CN206874366U - Circulate aero-engine in double combustion chamber - Google Patents
Circulate aero-engine in double combustion chamber Download PDFInfo
- Publication number
- CN206874366U CN206874366U CN201720559972.3U CN201720559972U CN206874366U CN 206874366 U CN206874366 U CN 206874366U CN 201720559972 U CN201720559972 U CN 201720559972U CN 206874366 U CN206874366 U CN 206874366U
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- Prior art keywords
- combustion chamber
- pressure compressor
- turbine
- engine
- aero
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 44
- 238000005192 partition Methods 0.000 claims abstract description 10
- 239000000446 fuel Substances 0.000 claims abstract description 4
- 239000002737 fuel gas Substances 0.000 abstract description 14
- 239000000463 material Substances 0.000 abstract description 5
- 239000000567 combustion gas Substances 0.000 abstract description 4
- 238000002347 injection Methods 0.000 abstract description 4
- 239000007924 injection Substances 0.000 abstract description 4
- 238000010276 construction Methods 0.000 abstract description 3
- 239000007789 gas Substances 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model proposes a kind of double combustion chamber to circulate aero-engine, including housing, casing center sets main shaft, it is connected with fan, low-pressure compressor, high-pressure compressor and turbine on main shaft in turn, fan rear portion sets partition wall that gas channel is divided into main duct and by-pass air duct, fuel nozzle is set to form combustion chamber between high-pressure compressor and turbine, switchable valve is provided with partition wall between the low-pressure compressor and high-pressure compressor, the combustion chamber is divided into inner combustion chamber and exterior combustion chamber.The utility model exterior combustion chamber greatly improves fuel gas temperature to increase combustion gas interior energy, thrust when increase fuel gas injection speed is to improve supersonic flight because no longer can be limited without turbine structure by turbine material high-temperature stability.Between low-pressure compressor and high-pressure compressor set valve opening, reach change provided with internal duct and external duct than purpose, it is simple in construction, again can be to bypass ratio linear regulation.
Description
Technical field
The utility model belongs to aero-engine field of structural design, more particularly to a kind of double combustion chamber circulation aeroplane engine
Machine.
Background technology
Aero-engine, the power needed for flight is provided for airborne vehicle, as the heart of aircraft, it directly affects aircraft
Performance, reliability and economy, it is the important embodiment of a national science and technology, industry and military capability of the country.Existing change circulation is started
Machine, the high-temperature fuel gas through combustion chambers burn expansion promote high and low pressure turbine to drive the internal bypass air compressed action of compressor,
Injection forms thrust backward at a high speed simultaneously.Fuel gas temperature will be improved by improving high-temperature fuel gas jet thrust, that is, improve whirlpool
Temperature before wheel, if there is such a defect using existing design：Because high-temperature fuel gas is while turbine rotation is promoted
Can be by turbine-heating to very high temperature, the existing metal material resistance to elevated temperatures for making turbine is limited, although
Through reducing turbine temperature using measures such as air coolings, but it is very limited to improving fuel gas temperature.Turbine metal so in existing design
The resistance to elevated temperatures of material limits the raising of fuel gas temperature and then the thrust to turbojet produces restriction.
Utility model content
The utility model is restricted for the raising that existing design has fuel gas temperature by turbine material resistance to elevated temperatures,
The shortcomings that being difficult to greatly improve engine efficiency, propose a kind of double combustion chamber's circulation aero-engine.
In order to achieve the above object, the technical solution adopted in the utility model is：
Aero-engine, including housing are circulated in a kind of double combustion chamber, and casing center sets main shaft, is connected with turn on main shaft
Fan, low-pressure compressor, high-pressure compressor and turbine, fan rear portion set partition wall that gas channel is divided into main duct and outer
Duct, set fuel nozzle to form combustion chamber between high-pressure compressor and turbine, the low-pressure compressor and high-pressure compressor it
Between partition wall on be provided with switchable valve, the combustion chamber is divided into inner combustion chamber and exterior combustion chamber.
Preferably, the turbine is multistage counter rotating turbine.
Preferably, the valve includes bullet, taper carries outer sheath and is equipped with and can be bored around the conical ring that bullet rotates
Passage is provided with body and conical ring.
Compared with prior art, it is the advantages of the utility model with good effect：
1st, exterior combustion chamber greatly improves because no longer can be limited without turbine structure by turbine material high-temperature stability
Fuel gas temperature increases combustion gas interior energy, thrust when increase fuel gas injection speed is to improve supersonic flight.
