CN110259600A - Double outer adaptive cycle engines of culvert - Google Patents
Double outer adaptive cycle engines of culvert Download PDFInfo
- Publication number
- CN110259600A CN110259600A CN201910552287.1A CN201910552287A CN110259600A CN 110259600 A CN110259600 A CN 110259600A CN 201910552287 A CN201910552287 A CN 201910552287A CN 110259600 A CN110259600 A CN 110259600A
- Authority
- CN
- China
- Prior art keywords
- fan
- pressure
- air duct
- pressure turbine
- back segment
- 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
Links
Classifications
-
- 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
- F02K3/06—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 with front fan
-
- 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
- F02K3/075—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 controlling flow ratio between flows
Abstract
The disclosure provides a kind of double outer adaptive cycle engines of culvert, including fan, low-pressure turbine, by-pass air duct jet pipe, main jet pipe and core engine, in which: fan is driven by low-pressure turbine；Fan includes leading portion fan and back segment fan, has the first by-pass air duct after leading portion fan, has the second by-pass air duct and main duct after back segment fan；The configuration of by-pass air duct jet pipe is in the outlet of the first by-pass air duct, and by-pass air duct jet pipe is for being discharged the air-flow for flowing through the first by-pass air duct；The configuration of main jet pipe is in the outlet of main duct, and main jet pipe is for being discharged the air-flow for flowing through the second by-pass air duct and main duct；Core engine includes high-pressure compressor, combustion chamber and high-pressure turbine, and high-pressure compressor is driven by high-pressure turbine, and combustion chamber is between high-pressure compressor and high-pressure turbine.
Description
Technical field
This disclosure relates to aero-engine field, more particularly to a kind of double outer adaptive cycle engines of culvert.
Background technique
At present and following many aircrafts require the more efficient propulsion system of installation capability, have in a variety of state of flights and
The ability of different task is executed under wide scope power regime.This requires engine to have big specific thrust in high-speed flight state,
And low consumption oil cut rate is realized in low-speed condition.Current conventional configuration fanjet does not have this ability.Conventional configuration
Fanjet is under low-speed condition, by reducing fan and core engine rotor speed, while reduce engine flow and
Pressure ratio realizes throttling.This operating mode limits the abundant optimization of specific fuel consumption (SFC) under throttle.The drop of engine flow
It is low to improve spillover resistance and jet pipe afterbody drag, and the reduction of engine pressure ratio reduces the thermal efficiency, this is exactly
Lead to the engine installation increased principal element of oil consumption rate.
Variable cycle engine is started by changing geometry, size or the position of some components of engine come emphasis change
Machine bypass ratio makes performance of the engine under different flight state increase.Engine is climbing, is accelerating and supersonic flight
When bypass ratio reduce, close to turbojet engine performance, to increase thrust；In subsonic flight, increases bypass ratio, pass through promotion
Propulsive efficiency reduces oil consumption rate.But in subsonic flight state, there is no fundamentally solve overflow resistance for variable cycle engine
Power increases and the thermal efficiency reduces problem, so opposite conventional configuration fanjet, the performance of oil consumption rate only slightly improves.
Adaptive cycle engine further extends on the basis of variable cycle engine, proposes variable fan and self-adaptive kernel
Scheming concept.It may be implemented in various state of flights, and the air flow rate and core engine pressure ratio of engine sucking keep permanent substantially
It is fixed.Therefore, adaptive cycle engine can reduce spillage drag simultaneously, improves propulsive efficiency and keep the high thermal efficiency.Mesh
The preceding adaptive engine scheme announced, three ducted fan systems being made up of Flade fan and core engine driving fan
Realize variable fan functionality.Self-adaptive kernel scheming is made of same turbo-driven leading portion compressor and back segment compressor.Leading portion
There is one section of duct parallel with back segment compressor after compressor, by controlling the switch in back segment compressor channel, realizes core engine
The control of pressure ratio.Although the program can be realized adaptive circulatory function, but bring weight increase, structure design and mechanism
Adjust complicated problem.
