CN206280158U - Aircraft engine turbine combustion-supporting system - Google Patents
Aircraft engine turbine combustion-supporting system Download PDFInfo
- Publication number
- CN206280158U CN206280158U CN201621117823.3U CN201621117823U CN206280158U CN 206280158 U CN206280158 U CN 206280158U CN 201621117823 U CN201621117823 U CN 201621117823U CN 206280158 U CN206280158 U CN 206280158U
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- CN
- China
- Prior art keywords
- turbogenerator
- air inlet
- kuppe
- air
- aircraft engine
- 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.)
- Expired - Fee Related
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Abstract
Aircraft engine turbine combustion-supporting system, including a turbogenerator, the turbogenerator inlet end sets a fair water cone, turbogenerator is housed and forms kuppe by the fair water cone after being connected with blower inlet casing, one diversion baffle is set positioned at the tail end of the turbogenerator and coordinates composition air inlet with the kuppe, the air inlet runner that air-flow needed for turbogenerator work is inhaled into and flows through the kuppe and turbogenerator and constitute in the air inlet, for the turbogenerator normal work provides source of the gas；The utility model is due to changing the intake method of turbogenerator; rear end air inlet is changed to by turbogenerator front end airflow; the heat preheating produced using the turbogenerator in the air inlet runner; so as to by the air inlet of the turbogenerator by cold air switch to it is heated after air; air after the heating can significantly improve the combustion rate of aircraft fuel oil, so as to improve power output, increase aircraft thrust 30% to 50%; exhaust emissions is reduced, atmospheric environment is protected.
Description
Technical field
The present invention relates to aircraft engine field, especially a kind of device combustion-supporting for aircraft engine turbine and set
It is standby.
Background technology
The combustion-supporting air of the aircraft turbine engine used by the current mankind is normal temperature air, as height rises, temperature
Turn cold, be exactly cold air on high-altitude, the air that aircraft flies higher to use is colder, and winter is even more so, from turbogenerator
Inlet end enter cold air make turbogenerator spray aero oil cannot fully burn and oil plant combustion not to the utmost.Receive its thrust
To influence, thrust reduces, and waste gas is big for environment pollution, unfavorable environmental protection, thus is necessary to be improved on this basis.
The content of the invention
A kind of aircraft engine turbine is provided and is helped the invention aims to solve the insufficient problem of cold air burning
Combustion system.
The technical proposal of the invention is realized in this way：
A kind of aircraft engine turbine combustion-supporting system, including a turbogenerator are provided, it is characterised in that：The turbine hair
Motivation inlet end sets a fair water cone, and turbogenerator is housed and form kuppe by the fair water cone after being connected with blower inlet casing,
One diversion baffle is set positioned at the tail end of the turbogenerator and coordinates composition air inlet, the propeller for turboprop with the kuppe
The air inlet runner that air-flow needed for machine work is inhaled into and flows through the kuppe and turbogenerator and constitute in the air inlet,
For the turbogenerator normal work provides source of the gas.
Intake method due to changing turbogenerator of the invention, is changed to rear end and enters by turbogenerator front end airflow
Gas, the heat preheating produced using the turbogenerator in the air inlet runner, so as to entering the turbogenerator
Gas by cold air switch to it is heated after air, the air after the heating can significantly improve the combustion rate of aircraft fuel oil so that
Power output is improved, increases aircraft thrust 30% to 50%, and reduce exhaust emissions concentration, protect atmospheric environment.
Preferably, the fair water cone is connected and fixes with blower inlet casing spiral.
Preferably, the profile of the kuppe is adapted with the turbogenerator profile.
Preferably, the steering angle of the diversion baffle is not more than 15 degree, to reduce the negative effect of choked flow.
Great advantage of the invention is to make the fuel oil burning of aircraft turbine engine more abundant.And fuel-efficient increase is pushed away
Power, reduces exhaust emission, more environmentally friendly.