2nd, exterior combustion chamber structure simplify can with flexible design shape and position in favor of airplane tail group correction of the flank shape reduce resistance and
Improve stealth.Two combustion chambers are not interfere with each other, and reduce the complexity of single combustion chamber work, reduce aerial flame-out parking
Probability.
The 3rd, valve opening is set between low-pressure compressor and high-pressure compressor, by a cone for equally having corresponding opening
Shape ring adjusts the registration of two openings in the form of rotating, and with the change of this air mass flow for adjusting provided with internal duct and external duct, reaches and changes
Become provided with internal duct and external duct than purpose.It is simple in construction, again can be to bypass ratio linear regulation.
Brief description of the drawings
Fig. 1 is the structural representation of the utility model aero-engine；
Above in each figure：1st, housing；2nd, main shaft；3rd, fan；4th, low-pressure compressor；5th, high-pressure compressor；6th, it is multistage to turning
Turbine；7th, partition wall；8th, main duct；9th, by-pass air duct；10th, valve；11st, inner combustion chamber；12nd, exterior combustion chamber.
Embodiment
In order to be better understood from the utility model, illustrate with reference to the accompanying drawings and examples.
Embodiment：As shown in figure 1, a kind of double combustion chamber's circulation aero-engine, including housing, casing center set master
Axle, it is connected with fan, low-pressure compressor, high-pressure compressor and multistage counter rotating turbine on main shaft in turn, fan rear portion, which is set, to be separated
Gas channel is divided into main duct and by-pass air duct by wall, sets fuel nozzle to form combustion chamber between high-pressure compressor and turbine,
Switchable valve is provided with partition wall between the low-pressure compressor and high-pressure compressor, the combustion chamber is divided into internal combustion
Burn room and exterior combustion chamber.The air through overcompression is divided into two by two combustion chambers inside and outside setting, inner combustion chamber is with whirlpool axle
Mode of operation, promote turbine that most interior energies are changed into mechanical energy and drive low-pressure compressor and high-pressure compressor work
Make；Exterior combustion chamber improves combustion gas interior energy expansion work with the pattern of rocket burner nozzle fuel gas temperature as high as possible.External combustion
Burn room and greatly improve fuel gas temperature because no longer can be limited without turbine structure by turbine material high-temperature stability to increase
Combustion gas interior energy, thrust when increase fuel gas injection speed is to improve supersonic flight.Can spirit because exterior combustion chamber structure simplifies
Design shape living and position are so that airplane tail group correction of the flank shape reduces resistance and improves stealth.Two combustion chambers are not interfere with each other, drop
The complexity of low single combustion chamber work, reduce the probability of aerial flame-out parking.
Valve opening is set between low-pressure compressor and high-pressure compressor, and the valve includes bullet, and taper carries outer
Side, which is set with, to be provided with passage on the conical ring that bullet rotates, bullet and conical ring.By adjusting conical ring
The anglec of rotation control the registration of bullet and conical ring upper vent hole to be adjusted into the air capacity of by-pass air duct.When inside and outside
Then by-pass air duct reaches maximum with main duct ratio when passage is completely superposed, suitable for low speed and subsonic speed；When interior exterior open cell is complete
Stagger, during in the absence of intersection, then by-pass air duct reaches minimum with main duct ratio and is applied to supersonic speed.
The conical ring for equally having corresponding opening by one adjusts two registrations being open in the form of rotating, and is adjusted with this
The change of the air mass flow of whole provided with internal duct and external duct, reach change provided with internal duct and external duct than purpose.It is simple in construction, again can be linear to bypass ratio
Regulation.
It is described above, only it is preferred embodiment of the present utility model, is not that other forms are made to the utility model
Limitation, any person skilled in the art is changed or is modified as possibly also with the technology contents of the disclosure above equivalent
The equivalent embodiment of change is applied to other fields, but every without departing from the content of the technical scheme of the utility model, according to this reality
Any simple modification, equivalent variations and the remodeling made with new technical spirit to above example, it is new to still fall within this practicality
The protection domain of type technical scheme.
Claims (3)
1. aero-engine, including housing are circulated in a kind of double combustion chamber, casing center sets main shaft, wind is connected with turn on main shaft
Fan, low-pressure compressor, high-pressure compressor and turbine, fan rear portion set partition wall that gas channel is divided into main duct and outer culvert
Road, fuel nozzle is set to form combustion chamber between high-pressure compressor and turbine, it is characterised in that：The low-pressure compressor and high pressure
Switchable valve is provided with partition wall between compressor, the combustion chamber passes through the Inner Wall of Combustion Chamber parallel to partition wall
It is divided into inner combustion chamber and exterior combustion chamber, exterior combustion chamber is close to partition wall, and inner combustion chamber is close to main shaft.