Summary of the invention
In order to solve at least one above-mentioned technical problem, the disclosure provides a kind of double outer adaptive cycle engines of culvert, main
Engine self-adaptive circulatory function is realized with relatively simple configuration for variable fan system and variable core engine.It is logical
Cross following technical scheme realization:
According to one aspect of the disclosure, double outer adaptive cycle engines of culvert, including fan, low-pressure turbine, by-pass air duct
Jet pipe, main jet pipe and core engine, in which: fan is driven by low-pressure turbine；Fan includes leading portion fan and back segment fan, leading portion wind
There is the first by-pass air duct after fan, there is the second by-pass air duct and main duct after back segment fan；The configuration of by-pass air duct jet pipe is contained outside first
The outlet in road, by-pass air duct jet pipe is for being discharged the air-flow for flowing through the first by-pass air duct；Main jet pipe is configured in the outlet of main duct, main jet
Pipe is for being discharged the air-flow for flowing through the second by-pass air duct and main duct；Core engine includes high-pressure compressor, combustion chamber and high-pressure turbine,
High-pressure compressor is driven by high-pressure turbine, and combustion chamber is between high-pressure compressor and high-pressure turbine.
According at least one embodiment of the disclosure, mode switching valve, mode switching valve are provided in the first by-pass air duct
For controlling the on and off of the first by-pass air duct.
According at least one embodiment of the disclosure, the rear duct injection of variable area is provided in the second by-pass air duct
Device flows through the air-flow of the second by-pass air duct and the stream pressure of low-pressure turbine exit by adjusting the area of rear culvert channel injector
Matching.
According at least one embodiment of the disclosure, the throat area of main jet pipe can be adjusted, by adjusting main jet pipe
Throat area, the back pressure of low-pressure turbine can be controlled, and then adjust the flow of fan.
According at least one embodiment of the disclosure, the import of back segment fan is configured with the adjustable guiding of back segment fan inlet
Blade, back segment fan inlet variable vane is for adjusting the air flow rate for entering back segment fan.
According at least one embodiment of the disclosure, the import of high-pressure turbine is configured with the adjustable guiding of high-pressure turbine import
Device, for adjusting the flow and pressure of core engine.
According at least one embodiment of the disclosure, high-pressure compressor includes the adjustable directing vane of high-pressure compressor import
Piece, high-pressure compressor import variable vane is for adjusting air flow rate.
According at least one embodiment of the disclosure, high-pressure compressor includes the stator blade of multistage adjustable angle, is led to
Cross airflow stability of the angle holding high-pressure compressor for adjusting stator blades at different levels under multimode.
According at least one embodiment of the disclosure, leading portion fan is two-stage fan, and back segment fan is level-one fan.
According at least one embodiment of the disclosure, leading portion fan is level-one fan, and back segment fan is two-stage fan.
According to another aspect of the present disclosure, above-mentioned double outer working methods for containing adaptive cycle engine include following step
It is rapid:
When aircraft is in supersonic cruising state, engine is worked with small bypass ratio mode, is closed in the first by-pass air duct
Mode switching valve, open back segment fan inlet variable vane, make air-flow after leading portion fan compression, fully enter back segment
Fan；The stator blade and the adjustable guider of high-pressure turbine import for opening high-pressure compressor import, make air-flow keep big flow stream
Through core engine；The throat area for adjusting main jet pipe, controls the back pressure of low-pressure turbine；The area for adjusting rear culvert channel injector makes the
Air-flow in two by-pass air ducts is matched with the stream pressure of low-pressure turbine exit, and engine is with high specific thrust work status.
When aircraft is in subsonic speed cruising condition, engine power state is reduced, and is converted to greatly by small bypass ratio mode
Bypass ratio mode opens mode switching valve, turns down back segment fan inlet variable vane, to increase the first by-pass air duct and back segment
The air flow rate ratio of fan；The stator blade and the adjustable guider of high-pressure turbine import of high-pressure compressor import are turned down, to reduce
The air flow rate of core engine, while keep constant high-pressure compressor pressure ratio；Adjust the angle of high-pressure compressor stator blades at different levels
Degree, to keep the airflow stability of high-pressure compressor；Amplify the throat area of main jet pipe, reduces low-pressure turbine back pressure, make fan
Air flow rate keep constant；The area for adjusting rear culvert channel injector, makes the air-flow and low-pressure turbine exit in the second by-pass air duct
Stream pressure matching, engine is with low consumption oil cut rate work status.
