CN106089488A - A kind of engine jet pipe structure of band flow separation active control function - Google Patents
A kind of engine jet pipe structure of band flow separation active control function Download PDFInfo
- Publication number
- CN106089488A CN106089488A CN201610378236.8A CN201610378236A CN106089488A CN 106089488 A CN106089488 A CN 106089488A CN 201610378236 A CN201610378236 A CN 201610378236A CN 106089488 A CN106089488 A CN 106089488A
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- China
- Prior art keywords
- nozzle section
- air flow
- deflector portion
- flow deflector
- jet pipe
- 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.)
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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
-
- 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
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
Abstract
The invention discloses the engine jet pipe structure of a kind of band flow separation active control function, including: the first nozzle section, first nozzle section is serpentine, and the first end of the first nozzle section and the high-temperature turbine outlet of electromotor, the second end of the first nozzle section has air vent；Air flow regulator, is arranged on the first nozzle section, for the shear stress values in each air flow deflector portion of sensing the first nozzle section, and regulates the air-flow in the first nozzle section according to the shear stress values in each air flow deflector portion；The engine jet pipe structure of the band flow separation active control function of application technical solution of the present invention, solves the curved jet pipe of S of the prior art and uses big jet pipe offset distance to cause engine interior flow separation, and the problem that the motor power caused declines.
Description
Technical field
The present invention relates to aero-engine field, sending out in particular to a kind of band flow separation active control function
Motivation nozzle structure.
Background technology
For aero-engine, the radiation signal of its jet pipe has important impact to the Stealth Fighter of aircraft.
Research shows, the curved jet pipe of S has advantage will be apparent below: (1) crooked jet profile can be to nozzle ring, after-burner flame
The internal high temperature parts such as regulator block completely so that aircraft its high-temperature turbine end face under any flight attitude all can not
Shone directly into, so can be significantly reduced the infrared intensity in jet pipe hot wall face；(2) the non-axis symmetry binary outlet of jet pipe
Feature can shorten tail jet high temperature core section length, strengthens the blending effect of tail jet and ambient atmosphere, and jet pipe heat is greatly reduced
The infrared intensity of tail jet；(3) incident electromagnetic wave repeatedly reflects in the curved passage of S and is dissipated, and can strengthen exhaust system
System radar invisible characteristic；(4) the curved jet pipe of S is applied to Flying-wing's aircraft, while having good Stealth Fighter, by the back of the body
Negative formula mount scheme, can be substantially reduced the extrernal resistance of aircraft.Therefore, the curved jet pipe of S as a crucial low detectivity technology,
It is applied on the electromotor on multiple strategic bomber and UCAV.In order to ensure the super maneuver ability of fighter plane, right
The thrust-weight ratio of dynamical system requires the highest, and this curved jet pipe of S being accomplished by fighter engine uses ultra-compact design, i.e. needs
The curved jet pipe of S uses bigger jet pipe offset distance.But big S curved jet pipe offset distance can cause the flow separation within jet pipe, cause spray
The drastically decline of pipe performance, ultimately results in the decline of motor power, brings difficulty to the supermaneuver flight of opportunity of combat.
Summary of the invention
Present invention is primarily targeted at the engine jet pipe structure that a kind of band flow separation active control function is provided, with
At least solving the curved jet pipe of S of the prior art uses big jet pipe offset distance to cause engine interior flow separation, and sending out of causing
The problem that motivation thrust declines.
In order to realize goal of the invention, according to present invention, it is provided that sending out of a kind of band flow separation active control function
Motivation nozzle structure, including: the first nozzle section, the first nozzle section is serpentine, the first end of the first nozzle section and the height of electromotor
Temperature turbine outlet connection, the second end of the first nozzle section has air vent；Air flow regulator, is arranged on the first nozzle section,
For sensing the shear stress values in each air flow deflector portion of the first nozzle section, and according to the shear stress in each air flow deflector portion
Air-flow in value regulation the first nozzle section.
Further, the first nozzle section sequentially forms the second air flow deflector portion and along its first end to the direction of the second end
Three air flow deflector portions；Wherein, air flow regulator includes: the first sensing parts, is arranged on the upper wall surface in the second air flow deflector portion,
For sensing the shear stress values of the upper wall surface in the second air flow deflector portion；Secondary Flow injection apparatus, is arranged on the second air flow deflector
The upper wall surface in portion, for the shear stress values according to the upper wall surface in the second air flow deflector portion with angle adjustable and adjustable flow along the
The upper wall surface jet-stream wind in two air flow deflector portions.