2. aero-engine is circulated in double combustion chamber according to claim 1, it is characterised in that：The turbine is to be multistage to turning
Turbine.
3. aero-engine is circulated in double combustion chamber according to claim 2, it is characterised in that：The valve includes taper
Body, taper carry outer sheath and are equipped with and can be provided with passage on the conical ring that bullet rotates, bullet and conical ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720559972.3U CN206874366U (en) | 2017-05-19 | 2017-05-19 | Circulate aero-engine in double combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720559972.3U CN206874366U (en) | 2017-05-19 | 2017-05-19 | Circulate aero-engine in double combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206874366U true CN206874366U (en) | 2018-01-12 |
Family
ID=61340391
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720559972.3U Expired - Fee Related CN206874366U (en) | 2017-05-19 | 2017-05-19 | Circulate aero-engine in double combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206874366U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108468602A (en) * | 2018-05-18 | 2018-08-31 | 北京航空航天大学 | A kind of variable Brayton cycle aero-engine of multiple shafting distribution |
| CN108518289A (en) * | 2018-05-17 | 2018-09-11 | 南京航空航天大学 | A kind of blade tip jet is from driving wheel-type Duct-Burning Turbofan |
| CN110985207A (en) * | 2019-12-30 | 2020-04-10 | 绵阳小巨人动力设备有限公司 | Miniature double-combustion-chamber variable-circulation turbojet engine |
| CN111042918A (en) * | 2019-12-31 | 2020-04-21 | 罗辉 | A variable cycle engine |
| WO2020093578A1 (en) * | 2018-11-07 | 2020-05-14 | 中国航发湖南动力机械研究所 | Aircraft and engine thereof |
| CN114576006A (en) * | 2022-03-10 | 2022-06-03 | 中国航空发动机研究院 | Engine and aircraft |
| CN116517688A (en) * | 2023-03-21 | 2023-08-01 | 南京航空航天大学 | Turbine shaft turbojet variable cycle engine scheme |
| US12066027B2 (en) | 2022-08-11 | 2024-08-20 | Next Gen Compression Llc | Variable geometry supersonic compressor |
| US12460651B2 (en) | 2022-08-11 | 2025-11-04 | Next Gen Compression Llc | Method for efficient part load compressor operation |
-
2017
- 2017-05-19 CN CN201720559972.3U patent/CN206874366U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108518289A (en) * | 2018-05-17 | 2018-09-11 | 南京航空航天大学 | A kind of blade tip jet is from driving wheel-type Duct-Burning Turbofan |
| CN108468602A (en) * | 2018-05-18 | 2018-08-31 | 北京航空航天大学 | A kind of variable Brayton cycle aero-engine of multiple shafting distribution |
| WO2020093578A1 (en) * | 2018-11-07 | 2020-05-14 | 中国航发湖南动力机械研究所 | Aircraft and engine thereof |
| CN110985207A (en) * | 2019-12-30 | 2020-04-10 | 绵阳小巨人动力设备有限公司 | Miniature double-combustion-chamber variable-circulation turbojet engine |
| CN111042918A (en) * | 2019-12-31 | 2020-04-21 | 罗辉 | A variable cycle engine |
| CN111042918B (en) * | 2019-12-31 | 2021-08-03 | 罗辉 | A variable cycle engine |
| CN114576006A (en) * | 2022-03-10 | 2022-06-03 | 中国航空发动机研究院 | Engine and aircraft |
| CN114576006B (en) * | 2022-03-10 | 2023-09-22 | 中国航空发动机研究院 | Engine and aircraft |
| US12066027B2 (en) | 2022-08-11 | 2024-08-20 | Next Gen Compression Llc | Variable geometry supersonic compressor |
| US12338829B2 (en) | 2022-08-11 | 2025-06-24 | Next Gen Compression Llc | Variable geometry supersonic compressor |
| US12460651B2 (en) | 2022-08-11 | 2025-11-04 | Next Gen Compression Llc | Method for efficient part load compressor operation |
| CN116517688A (en) * | 2023-03-21 | 2023-08-01 | 南京航空航天大学 | Turbine shaft turbojet variable cycle engine scheme |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180112 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |