CN108894890A - A kind of tiny engine adjustable orifice - Google Patents
A kind of tiny engine adjustable orifice Download PDFInfo
- Publication number
- CN108894890A CN108894890A CN201810982070.XA CN201810982070A CN108894890A CN 108894890 A CN108894890 A CN 108894890A CN 201810982070 A CN201810982070 A CN 201810982070A CN 108894890 A CN108894890 A CN 108894890A
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- CN
- China
- Prior art keywords
- rack gear
- adjustable
- spout
- adjustable orifice
- frame
- 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.)
- Pending
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Classifications
-
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Special Spraying Apparatus (AREA)
Abstract
The present invention relates to nozzle technical fields, and in particular to a kind of tiny engine adjustable orifice.Including engine jet pipe, its main feature is that being provided with adjustable orifice frame on the jet pipe, spout linkage adjustable plate is provided in adjustable orifice frame, universal drive shaft is installed by being driven shaft fixing support on adjustable orifice frame, universal drive shaft is connected with active rack gear connecting rod, active rack gear is provided on active rack gear connecting rod, active rack gear is engaged with the driven rack gear being mounted on adjustable orifice frame to be connected.It adjusts spout linkage adjustable plate and realizes that spout is adjusted, be adapted to a variety of aircraft by adjusting universal drive shaft, adjustable to play engine maximum performance；Its structural principle is simple, and minute vehicle all vectors are promoted.
Description
Technical field
The present invention relates to nozzle technical fields, and in particular to a kind of tiny engine adjustable orifice.
Background technique
Jet pipe is one of component part of turbojet engine of jet plane, and main function is to fire jet plane
Product such as carbon dioxide, sulfur dioxide, carbon monoxide, nitrogen oxides, imperfect combustion small molecule hydrocarbon after oil firing
Matter ejects, and plays the role of waste air, while also pushing aircraft using the reaction force that air when injection generates.
Adjustable orifice makes aircraft directly control the size of thrust by the size of adjusting spout, indirectly control aircraft
Speed.There are three nozzle exit area is general：Big spout, middle spout, small spout.The position of different spouts corresponds to different engine shapes
State：Big spout corresponds to aircraft and flies Afterburning condition.Aircraft is fastest at this time；Middle spout corresponds to the general state of engine
(such as specified, cruise), the speed of aircraft is in midrange velocity envelope at this time；Small spout correspond to engine " maximum " state or small turn
Fast state, the speed of aircraft is only second to reinforcing or in small velocity interval at this time.
China Patent No. " CN106150754A " discloses a kind of axial symmetry plug vector spray.Including：Cylinder, leading portion are
Cylindrical type flat segments, back segment are converging portion；Plug cone leading portion is located at inner barrel, and the inner mold face of the rear end of plug cone leading portion is spherical surface；
Plug cone back segment, front end has and the outer mold surface that matches of plug cone leading portion rear end inner mold face shapes and sizes, and by outer mold surface with
The inner mold face of plug cone leading portion constitutes spherical pair；Supporting plate, one end and cylinder fasten, and the other end is fixed with plug cone leading portion；Pressurized strut, position
In the inner cavity that the plug cone leading portion rear end and plug cone back segment front end are formed, one end is hinged on plug cone leading portion inner wall, separately
One end is hinged on the inner wall of plug cone back segment.Axial symmetry plug vector spray of the invention, it is simple and reliable for structure, it can be effectively real
Existing vector promotes, and meets the needs of engine different working condition, but its slewing area is small.
Micro turbine engine spout in the prior art is all a single state, the usability under complicated multi-state environment
Energy can not be optimal.
Summary of the invention
It is an object of the invention to avoid the deficiencies in the prior art from providing a kind of tiny engine adjustable orifice, to solve
Problems of the prior art.
To achieve the above object, the technical scheme adopted by the invention is as follows：A kind of tiny engine adjustable orifice, packet
Engine jet pipe is included, its main feature is that being provided with adjustable orifice frame on the jet pipe, is provided with spout in adjustable orifice frame
Link adjustable plate, is equipped with universal drive shaft, universal drive shaft and active by being driven shaft fixing support on adjustable orifice frame
Rack gear connecting rod is connected, and is provided with active rack gear on active rack gear connecting rod, active rack gear be mounted on adjustable orifice frame from
Carry-over bar engagement is connected.