Detailed description of the invention
Attached drawing shows the illustrative embodiments of the disclosure, and it is bright together for explaining the principles of this disclosure,
Which includes these attached drawings to provide further understanding of the disclosure, and attached drawing is included in the description and constitutes this
Part of specification.
Fig. 1 is double outer section view signals for containing adaptive cycle engine according at least one embodiment of the disclosure
Figure.
Fig. 2 is illustrated according to second of configuration scheme of the variable fan system of at least one embodiment of the disclosure
Figure.
Specific embodiment
The disclosure is described in further detail with embodiment with reference to the accompanying drawing.It is understood that this place
The specific embodiment of description is only used for explaining related content, rather than the restriction to the disclosure.It also should be noted that being
Convenient for description, part relevant to the disclosure is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the disclosure can
To be combined with each other.The disclosure is described in detail below with reference to the accompanying drawings and in conjunction with embodiment.
Aircraft has different requirements under different flight state, to the performance of engine, and the disclosure provides a kind of pair of outer culvert certainly
Cycle engine is adapted to, by adjusting the adjustable mechanism in variable fan system and self-adaptive kernel scheming, Lai Shixian flow, pressure ratio
With the automatic adjusument of bypass ratio.
In an embodiment of the disclosure, as shown in Figure 1, it is double it is outer contain adaptive cycle engine include fan 1, it is low
Pressure turbine 5, by-pass air duct jet pipe 7, main jet pipe 8 and core engine, fan 1 are driven by low-pressure turbine 5, and air-flow is from 7 He of by-pass air duct jet pipe
Main jet pipe 8 is discharged, and core engine includes high-pressure compressor 2, combustion chamber 3 and high-pressure turbine 4, and high-pressure compressor 2 is driven by high-pressure turbine 4
Dynamic, combustion chamber 3 is between high-pressure compressor 2 and high-pressure turbine 4.In addition, engine further includes configuration at 5 rear of low-pressure turbine
After-burner 6.
Specifically, fan 1 includes two sections of front and back, i.e. leading portion fan 11 and back segment fan 14.Leading portion fan 11 is two-stage wind
Fan, back segment fan 14 are level-one fan.There is the first by-pass air duct, the outlet of the first by-pass air duct is provided with outer culvert after leading portion fan 11
Road jet pipe 7.When engine operation, air-flow 101 is divided into outside first after the compression of leading portion fan 11 and contains air-flow 102 and back segment fan
Air-flow 103.After culvert air-flow 102 enters the first by-pass air duct outside first, it is discharged from by-pass air duct jet pipe 7.Back segment fan airstream 103 then into
Enter back segment fan 14 to continue to be pressurized.There is the second by-pass air duct and main duct after back segment fan 14.After back segment fan airstream 103 passes through
It after section fan 14 compresses, is split into outside second and contains air-flow 105 and core air-flow 106, and have respectively entered the second by-pass air duct and interior
Duct.After culvert air-flow 105 flows through the second by-pass air duct outside second, a part enters the wall chamber of main jet pipe 8, another portion as cooling air
Divide and mixed with core flow 106, into after-burner 6, finally enters further expansion discharge in main jet pipe 8.
In an embodiment of the disclosure, the entrance of the first by-pass air duct is provided with mode switching valve 12, passes through mode
Switching valve 12 controls the on and off of the first by-pass air duct.
In an embodiment of the disclosure, the backend configuration of the second by-pass air duct has the adjustable rear culvert channel injector of area
16, by adjusting the area of rear culvert channel injector 16, the air-flow of the second by-pass air duct and the gas of the outlet of low-pressure turbine 5 can be flowed through
The pressure match of stream.By adjusting pressure, cooperates the air flow rate of fan 1 to adjust, can satisfy aircraft in different flight state
Under for engine performance difference require.
In an embodiment of the disclosure, the throat area of main jet pipe 8 is adjustable, by adjusting main jet pipe 8
Throat area, can control the back pressure of low-pressure turbine 5, to achieve the effect that adjust 1 air flow rate of fan.For example, working as aircraft
When in subsonic speed cruising condition, to reduce by 5 back pressure of low-pressure turbine, and then it can be made by the throat area of amplification main jet pipe 8
The air flow rate (opposite supersonic cruising state) of fan 1 is kept constant.