Further, the first sensing parts are provided with multiple, and multiple first sensing parts are along the air-flow stream of the first nozzle section
Dynamic direction is evenly arranged.
Further, one end of Secondary Flow injection apparatus is connected with the compressor of electromotor, Secondary Flow injection apparatus another
One end is connected to upper wall surface and the air inlet of close first nozzle section in the second air flow deflector portion.
Further, air flow regulator also includes: the second sensing parts, is arranged on the lower wall in the 3rd air flow deflector portion
Face, for the shear stress values of the lower wall surface in sensing the 3rd air flow deflector portion；Exhaust apparatus, is arranged on the 3rd air flow deflector portion
Lower wall surface, the shear stress values for the lower wall surface according to the 3rd air flow deflector portion will be located in the 3rd air flow deflector with adjustable flow
The fraction of the lower wall surface in portion is discharged.
Further, the second sensing parts are provided with multiple, and multiple second sensing parts are along the air-flow stream of the first nozzle section
Dynamic direction is evenly arranged.
Further, air flow regulator also includes: feedback system, respectively with the first sensing parts and the second sensing parts
And Secondary Flow injection apparatus and exhaust apparatus connect；Feedback system is for the shearing of the upper wall surface according to the second air flow deflector portion
Stress value controls spray angle and the injection flow of Secondary Flow injection apparatus；And feedback system is for according to the 3rd air flow deflector
The shear stress values of the lower wall surface in portion controls the extraction flow of exhaust apparatus.
Further, the engine jet pipe structure of band flow separation active control function also includes: the second nozzle section, second
Nozzle section is serpentine, and the first end of the second nozzle section has the high-temperature turbine with electromotor and exports the air inlet being connected, the second spray
Second end of pipeline section and the first end of the first nozzle section are connected in the second nozzle section and the first nozzle section along air inlet to aerofluxus
The direction of mouth sequentially forms the first air flow deflector portion, the second air flow deflector portion and the 3rd air flow deflector portion.
Further, the common tangent of the upper wall surface in the lower wall surface in the second air flow deflector portion and the 3rd air flow deflector portion crosses air inlet
The minimum point of mouth cross section.
Further, the length ratio of the axis direction that the second nozzle section and the first nozzle section export along high-temperature turbine is 2:
Between 3 to 2: 5 and the ratio of length sum and the maximum gauge of the second nozzle section of the second nozzle section and the first nozzle section is less than 2.
The engine jet pipe structure of the band flow separation active control function of application technical solution of the present invention, including: serpentine
The first nozzle section, the first end of the first nozzle section and the high-temperature turbine outlet of electromotor, the second end of the first nozzle section
Having air vent, be provided with air flow regulator on the first nozzle section, air flow regulator is for sensing the first nozzle section
The shear stress values in each air flow deflector portion, and regulate in the first nozzle section according to the shear stress values in each air flow deflector portion
Air-flow.Solving the curved jet pipe of S of the prior art uses big jet pipe offset distance to cause engine interior flow separation, and cause
The problem that motor power declines.
Accompanying drawing explanation
Accompanying drawing described herein is used for providing a further understanding of the present invention, constitutes the part of the application, this
Bright schematic description and description is used for explaining the present invention, is not intended that inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the engine jet pipe structure of the most optional a kind of band flow separation active control function
Schematic diagram；
Fig. 2 is the engine jet pipe structure of the most optional a kind of band flow separation active control function
Radial deflection structural representation.
Wherein, above-mentioned accompanying drawing includes the following drawings labelling:
1, the first nozzle section；11, air vent；2, the second nozzle section；21, air inlet；3, air flow regulator；31, first
Sensing parts；32, Secondary Flow injection apparatus；33, the second sensing parts；34, exhaust apparatus；35, feedback system；4, the first air-flow
Deflector；5, the second air flow deflector portion；6, the 3rd air flow deflector portion.
Detailed description of the invention
In order to make those skilled in the art be more fully understood that the present invention program, below in conjunction with in the embodiment of the present invention
Accompanying drawing, is clearly and completely described the technical scheme in the embodiment of the present invention, it is clear that described embodiment is only
The embodiment of a present invention part rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under not making creative work premise, all should belong to the model of present invention protection
Enclose.