The spout linkage adjustable plate setting passes through pin in adjustable orifice frame medial surface both ends, spout linkage adjustable plate
Axis is connected with active rack gear and driven rack gear respectively, and active rack gear and driven rack gear end of engagement pass through limit screw cap and adjustable orifice
Frame is connected, and universal drive shaft drives active rack gear, and the driven rack gear of active rack drives realizes the rotation of spout linkage adjustable plate
To which spout be adjusted.
The beneficial effects of the invention are as follows：A kind of tiny engine adjustable orifice, by adjusting universal drive shaft,
It adjusts spout linkage adjustable plate and realizes that spout is adjusted, be adapted to a variety of aircraft, it is adjustable to play engine maximality
Energy；Its structural principle is simple, and minute vehicle all vectors are promoted.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is schematic view of the front view of the invention.
As shown in the figure：1. jet pipe；2. universal drive shaft；3. being driven shaft fixing support；4. active rack gear connecting rod；5. adjustable spray
Mouth frame；6. active rack gear；7. driven rack gear；8. limit screw cap；The adjustable plate 9. spout links.
Specific embodiment
The principle and features of the present invention will be described below with reference to the accompanying drawings, and the given examples are served only to explain the present invention, and
It is non-to be used to limit the scope of the invention.
As illustrated in fig. 1 and 2, a kind of tiny engine adjustable orifice, including engine jet pipe 1, its main feature is that institute
It is provided with adjustable orifice frame 5 on the jet pipe 1 stated, spout linkage adjustable plate 9, adjustable orifice are provided in adjustable orifice frame 5
Universal drive shaft 2 is installed by being driven shaft fixing support 3 on frame 5, universal drive shaft 2 is connected with active rack gear connecting rod 4, main
Active rack gear 6 is provided on carry-over bar connecting rod 4, active rack gear 6 is engaged with the driven rack gear 7 being mounted on adjustable orifice frame 5
It is connected.
At 5 medial surface both ends of adjustable orifice frame, spout linkage adjustable plate 9 is logical for spout linkage adjustable plate 9 setting
It crosses pin shaft to be connected with active rack gear 6 and driven rack gear 7 respectively, active rack gear 6 and 7 end of engagement of driven rack gear pass through limit screw cap 8
It is connected with adjustable orifice frame 5, universal drive shaft 2 drives active rack gear 6, and active rack gear 6 drives driven rack gear 7, realizes spout
The rotation of linkage adjustable plate 9 is to be adjusted spout 1.
The foregoing is merely presently preferred embodiments of the present invention, is not intended to limit the invention, it is all in spirit of the invention and
Within principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (2)
1. a kind of tiny engine adjustable orifice, including engine jet pipe, it is characterized in that being provided with adjustable spray on the jet pipe
Mouthful frame is provided with spout linkage adjustable plate in adjustable orifice frame, passes through transmission shaft fixing support peace on adjustable orifice frame
Equipped with universal drive shaft, universal drive shaft is connected with active rack gear connecting rod, and active rack gear is provided on active rack gear connecting rod, actively
Rack gear is engaged with the driven rack gear being mounted on adjustable orifice frame to be connected.