In an embodiment of the disclosure, the import of back segment fan 14 is configured with the adjustable directing vane of back segment fan inlet
The angle of piece 13, back segment fan inlet variable vane 13 is adjustable, by adjusting the adjustable directing vane of back segment fan inlet
The angle of piece 13 can control the air flow rate for entering back segment fan 14.
In an embodiment of the disclosure, the import of high-pressure turbine 4 is configured with the guider 22 of adjustable angle, passes through
The angle of high-pressure turbine import is adjustable guider 22 adjusts the flow and pressure of core engine.
In an embodiment of the disclosure, high-pressure compressor 2 includes high-pressure compressor import variable vane 21,
Its import that high-pressure compressor 2 is set, for adjusting air flow rate.Core flow 106 is through the adjustable guiding of high-pressure compressor import
High-pressure compressor 2 is entered after blade 21, after the compression of high-pressure compressor 2, is burnt into combustion chamber 3, is discharged from combustion chamber 3
After further flow through the adjustable guider 22 of high-pressure turbine import and enter high-pressure turbine 4 and low-pressure turbine 5, and expansion work.
Angle by adjusting high-pressure compressor import variable vane 21 and the adjustable guider 22 of high-pressure turbine import can control
The flow and pressure of core engine.For example, it is adjustable that high-pressure compressor import can be turned down when aircraft is in subsonic speed cruising condition
Guide vane 21 and the adjustable guider 22 of high-pressure turbine import, to reduce the flow of core air-flow 106, while making high-pressure compressor
2 pressure ratios (opposite supersonic cruising state) are kept constant.
Preferably, in order to guarantee airflow stability of the high-pressure compressor 2 under multimode, high-pressure compressor is provided with multistage
The stator blade of adjustable angle.It can keep high-pressure compressor 2 under multimode by adjusting the angle of stator blades at different levels
Airflow stability.
In an embodiment of the disclosure, when aircraft is in supersonic cruising state, double outer adaptive circulations of culvert
Engine can realize the automatic adjusument to flow, pressure ratio and bypass ratio: supersonic cruising state by following working method
When, engine is worked with small bypass ratio mode；Close pattern switching valve 12 opens back segment fan inlet variable vane 13,
Air-flow 101 fully enters back segment fan 14 after the compression of leading portion fan 11；Open high-pressure compressor import variable vane 21
With the adjustable guider 22 of high-pressure turbine import, core air-flow 106 is made to keep big flow.Rule of thumb or actual needs, adjustment are led
8 throat opening area of jet pipe is at appropriate location, keeps the appropriate back pressure of low-pressure turbine 5.The area of rear culvert channel injector 16 is adjusted,
Guarantee to contain air-flow 105 and 5 exit flow pressure match of low-pressure turbine outside second.Engine is with high specific thrust work status.
When aircraft is in subsonic speed cruising condition, double outer adaptive cycle engines of culvert can be realized by following steps
Automatic adjusument to flow, pressure ratio and bypass ratio: when subsonic speed cruising condition, turbine entrance temperature temperature is reduced, and is started simultaneously
Machine is converted to big bypass ratio mode by small bypass ratio mode.Open mode switching valve 12, back segment fan inlet variable vane
13 turn down, and increase the flow-rate ratio for containing air-flow 102 and back segment fan airstream 103 outside first.Turn down that high-pressure compressor import is adjustable to be led
To blade 21 and the adjustable guider 22 of high-pressure turbine import, to reduce 106 flow of core air-flow, while making high-pressure compressor pressure ratio
(opposite supersonic cruising state) is kept constant.The angle of corresponding adjustment remaining stator blade at different levels of high-pressure compressor 2, to keep
2 airflow stability of high-pressure compressor.Amplify the throat area of main jet pipe 8, reduces by 5 back pressure of low-pressure turbine, make 1 air flow rate of fan
(opposite supersonic cruising state) is kept constant.Adjust rear culvert channel injector 16 area, guarantee second outside contain air-flow 105 with it is low
The stream pressure matching for pressing turbine 5 to export.In subsonic speed cruising condition, double outer adaptive cycle engines of culvert realize high air inlet
Flow, high overall pressure tatio and big bypass ratio, installed specific fuel consumption are greatly reduced.