The engine jet pipe structure of band flow separation active control function according to embodiments of the present invention, as it is shown in figure 1, bag
Including: the first nozzle section 1 and air flow regulator 3, the first nozzle section 1 is serpentine, the first end of the first nozzle section 1 and electromotor
High-temperature turbine outlet, the second end of the first nozzle section 1 has air vent 11；Air flow regulator 3 is arranged at the first spray
On pipeline section 1, for the shear stress values in each air flow deflector portion of sensing the first nozzle section 1, and according to each air flow deflector portion
Shear stress values regulate the air-flow in the first nozzle section 1.
The engine jet pipe structure of the band flow separation active control function of application technical solution of the present invention, including: serpentine
The first nozzle section 1, the first end of the first nozzle section 1 and the high-temperature turbine outlet of electromotor, the second of the first nozzle section 1
End has air vent 11, is provided with air flow regulator 3 on the first nozzle section 1, and air flow regulator 3 is for sensing the first spray
The shear stress values in each air flow deflector portion of pipeline section 1, and regulate the first spray according to the shear stress values in each air flow deflector portion
Air-flow in pipeline section 1.Solving the curved jet pipe of S of the prior art uses big jet pipe offset distance to cause engine interior flow separation,
And the problem that the motor power caused declines.
When being embodied as, the engine jet pipe structure of the band flow separation active control function of the embodiment of the present invention is also wrapped
Including: the second nozzle section 2, the second nozzle section 2 is similarly serpentine, and alternatively, the first nozzle section 1 is the serpentine of forward, the second spray
Pipeline section 2 is reverse serpentine, and the first end of the second nozzle section 2 has the high-temperature turbine with electromotor and exports the air inlet being connected
21, the cross section of air inlet 21 is that circular and with electromotor high-temperature turbine exit end face matches, the aerofluxus of the first nozzle section 1
Mouth 11 is rectangular air outlet, consequently facilitating nozzle and the integrated design of aircraft, thus reduce the flight resistance of opportunity of combat
Power.Second end of the second nozzle section 2 and the first end of the first nozzle section 1 connect thus at the second nozzle section 2 and the first nozzle section 1
The middle direction along air inlet 21 to air vent 11 sequentially forms the 4, second air flow deflector portion of the first air flow deflector portion 5 and the 3rd air-flow
Deflector 6, the runner in the first air flow deflector portion 4 along the second nozzle section 2 radially downward deviation high-temperature turbine outlet axially make
Air-flow from high-temperature turbine outlet flows downward and deviates the axial of high-temperature turbine outlet；The runner in the second air flow deflector portion 5 by
It is deflected downwardly the axis direction of high-temperature turbine outlet transfer to along the deflection radially upward of the second nozzle section 2 and tend to high-temperature turbine and go out
Mouthful axis direction, i.e. air-flow is transferred to by flowing downward and flowing up；The runner in the 3rd air flow deflector portion 6 from upper deflecting and toward
The axis direction of high-temperature turbine outlet transfers the direction parallel with the axis of high-temperature turbine outlet to, thus will be inclined by the 3rd air-flow
The air-flow of transfer part 6 is along the direction at a high speed ejection parallel with the axis of high-temperature turbine outlet.
By regulating the 4, second air flow deflector portion of the first air flow deflector portion 5 and the radial direction offset distance in the 3rd air flow deflector portion 6, reach
To under predetermined draw ratio, by internal to high-temperature turbine outlet and the nozzle ring of inside, after-burner flameholder etc.
High-temperature component blocks effectively, thus reduces the infrared intensity in jet pipe hot wall face so that electromotor is in any angle
Its high-temperature turbine exit end face lower all can not be shone directly into.
Specifically, as in figure 2 it is shown, the public affairs of the lower wall surface in the upper wall surface in the second air flow deflector portion 5 and the 3rd air flow deflector portion 6
Tangent line MN crosses minimum point B of the cross section of air inlet 21 and the peak C of the cross section of air vent 11.By the second air flow deflector
The radial direction offset distance in portion 5 and the 3rd air flow deflector portion 6 reaches the purpose blocked completely by high-temperature turbine exit end face.
Alternatively, the length ratio of the axis direction that the second nozzle section 2 and the first nozzle section 1 export along high-temperature turbine is 2:
To ensure that there is higher aeroperformance between 3 to 2: 5.