2. a kind of tiny engine adjustable orifice as described in claim 1, which is characterized in that the spout linkage adjustable plate
Setting at adjustable orifice frame medial surface both ends, spout link adjustable plate by pin shaft respectively with active rack gear and driven rack gear phase
Even, active rack gear and driven rack gear end of engagement are connected by limit screw cap with adjustable orifice frame, and universal drive shaft driving is actively
Rack gear, the driven rack gear of active rack drives realize the rotation of spout linkage adjustable plate to which spout be adjusted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810982070.XA CN108894890A (en) | 2018-08-27 | 2018-08-27 | A kind of tiny engine adjustable orifice |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810982070.XA CN108894890A (en) | 2018-08-27 | 2018-08-27 | A kind of tiny engine adjustable orifice |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108894890A true CN108894890A (en) | 2018-11-27 |
Family
ID=64358711
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810982070.XA Pending CN108894890A (en) | 2018-08-27 | 2018-08-27 | A kind of tiny engine adjustable orifice |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108894890A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112295803A (en) * | 2020-09-25 | 2021-02-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet device with continuously adjustable nozzle height |
| CN114459769A (en) * | 2022-04-14 | 2022-05-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Small-size turbojet engine ground thrust vector calibration device |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3837579A (en) * | 1972-06-19 | 1974-09-24 | Construct De Moteurs D Aviat S | Variable-geometry nozzle for a jet engine |
| US4037405A (en) * | 1975-09-30 | 1977-07-26 | United Technologies Corporation | Two dimensional nozzle with rotating plug |
| US4778109A (en) * | 1986-12-17 | 1988-10-18 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Adjustable two dimensional nozzle for aircraft jet engines |
| US5050803A (en) * | 1989-10-12 | 1991-09-24 | General Electric Company | Actuation system for positioning a vectoring exhaust nozzle |
| FR2740833A1 (en) * | 1995-11-02 | 1997-05-09 | Snecma | Jet engine variable=section outlet pipe, mounted on rear end of fixed circular-section structure of exhaust duct |
| RU2187681C1 (en) * | 2001-03-27 | 2002-08-20 | Акционерное общество открытого типа Авиамоторный научно-технический комплекс "Союз" | Air-jet engine exit two-dimensional nozzle |
| CN103696875A (en) * | 2013-12-05 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Sawtooth angle-adjustable two-dimensional vectoring nozzle |
| CN104806378A (en) * | 2015-04-02 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary plug type spray pipe having reverse thrusting function |
| CN108087144A (en) * | 2017-11-28 | 2018-05-29 | 中国航发沈阳发动机研究所 | A kind of binary plug vector spray and with its aircraft |
| CN208633941U (en) * | 2018-08-27 | 2019-03-22 | 西北工业大学 | A kind of tiny engine adjustable orifice |
-
2018
- 2018-08-27 CN CN201810982070.XA patent/CN108894890A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3837579A (en) * | 1972-06-19 | 1974-09-24 | Construct De Moteurs D Aviat S | Variable-geometry nozzle for a jet engine |
| US4037405A (en) * | 1975-09-30 | 1977-07-26 | United Technologies Corporation | Two dimensional nozzle with rotating plug |
| US4778109A (en) * | 1986-12-17 | 1988-10-18 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Adjustable two dimensional nozzle for aircraft jet engines |
| US5050803A (en) * | 1989-10-12 | 1991-09-24 | General Electric Company | Actuation system for positioning a vectoring exhaust nozzle |
| FR2740833A1 (en) * | 1995-11-02 | 1997-05-09 | Snecma | Jet engine variable=section outlet pipe, mounted on rear end of fixed circular-section structure of exhaust duct |
| RU2187681C1 (en) * | 2001-03-27 | 2002-08-20 | Акционерное общество открытого типа Авиамоторный научно-технический комплекс "Союз" | Air-jet engine exit two-dimensional nozzle |
| CN103696875A (en) * | 2013-12-05 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Sawtooth angle-adjustable two-dimensional vectoring nozzle |
| CN104806378A (en) * | 2015-04-02 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary plug type spray pipe having reverse thrusting function |
| CN108087144A (en) * | 2017-11-28 | 2018-05-29 | 中国航发沈阳发动机研究所 | A kind of binary plug vector spray and with its aircraft |
| CN208633941U (en) * | 2018-08-27 | 2019-03-22 | 西北工业大学 | A kind of tiny engine adjustable orifice |
Non-Patent Citations (1)
| Title |
|---|
| 陈本柱: "推力换向和二元喷管技术的发展", 航空科学技术, no. 1, pages 35 - 39 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112295803A (en) * | 2020-09-25 | 2021-02-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet device with continuously adjustable nozzle height |
| CN114459769A (en) * | 2022-04-14 | 2022-05-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Small-size turbojet engine ground thrust vector calibration device |
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