In an embodiment of the disclosure, fan 1 can also have second of configuration scheme, i.e., by leading portion fan 11
Level-one is changed to by two-stage, back segment fan 14 is changed to two-stage by level-one, and other structures, which are not done, to be changed.Under different flight state, start
Machine is same as above the adaptive regulation method of flow, pressure ratio and bypass ratio.As shown in Fig. 2, fan system 1 is still by low-pressure turbine 5
Driving, the first by-pass air duct are still arranged after leading portion fan 11, and the entrance of the first by-pass air duct, air-flow is arranged in mode switching valve 12
101 after the compression of leading portion fan 11, are divided into outside first and contain air-flow 102 and back segment fan airstream 103, and back segment fan airstream 103 flows
Enter back segment fan 14 after back segment fan inlet variable vane 13 to continue to be pressurized；Contain outside setting second after back segment fan 14
Road and main duct, back segment fan airstream 103 are split into after the compression of back segment fan 14 into culvert outside the second of the second by-pass air duct
Air-flow 105, and flow through the core air-flow 106 that high-pressure compressor import variable vane 21 enters core engine.
Double outer adaptive cycle engines of culvert of the disclosure, it is simpler in terms of structure is designed with regulative mode, pass through
The structure of fan and core engine is improved, so that fan system in pressure change, is able to maintain fan airstream flow base
This is constant, is able to maintain pressure ratio in core engine changes in flow rate and is basically unchanged, to realize the adaptive of flow, pressure ratio and bypass ratio
It should adjust, aircraft can be taken into account to the high thrust of high engine speeds and the two different performance requirements of low speed low consumption oil cut rate.
It will be understood by those of skill in the art that above embodiment is used for the purpose of clearly demonstrating the disclosure, and simultaneously
Non- be defined to the scope of the present disclosure.For those skilled in the art, may be used also on the basis of disclosed above
To make other variations or modification, and these variations or modification are still in the scope of the present disclosure.
Claims (10)
1. a kind of double outer adaptive cycle engines of culvert, including fan, low-pressure turbine, by-pass air duct jet pipe, main jet pipe and core engine,
Wherein:
The fan is driven by low-pressure turbine；
The fan includes leading portion fan and back segment fan, has the first by-pass air duct, the back segment fan after the leading portion fan
There is the second by-pass air duct and main duct afterwards；
In the outlet of first by-pass air duct, the by-pass air duct jet pipe flows through described for being discharged for by-pass air duct jet pipe configuration
The air-flow of one by-pass air duct；
In the outlet of the main duct, the main jet pipe flows through second by-pass air duct and interior for being discharged for main jet pipe configuration
The air-flow of duct；
The core engine includes high-pressure compressor, combustion chamber and high-pressure turbine, and the high-pressure compressor is driven by high-pressure turbine, institute
Combustion chamber is stated between the high-pressure compressor and high-pressure turbine.
2. engine according to claim 1, which is characterized in that
Mode switching valve is provided in first by-pass air duct, the mode switching valve is for controlling opening for first by-pass air duct
The pass and.
3. engine according to claim 1, which is characterized in that
The rear culvert channel injector of variable area is provided in second by-pass air duct, by adjusting the face of the rear culvert channel injector
Product, the air-flow for flowing through second by-pass air duct are matched with the stream pressure of the low-pressure turbine exit.
4. engine according to claim 1, which is characterized in that
The throat area of the main jet pipe can be adjusted.
5. engine according to claim 1, which is characterized in that
The import of the back segment fan is configured with back segment fan inlet variable vane, the adjustable guiding of back segment fan inlet
Blade is for adjusting the air flow rate for entering the back segment fan.
6. engine according to claim 1, which is characterized in that
The import of the high-pressure turbine is configured with the adjustable guider of high-pressure turbine import.
7. engine according to claim 1, which is characterized in that
The high-pressure compressor includes the stator blade of multistage adjustable angle.
8. engine according to any one of claim 1 to 7, which is characterized in that
The leading portion fan is two-stage fan, and the back segment fan is level-one fan.
9. engine according to any one of claim 1 to 7, which is characterized in that
The leading portion fan is level-one fan, and the back segment fan is two-stage fan.