Brief description of the drawings
Fig. 1 is semi-section structural representation of the invention.
Specific embodiment
Embodiments of the invention are illustrated below in conjunction with the accompanying drawings, but are not limited to the present invention：
There is provided a kind of aircraft engine turbine combustion-supporting system, including a turbogenerator 1, the turbogenerator 1 enters
Gas end sets a fair water cone 2, and turbogenerator 1 is housed and form kuppe by the fair water cone 2 after being connected with blower inlet casing 3, position
A diversion baffle 4 is set in the tail end of the turbogenerator 1 and coordinates composition air inlet 5, the turbine hair with the kuppe
Motivation 1 works the air inlet that required air-flow is inhaled into and flows through the kuppe and turbogenerator 1 and constitute in the air inlet 5
Runner 6, for the normal work of the turbogenerator 1 provides source of the gas.
During implementation, the fair water cone 2 is connected and fixes with the spiral of blower inlet casing 3.
During implementation, the profile of the kuppe is adapted with the profile of the turbogenerator 1.
During implementation, the steering angle of the diversion baffle 4 is not more than 15 degree, to reduce the negative effect of choked flow.
The present invention can be not only used for gasoline turbogenerator, it can also be used to Diesel engine, it can also be used to which alcohol is made into fuel
Turbogenerator, and various biological so material turbogenerators are militarily available for operational aircraft to improve its combat capabilities and select.
Although having been shown that detailed embodiment of the invention above, those skilled in the art is without prejudice to of the invention
Under the premise of, part modifications and changes can be carried out；The content referred in described above and accompanying drawing only illustratively illustration, and
It is non-as limitation of the present invention, the aircraft engine turbine combustion-supporting system with above-mentioned technical characteristic each falls within guarantor of the present invention
Shield scope.
Claims (4)
1. a kind of aircraft engine turbine combustion-supporting system, an including turbogenerator, it is characterised in that：The turbogenerator enters
Gas end sets a fair water cone, and turbogenerator is housed and form kuppe by the fair water cone after being connected with blower inlet casing, positioned at institute
The tail end for stating turbogenerator sets a diversion baffle with kuppe cooperation composition air inlet, the turbogenerator work
The air inlet runner that required air-flow is inhaled into and flows through the kuppe and turbogenerator and constitute in the air inlet, is described
Turbogenerator normal work provides source of the gas.
2. aircraft engine turbine combustion-supporting system as claimed in claim 1, it is characterised in that：The excellent fair water cone and blower inlet casing
Spiral is connected and fixed.
3. aircraft engine turbine combustion-supporting system as claimed in claim 1, it is characterised in that：The profile of the kuppe and institute
Turbogenerator profile is stated to be adapted.
4. aircraft engine turbine combustion-supporting system as claimed in claim 1, it is characterised in that：The steering angle of the diversion baffle
No more than 15 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621117823.3U CN206280158U (en) | 2016-10-13 | 2016-10-13 | Aircraft engine turbine combustion-supporting system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621117823.3U CN206280158U (en) | 2016-10-13 | 2016-10-13 | Aircraft engine turbine combustion-supporting system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206280158U true CN206280158U (en) | 2017-06-27 |
Family
ID=59085851
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621117823.3U Expired - Fee Related CN206280158U (en) | 2016-10-13 | 2016-10-13 | Aircraft engine turbine combustion-supporting system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206280158U (en) |
-
2016
- 2016-10-13 CN CN201621117823.3U patent/CN206280158U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| DD01 | Delivery of document by public notice |
Addressee: Chen Cai Document name: payment instructions |
|
| DD01 | Delivery of document by public notice | ||
| DD01 | Delivery of document by public notice |
Addressee: Chen Cai Document name: Notice of termination of patent right |
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| DD01 | Delivery of document by public notice | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170627 Termination date: 20211013 |
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| CF01 | Termination of patent right due to non-payment of annual fee |