It addition, the length sum of the second nozzle section 2 and the first nozzle section 1 is little with the ratio of the maximum gauge of the second nozzle section 2
In 2, the length of the most whole nozzle structure is less than 2 with the diameter ratio of air inlet 21, thus reduces the volume of jet pipe, and raising is started
The thrust-weight ratio of machine.
Second nozzle section 2 and some coincidence of the first nozzle section 1, the first air flow deflector portion 4 is near the second nozzle section 2
At air inlet 21, the second air flow deflector portion 5 is positioned at the second nozzle section 2 and the transition position of the first nozzle section 1, the 3rd air flow deflector portion
6 at the air vent 11 of the first nozzle section 1.
As it is shown in figure 1, air flow regulator 3 includes: the first sensing parts 31 and Secondary Flow injection apparatus 32, the first sensing
Parts 31 are provided with multiple, and multiple first sensing parts 31 are evenly arranged in second along the air current flow direction of the first nozzle section 1
The upper wall surface in air flow deflector portion 5, for the shear stress values of the upper wall surface in sensing the second air flow deflector portion 5；Secondary Flow injection dress
Put at 32 upper wall surfaces being similarly disposed at the second air flow deflector portion 5, for the shearing of the upper wall surface according to the second air flow deflector portion 5
Stress value with angle adjustable and adjustable flow along the upper wall surface jet-stream wind in the second air flow deflector portion 5.First sensing parts 31 are
Being attached to the foil gauge of the upper wall surface in the second air flow deflector portion 5, the air-flow through the second air flow deflector portion 5 is transferred to by flowing downward
Flow up, thus at the upper wall surface in the second air flow deflector portion 5, flow separation occurs, now, cutting on the wall at separation
Shearing stress value meeting respective change, under different engine behaviors, jet pipe internal flow separation situation is different, and the shearing recorded should
Force value is the most different, when foil gauge senses that stress value is zero, i.e. would know that flow separation completely occur.Secondary Flow injection dress
Putting one end of 32 to be connected with the compressor of electromotor, the other end of Secondary Flow injection apparatus 32 is connected to the second air flow deflector portion 5
Upper wall surface, thus the high pressure draught of engine compressor is guided at the upper wall surface in the second air flow deflector portion 5, Secondary Flow sprays
Device 32 has and controls the flow control valve of its injection flow size and regulate the linkage of its spray angle, by
Flow control valve and linkage send corresponding control instruction can be according to the size of the stress value recorded, with angle adjustable
With adjustable flow along the upper wall surface jet-stream wind in the second air flow deflector portion 5, thus make up the upper wall surface in the second air flow deflector portion 5
The impact that the thrust of electromotor is caused by flow separation, it is ensured that the thrust of electromotor.
Air-flow through the 3rd air flow deflector portion 6 can flow along the upper wall surface in the 3rd air flow deflector portion 6, thus at the 3rd gas
Produce flow separation at the lower wall surface of stream deflector 6, therefore, at the lower wall surface in the 3rd air flow deflector portion 6, be additionally provided with second
Sensing parts 33 and exhaust apparatus 34, alternatively, the second sensing parts 33 are also equipped with multiple, and the second sensing parts 33 are also adopted by
Foil gauge is uniformly attached on the lower wall surface in the 3rd air flow deflector portion 6 along the air current flow direction of the first nozzle section 1, is used for sensing
The shear stress values of the lower wall surface in the 3rd air flow deflector portion 6；Exhaust apparatus 34 is one and is arranged on the 3rd air flow deflector portion 6 times
On wall and the exhaust window of scalable aperture size, when there is flow separation in the lower wall surface in the 3rd air flow deflector portion 6, aerofluxus
The aperture of exhaust window is regulated to accordingly by device 34 according to the shear stress values of the lower wall surface in the 3rd air flow deflector portion 6 recorded
Size, owing in jet pipe, stream pressure is higher than exhaust window, by this pressure differential by the lower wall surface in the 3rd air flow deflector portion 6
Low energy fluid discharge nozzle, thus effectively eliminate the 3rd air flow deflector portion 6 lower wall surface at flow separation.
Alternatively, the shear stress values in order to realize recording the first sensing parts 31 and the second sensing parts 33 makes sound
Should, and control Secondary Flow injection apparatus 32 and exhaust apparatus 34 upper wall surface and the 3rd air-flow respectively to the second air flow deflector portion 5
The air-flow of the lower wall surface of deflector 6 is adjusted, and alternatively, air flow regulator 3 also includes: feedback system 35, feedback system
35 survey to receive the first sensing parts 31 and the second sensing parts 33 with the first sensing parts 31 and the second sensing parts 33 respectively
The shear stress values obtained, feedback system 35 also connects with the flow control valve on Secondary Flow injection apparatus 32 and linkage simultaneously
Connecing and exhaust window on exhaust apparatus 34 connects, feedback system 35 receives cutting of the upper wall surface in the second air flow deflector portion 5
During shearing stress value, the flow control valve on Secondary Flow injection apparatus 32 and linkage send control instruction respectively, pass through
The jet-impingement flow of flow control valve gate control Secondary Flow injection apparatus 32, controls Secondary Flow injection apparatus by linkage
The spray angle of 32, thus the flow separation at the upper wall surface in the second air flow deflector portion 5 is effectively regulated；Feedback system 35
During the shear stress values of the lower wall surface receiving the 3rd air flow deflector portion 6, send control to the exhaust window of exhaust apparatus 34 and refer to
Order, by controlling the aperture regulation extraction flow of exhaust window, thus divides the flowing at the lower wall surface in the 3rd air flow deflector portion 6
From effectively regulating.
Below it is only the preferred embodiment of the present invention, it is noted that those skilled in the art are come
Saying, under the premise without departing from the principles of the invention, it is also possible to make some improvements and modifications, these improvements and modifications also should be regarded as
Protection scope of the present invention.
Claims (10)
1. the engine jet pipe structure of a band flow separation active control function, it is characterised in that including:
First nozzle section, described first nozzle section is serpentine, the first end of described first nozzle section and the high-temperature turbine of electromotor
Outlet, the second end of described first nozzle section has air vent；
Air flow regulator, is arranged on described first nozzle section, for sensing each air flow deflector of described first nozzle section
The shear stress values in portion, and according to the gas in the shear stress values in air flow deflector portion regulates described first nozzle section each described
Stream.
The engine jet pipe structure of band flow separation active control function the most according to claim 1, it is characterised in that institute
State the first nozzle section and sequentially form the second air flow deflector portion and the 3rd air flow deflector portion along its first end to the direction of the second end；
Wherein, described air flow regulator includes:
First sensing parts, are arranged on the upper wall surface in described second air flow deflector portion, are used for sensing described second air flow deflector portion
The shear stress values of upper wall surface；
Secondary Flow injection apparatus, is arranged on the upper wall surface in described second air flow deflector portion, for according to described second air flow deflector
The shear stress values of the upper wall surface in portion sprays gas with angle adjustable and adjustable flow along the upper wall surface in described second air flow deflector portion
Stream.
The engine jet pipe structure of band flow separation active control function the most according to claim 2, it is characterised in that institute
Stating the first sensing parts and be provided with multiple, multiple described first sensing parts are equal along the air current flow direction of described first nozzle section
Even layout.
The engine jet pipe structure of band flow separation active control function the most according to claim 2, it is characterised in that institute
The compressor of one end and electromotor of stating Secondary Flow injection apparatus is connected, and the other end of described Secondary Flow injection apparatus is connected to institute
State the upper wall surface in the second air flow deflector portion.
The engine jet pipe structure of band flow separation active control function the most according to claim 2, it is characterised in that institute
State air flow regulator also to include:
Second sensing parts, are arranged on the lower wall surface in described 3rd air flow deflector portion, are used for sensing described 3rd air flow deflector portion
The shear stress values of lower wall surface；
Exhaust apparatus, is arranged on the lower wall surface in described 3rd air flow deflector portion, for according under described 3rd air flow deflector portion
The shear stress values of wall will be located in the fraction of the lower wall surface in described 3rd air flow deflector portion and discharges with adjustable flow.
The engine jet pipe structure of band flow separation active control function the most according to claim 5, it is characterised in that institute
Stating the second sensing parts and be provided with multiple, multiple described second sensing parts are equal along the air current flow direction of described first nozzle section
Even layout.
The engine jet pipe structure of band flow separation active control function the most according to claim 5, it is characterised in that institute
State air flow regulator also to include:
Feedback system, respectively with described first sensing parts and described second sensing parts and described Secondary Flow injection apparatus and
Described exhaust apparatus connects；
Described feedback system controls described Secondary Flow for the shear stress values of the upper wall surface according to described second air flow deflector portion
The spray angle of injection apparatus and injection flow；And
Described feedback system controls described aerofluxus dress for the shear stress values of the lower wall surface according to described 3rd air flow deflector portion
The extraction flow put.
The engine jet pipe structure of band flow separation active control function the most according to claim 1, it is characterised in that institute
The engine jet pipe structure stating band flow separation active control function also includes:
Second nozzle section, described second nozzle section is serpentine, the first end of described second nozzle section have with described in electromotor
The air inlet that high-temperature turbine outlet connects, the second end of described second nozzle section is connected to the first end of described first nozzle section
Described second nozzle section and described first nozzle section sequentially form the first gas along described air inlet to the direction of described air vent
Stream deflector, the second air flow deflector portion and the 3rd air flow deflector portion.
The engine jet pipe structure of band flow separation active control function the most according to claim 8, it is characterised in that institute
Stating the lower wall surface in the second air flow deflector portion and the common tangent of the upper wall surface in described 3rd air flow deflector portion, to cross described air inlet transversal
The minimum point in face.
The engine jet pipe structure of band flow separation active control function the most according to claim 9, it is characterised in that
The length ratio of the axis direction that described second nozzle section exports along described high-temperature turbine with described first nozzle section is 2: 3 to 2:
Between 5 and the ratio of length sum and the maximum gauge of described second nozzle section of described second nozzle section and described first nozzle section
Less than 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201610378236.8A CN106089488A (en) | 2016-05-30 | 2016-05-30 | A kind of engine jet pipe structure of band flow separation active control function |
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| CN201610378236.8A CN106089488A (en) | 2016-05-30 | 2016-05-30 | A kind of engine jet pipe structure of band flow separation active control function |
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| CN110327575A (en) * | 2019-07-17 | 2019-10-15 | 三一汽车制造有限公司 | The control method and system of fire monitor, fire fighting truck and computer readable storage medium |
| CN110339514A (en) * | 2019-07-17 | 2019-10-18 | 三一汽车制造有限公司 | The control method and system of fire fighting truck, fire fighting truck and computer readable storage medium |
| CN112485012A (en) * | 2020-11-13 | 2021-03-12 | 东北大学 | Solid rocket engine experiment table and stress testing method |
| CN114776461A (en) * | 2022-03-25 | 2022-07-22 | 中国民用航空飞行学院 | S-shaped spray pipe for aircraft engine and design method thereof |
| CN114872908A (en) * | 2022-06-08 | 2022-08-09 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN114954964A (en) * | 2022-06-08 | 2022-08-30 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
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| CN110327575A (en) * | 2019-07-17 | 2019-10-15 | 三一汽车制造有限公司 | The control method and system of fire monitor, fire fighting truck and computer readable storage medium |
| CN110339514A (en) * | 2019-07-17 | 2019-10-18 | 三一汽车制造有限公司 | The control method and system of fire fighting truck, fire fighting truck and computer readable storage medium |
| WO2021008097A1 (en) * | 2019-07-17 | 2021-01-21 | 三一汽车制造有限公司 | Control method and system for fire monitor, fire fighting truck, and computer-readable storage medium |
| WO2021008096A1 (en) * | 2019-07-17 | 2021-01-21 | 三一汽车制造有限公司 | Control method and system for firefighting truck, firefighting truck and computer-readable storage medium |
| CN110339514B (en) * | 2019-07-17 | 2021-06-11 | 三一汽车制造有限公司 | Fire fighting truck control method and system, fire fighting truck and computer readable storage medium |
| CN112485012A (en) * | 2020-11-13 | 2021-03-12 | 东北大学 | Solid rocket engine experiment table and stress testing method |
| CN114776461A (en) * | 2022-03-25 | 2022-07-22 | 中国民用航空飞行学院 | S-shaped spray pipe for aircraft engine and design method thereof |
| CN114872908A (en) * | 2022-06-08 | 2022-08-09 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN114954964A (en) * | 2022-06-08 | 2022-08-30 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN114872908B (en) * | 2022-06-08 | 2024-03-26 | 中国航空发动机研究院 | Jet pipe device and aeroengine |
| CN114954964B (en) * | 2022-06-08 | 2024-04-16 | 中国航空发动机研究院 | Jet pipe device and aeroengine |
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Application publication date: 20161109 |