10. a kind of double outer working methods for containing adaptive cycle engine according to any one of claim 1 to 9,
It is characterized in that, comprising the following steps:
When aircraft is in supersonic cruising state, the engine is worked with small bypass ratio mode, is closed in the first by-pass air duct
Mode switching valve, open back segment fan inlet variable vane, make air-flow after leading portion fan compression, fully enter back segment
Fan；The stator blade and the adjustable guider of high-pressure turbine import for opening high-pressure compressor import, make air-flow keep big flow stream
Through core engine；The throat area for adjusting main jet pipe, controls the back pressure of low-pressure turbine；The area for adjusting rear culvert channel injector makes the
Air-flow in two by-pass air ducts is matched with the stream pressure of low-pressure turbine exit, and the engine is with high specific thrust work status.
When aircraft is in subsonic speed cruising condition, the engine power state is reduced, and is converted to greatly by small bypass ratio mode
Bypass ratio mode opens the mode switching valve, turns down the back segment fan inlet variable vane, is contained outside first with increasing
The air flow rate ratio in road and back segment fan；Turn down the stator blade and the adjustable guiding of high-pressure turbine import of high-pressure compressor import
Device to reduce the air flow rate of core engine, while keeps constant high-pressure compressor pressure ratio；Adjust high-pressure compressor stators at different levels
The angle of blade, to keep the airflow stability of the high-pressure compressor；Amplify the throat area of the main jet pipe, described in reduction
Low-pressure turbine back pressure keeps constant the air flow rate of fan；The area for adjusting rear culvert channel injector, makes in the second by-pass air duct
Air-flow is matched with the stream pressure of low-pressure turbine exit, and the engine is with low consumption oil cut rate work status.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910552287.1A CN110259600A (en) | 2019-06-25 | 2019-06-25 | Double outer adaptive cycle engines of culvert |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910552287.1A CN110259600A (en) | 2019-06-25 | 2019-06-25 | Double outer adaptive cycle engines of culvert |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110259600A true CN110259600A (en) | 2019-09-20 |
Family
ID=67921164
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910552287.1A Pending CN110259600A (en) | 2019-06-25 | 2019-06-25 | Double outer adaptive cycle engines of culvert |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110259600A (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111042918A (en) * | 2019-12-31 | 2020-04-21 | 罗辉 | Variable cycle engine |
| CN112727635A (en) * | 2020-12-31 | 2021-04-30 | 中国航空发动机研究院 | Double-culvert engine |
| CN113283021A (en) * | 2021-03-15 | 2021-08-20 | 中国航发沈阳发动机研究所 | Method for determining adjustable area of rear duct ejector |
| CN113323769A (en) * | 2021-06-07 | 2021-08-31 | 北京航空航天大学 | Variable cycle engine configuration based on multi-duct intake interstage combustion chamber |
| CN113847163A (en) * | 2021-10-25 | 2021-12-28 | 中国航发沈阳发动机研究所 | Jet system of outer duct of fan of aircraft engine |
| CN113864082A (en) * | 2021-09-13 | 2021-12-31 | 上海新云彩航空科技有限责任公司 | Aviation jet engine |
| CN113864083A (en) * | 2021-10-12 | 2021-12-31 | 中国航发湖南动力机械研究所 | Novel variable-cycle gas turbine engine |
| CN114320660A (en) * | 2022-01-05 | 2022-04-12 | 北京理工大学 | Wide-speed-range ramjet engine based on axial ultrasonic incoming flow variable geometry fan |
| CN114483304A (en) * | 2022-01-29 | 2022-05-13 | 中国航发湖南动力机械研究所 | Novel variable-circulation turboshaft engine structure |
