield (12) is far away from one side fixedly connected with a spring (13) at the center of the shell (1), magnetic sheets (14) are fixedly arranged on the inner side and the outer side of the current collecting sheet (11); the current collecting pieces (11) are connected to the right end of the shell (1) in a surrounding and rotating mode, and adjacent current collecting pieces (11) are staggered in a crossing mode; the wind shield (12) extends to an outer duct (3) between the shell (1) and the air injection cylinder (2) leftwards, and one end close to the inner wall of the shell (1) is fixedly connected with the inner wall of the convex part of the shell (1) through a spring (13); the magnetic sheets (14) are symmetrically distributed on the inner side and the outer side of the current collecting sheets (11), and in the staggered distribution process of the current collecting sheets (11), the magnetic poles on the joint surfaces of the two current collecting sheets (11) are synonym magnetic poles;
by utilizing the action of the air flow in the outer duct (3) on the wind shield (12), the extension spring (13) of the wind shield (12) can simultaneously move inwards, the right side of the current collecting piece (11) can simultaneously expand outwards, the outlet area of the current collecting piece (11) is increased, the damage of high-speed air flow on the current collecting piece (11) is avoided, when the air flow is small, the advancing speed of an aircraft is slowed, the flow rate of the air flow in the outer duct (3) is reduced, the wind shield (12) moves outwards under the action of the restoring force of the spring (13), the current collecting piece (11) on the right side is driven to contract inwards, the outlet area of the current collecting piece (11) is reduced, when the jet engine stops operating, the current collecting piece (11) can concentrate to contract towards the middle, the staggered current collecting pieces (11) move relatively, and the attached current collecting pieces (11) can scrape the dust originally exposed on the inner side surface And (4) removing.
2. A wind power variation-based jet engine structure for an aircraft according to claim 1, wherein: the shell (1) and the air injection cylinder (2) and the rotating shaft inside are fixedly connected by hollow supports.
3. A wind power variation-based jet engine structure for an aircraft according to claim 1, wherein: the inside of intake duct (5) rotates and is connected with the fan, and the center fixed mounting of fan left end has the toper piece.
4. A wind power variation-based jet engine structure for an aircraft according to claim 1, wherein: the gas compressor (6) and the turbine (7) are respectively connected to the left side and the right side inside the gas injection cylinder (2) in a rotating mode, the combustion chamber (8) is located between the gas compressor (6) and the turbine (7), and a conical block is fixedly installed in the center of the right end of the turbine (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010359736.3A CN111520253B (en) | 2020-04-30 | 2020-04-30 | Jet engine structure for airplane based on wind power change |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010359736.3A CN111520253B (en) | 2020-04-30 | 2020-04-30 | Jet engine structure for airplane based on wind power change |
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| CN111520253A CN111520253A (en) | 2020-08-11 |
| CN111520253B true CN111520253B (en) | 2021-07-27 |
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| CN113788139B (en) * | 2021-10-26 | 2024-05-24 | 上海磐拓航空科技服务有限公司 | Method for precisely controlling track of aircraft by using multifunctional pneumatic control surface |
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| FR2860046B1 (en) * | 2003-09-19 | 2005-12-02 | Snecma Moteurs | HOT PIPE CONTROL OF AXISYMETRIC TUYERE TURBOJET ENGINE |
| CN101008365A (en) * | 2007-01-12 | 2007-08-01 | 杨清太 | Multi-nozzle jet engine and method for driving heliogyro thereby |
| US9701415B2 (en) * | 2007-08-23 | 2017-07-11 | United Technologies Corporation | Gas turbine engine with axial movable fan variable area nozzle |
| CN104975984A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Turbofan engine structurally integrated with aircraft |
| CN106194494B (en) * | 2016-08-09 | 2018-01-05 | 南京理工大学 | A kind of adjustable jet for Micro Turbine Jet Engine after-burner |
| CN109850142B (en) * | 2018-08-08 | 2023-03-31 | 珠海市蓝鹰贸易有限公司 | Novel jet-propelled vertical lift aircraft and novel aviation power system |
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Effective date of registration: 20210707 Address after: 317600 south side of Xuanmen phase III marine economic transformation and upgrading demonstration zone, Yuhuan City, Taizhou City, Zhejiang Province Applicant after: YUHUAN TIANRUN AVIATION MACHINERY MANUFACTURING Co.,Ltd. Address before: No.82, caosan street, Guzhen Town, Zhongshan City, Guangdong Province 528421 Applicant before: Zhu Fengmei |
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