| CN114542518A (en) * | 2022-02-23 | 2022-05-27 | 中国航发沈阳发动机研究所 | Double-duct compressor |
| CN114856856A (en) * | 2022-05-06 | 2022-08-05 | 中国科学院工程热物理研究所 | High-lift-limit low-oil-consumption medium bypass ratio variable cycle engine |
| CN114856818A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Variable cycle engine core machine with variable working mode |
| CN114856855A (en) * | 2022-05-06 | 2022-08-05 | 中国科学院工程热物理研究所 | Wide-speed-range variable-cycle engine based on inter-stage combustion chamber driving low-pressure turbine rotor |
| CN114876665A (en) * | 2022-05-13 | 2022-08-09 | 中国航空发动机研究院 | Variable cycle engine compression system |
| CN116201656A (en) * | 2023-03-10 | 2023-06-02 | 中国科学院工程热物理研究所 | Turbojet propulsion power system suitable for hypersonic cruising of unmanned aerial vehicle |
| CN114856856B (en) * | 2022-05-06 | 2024-04-30 | 中国科学院工程热物理研究所 | High-rise-limit low-oil-consumption medium-bypass-ratio variable-cycle engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3182898A (en) * | 1962-05-31 | 1965-05-11 | Rolls Royce | Axial flow compressor or fan and gas turbine engine provided therewith |
| US3886737A (en) * | 1972-08-22 | 1975-06-03 | Mtu Muenchen Gmbh | Turbojet engines of multi-shaft and multi-flow construction |
| GB1493049A (en) * | 1974-02-25 | 1977-11-23 | Gen Electric | Turbofan engine |
| US5806303A (en) * | 1996-03-29 | 1998-09-15 | General Electric Company | Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle |
| CN101021181A (en) * | 2006-02-13 | 2007-08-22 | 通用电气公司 | Double bypass turbofan |
| RU2637153C1 (en) * | 2016-07-04 | 2017-11-30 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Method of operation of three-circuit turbojet engine |
-
2019
- 2019-06-25 CN CN201910552287.1A patent/CN110259600A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3182898A (en) * | 1962-05-31 | 1965-05-11 | Rolls Royce | Axial flow compressor or fan and gas turbine engine provided therewith |
| US3886737A (en) * | 1972-08-22 | 1975-06-03 | Mtu Muenchen Gmbh | Turbojet engines of multi-shaft and multi-flow construction |
| GB1493049A (en) * | 1974-02-25 | 1977-11-23 | Gen Electric | Turbofan engine |
| US5806303A (en) * | 1996-03-29 | 1998-09-15 | General Electric Company | Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle |
| CN101021181A (en) * | 2006-02-13 | 2007-08-22 | 通用电气公司 | Double bypass turbofan |
| RU2637153C1 (en) * | 2016-07-04 | 2017-11-30 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Method of operation of three-circuit turbojet engine |
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111042918A (en) * | 2019-12-31 | 2020-04-21 | 罗辉 | Variable cycle engine |
| CN112727635B (en) * | 2020-12-31 | 2022-04-26 | 中国航空发动机研究院 | Double-culvert engine |
| CN112727635A (en) * | 2020-12-31 | 2021-04-30 | 中国航空发动机研究院 | Double-culvert engine |
| CN113283021B (en) * | 2021-03-15 | 2023-07-21 | 中国航发沈阳发动机研究所 | Method for determining adjustable area of rear duct ejector |
| CN113283021A (en) * | 2021-03-15 | 2021-08-20 | 中国航发沈阳发动机研究所 | Method for determining adjustable area of rear duct ejector |
| CN114776473A (en) * | 2021-06-07 | 2022-07-22 | 北京航空航天大学 | Variable cycle engine configuration based on multi-duct intake interstage combustion chamber |
| CN114776473B (en) * | 2021-06-07 | 2024-01-19 | 北京航空航天大学 | Variable cycle engine configuration based on multi-duct air inlet interstage combustion chamber |
| CN113323769A (en) * | 2021-06-07 | 2021-08-31 | 北京航空航天大学 | Variable cycle engine configuration based on multi-duct intake interstage combustion chamber |
| CN113864082A (en) * | 2021-09-13 | 2021-12-31 | 上海新云彩航空科技有限责任公司 | Aviation jet engine |
| CN113864082B (en) * | 2021-09-13 | 2022-12-06 | 上海新云彩航空科技有限责任公司 | Aviation jet engine |
| CN113864083A (en) * | 2021-10-12 | 2021-12-31 | 中国航发湖南动力机械研究所 | Novel variable-cycle gas turbine engine |
| CN113847163A (en) * | 2021-10-25 | 2021-12-28 | 中国航发沈阳发动机研究所 | Jet system of outer duct of fan of aircraft engine |
| CN113847163B (en) * | 2021-10-25 | 2024-02-23 | 中国航发沈阳发动机研究所 | Outer duct injection system of aeroengine fan |
| CN114320660A (en) * | 2022-01-05 | 2022-04-12 | 北京理工大学 | Wide-speed-range ramjet engine based on axial ultrasonic incoming flow variable geometry fan |
| CN114320660B (en) * | 2022-01-05 | 2023-02-03 | 北京理工大学 | Wide-speed-range ramjet engine based on axial ultrasonic incoming flow variable geometry fan |
| CN114483304A (en) * | 2022-01-29 | 2022-05-13 | 中国航发湖南动力机械研究所 | Novel variable-circulation turboshaft engine structure |
| CN114483304B (en) * | 2022-01-29 | 2023-09-26 | 中国航发湖南动力机械研究所 | Novel variable circulation turboshaft engine structure |
| CN114542518A (en) * | 2022-02-23 | 2022-05-27 | 中国航发沈阳发动机研究所 | Double-duct compressor |
| CN114856856A (en) * | 2022-05-06 | 2022-08-05 | 中国科学院工程热物理研究所 | High-lift-limit low-oil-consumption medium bypass ratio variable cycle engine |
| CN114856855B (en) * | 2022-05-06 | 2023-08-08 | 中国科学院工程热物理研究所 | Wide-speed-range variable cycle engine for driving low-pressure turbine rotor based on interstage combustion chamber |
| CN114856855A (en) * | 2022-05-06 | 2022-08-05 | 中国科学院工程热物理研究所 | Wide-speed-range variable-cycle engine based on inter-stage combustion chamber driving low-pressure turbine rotor |
| CN114856856B (en) * | 2022-05-06 | 2024-04-30 | 中国科学院工程热物理研究所 | High-rise-limit low-oil-consumption medium-bypass-ratio variable-cycle engine |
| CN114856818A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Variable cycle engine core machine with variable working mode |
| CN114876665A (en) * | 2022-05-13 | 2022-08-09 | 中国航空发动机研究院 | Variable cycle engine compression system |
| CN116201656A (en) * | 2023-03-10 | 2023-06-02 | 中国科学院工程热物理研究所 | Turbojet propulsion power system suitable for hypersonic cruising of unmanned aerial vehicle |
| CN116201656B (en) * | 2023-03-10 | 2023-11-17 | 中国科学院工程热物理研究所 | Turbojet propulsion power system suitable for hypersonic cruising of unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110259600A (en) | Double outer adaptive cycle engines of culvert | |
| JP5571285B2 (en) | Control line control of a compression system with flow recirculation. | |
| US4175384A (en) | Individual bypass injector valves for a double bypass variable cycle turbofan engine | |
| EP1942269B1 (en) | Convertible gas turbine engine | |
| US5184459A (en) | Variable vane valve in a gas turbine | |
| CA2519823C (en) | Methods and apparatus for assembling a gas turbine engine | |
| US10450078B2 (en) | Adaptive aircraft engine and aircraft having an adaptive engine | |
| JP2013506081A (en) | Convertible fan engine | |
| US20110167792A1 (en) | Adaptive engine | |
| US20120124964A1 (en) | Gas turbine engine with improved fuel efficiency | |
| EP2994633B1 (en) | Secondary nozzle for jet engine | |
| US11884414B2 (en) | Supersonic aircraft turbofan engine | |
| CN116201656B (en) | Turbojet propulsion power system suitable for hypersonic cruising of unmanned aerial vehicle | |
| EP0926332A2 (en) | Operating method for a jet engine | |
| US20100089030A1 (en) | Controlling the aerodynamic drag of a gas turbine engine during a shutdown state | |
| RU2637153C1 (en) | Method of operation of three-circuit turbojet engine | |
| CN114856856B (en) | High-rise-limit low-oil-consumption medium-bypass-ratio variable-cycle engine | |
| EP2809936B1 (en) | Gas turbine engine with improved fuel efficiency | |
| RU2675637C1 (en) | Method for operation of three-circuit turbojet engine with afterburner chamber | |
| CN114856856A (en) | High-lift-limit low-oil-consumption medium bypass ratio variable cycle engine | |
| CN115405437A (en) | Variable cycle engine, aircraft and control method of variable cycle engine |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190920 |