CN106555705A - Topping turbine jet engine - Google Patents
Topping turbine jet engine Download PDFInfo
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- CN106555705A CN106555705A CN201510621852.7A CN201510621852A CN106555705A CN 106555705 A CN106555705 A CN 106555705A CN 201510621852 A CN201510621852 A CN 201510621852A CN 106555705 A CN106555705 A CN 106555705A
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- turbine
- combustor
- compressor
- injection duct
- air
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Abstract
Topping turbine jet engine drives turbine method in changing existing turbojet.Turbine is moved on to from behind combustor and (specify combustor jet backward) before combustor.In topping turbine jet engine, injector is constituted by burner (10), De Laval noz(zle) (11) and injection jet pipe (12).The ejector action of injector makes the flow at high speed of air in injection duct (9), promotes the turbine positioned at injection duct (9) inlet end.Turbine rotor (4) is joined together by connection ring (5) and compressor first order rotor (6), compressor main shaft (7), and compressors at different levels and other machinerys work after driving.Compressor provides pressure-air for combustor, maintains combustor and injector work.Turbine can be very good to utilize ram effect at the volley.The air demand of the air inflow and compressor of injection duct to combustor can be adjusted by compressor injection duct combine regulation valve (13).
Description
Technical field
Machinery and technical field of transportation.F01M：General machine or electromotor.
Background technology
At present, it is all of in airborne vehicle（But it is not limited to）Used in all kinds of turbojets in, turbine is all placed in combustor below.The high temperature and high speed gas-driven turbine that combustor is produced rotates at a high speed, then the compressor and other machinerys positioned at combustor head is driven by power transmission shaft by turbine（Such as fan, propeller etc.）Work.Due to the restriction of turbine heat resistance, at combustor exit, fuel gas temperature further can not be improved, and the kinetic energy of combustion gas also further cannot be improved.
The pressure-air that compressor is provided, has suitable one to be intended merely to reduce the gas temperature of combustor exit into combustor.Some pressure-air bypasses combustor supply turbine heat transmission.Reduce the efficiency of electromotor.Although after-burner can utilize this portion gas, the efficiency of after-burner is also not high.
Under the extremities that turbine is widely varied in temperature, stress all the time, its material and manufacturing process are extremely complex, harsh.The manufacturing technology of turbine becomes the bottleneck of modern turbojet development.
The content of the invention
Topping turbine jet engine drives turbine method in changing existing turbojet.So as to change position of the turbine in jet engine.Turbine is moved on to before combustor from behind combustor（Specify combustor jet backward）.
In topping turbine jet engine（Hereinafter referred to as：Preposition whirlpool spray）In, by burner（10）, De Laval noz(zle)（11）With injection jet pipe（12）Composition injector.Using the ejector action of injector, the flow at high speed of air in injection duct (9), and promote positioned at injection duct（9）The turbine of inlet end.The turbine rotor of preposition whirlpool spray（4）With compressor first order rotor（6）It is by connection ring（5）It is connected.Compressor first order rotor（6）By compressor main shaft（7）After driving, compressors at different levels and other machinerys work.Compressor main shaft（7）Using front-end bracket（2）And rear end support（8）It is separately fixed in shell and compressor casing.Meanwhile, nozzle ring（3）And front-end bracket（2）A part.Compressor provides pressure-air for combustor, maintains burning and injector work.
Due to the nozzle ring of preposition whirlpool spray（3）And turbine rotor（4）Positioned at injection duct inlet（1）Position, turbine can be very good to utilize ram effect at the volley.
The turbine of preposition whirlpool spray is in low-temperature working environment all the time, it is not necessary to cool down.Therefore the material manufacture of high-strength light can be utilized.Meanwhile, because the reduction of stator blade and temperature of rotor stress, the thickness of its trailing edge can be made thin thin, be conducive to improving the efficiency of turbine.
Due to without turbine, can further improving the delivery temperature of electromotor, the thrust-weight ratio of electromotor be greatly improved behind combustor.
Preposition whirlpool spray is using single tubular type combustor.Compared with various combustor common at present, single tubular type combustor has the characteristics of volume is big, specific surface area is little.Combustion chambers burn is stable, high combustion efficiency, ignition range width, little flow resistance and simple structure, safe and reliable and life-span length.
Adjustable compressor injection duct combine regulation valve of preposition whirlpool spray（13）, for the working condition of electromotor is highly important.By compressor injection duct combine regulation valve（13）The air demand of the air inflow and compressor of injection duct to combustor can be adjusted.When electromotor remains static ignition trigger, compressor injection duct combine regulation valve（13）It is closed, injection duct inlet（1）Air inflow it is maximum, make topping turbine obtain larger power to drive compressor to work.And maintain electromotor to produce larger thrust.With the raising of movement velocity, ram effect can increase injection duct（9）Air inlet（1）Gas flow and compressor capacity.At this moment compressor injection duct combine regulation valve can be opened（13）, reduce the air demand of injection duct inlet throughput and compressor to combustor.Maintain the work of engine stabilizer.
The turbine of preposition whirlpool spray can also be designed to multistage and multiaxis.It is easily achieved according to existing Machining Technology.
If arranging compressor final stage guider shutoff device in the spray of preposition whirlpool.Use liquid oxygen instead combustion-supporting, in the case of using aerial kerosene, airborne vehicle can be in outer-space flight.Description of the drawings：Figure of description is topping turbine jet engine schematic diagram.
Claims (3)
1. the turbine of topping turbine jet engine is before combustor, not by the direct effect of high-temperature fuel gas.
2. the turbine of topping turbine jet engine is by injection air-flow and punching press air stream drives.
3. electromotor by compressor injection duct combine regulation valve, can adjust the working condition of electromotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510621852.7A CN106555705A (en) | 2015-09-25 | 2015-09-25 | Topping turbine jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510621852.7A CN106555705A (en) | 2015-09-25 | 2015-09-25 | Topping turbine jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106555705A true CN106555705A (en) | 2017-04-05 |
Family
ID=58414501
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510621852.7A Pending CN106555705A (en) | 2015-09-25 | 2015-09-25 | Topping turbine jet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106555705A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113309636A (en) * | 2021-07-01 | 2021-08-27 | 西北工业大学 | Double-duct injection device for aircraft engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2237069A (en) * | 1989-10-20 | 1991-04-24 | Kershaw H A | Gas turbine engine |
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN202001139U (en) * | 2010-08-12 | 2011-10-05 | 靳北彪 | Stamping engine with pneumatic turbine |
| CN103221674A (en) * | 2010-11-23 | 2013-07-24 | 斯奈克玛公司 | Combined turbojet and ramjet engine |
-
2015
- 2015-09-25 CN CN201510621852.7A patent/CN106555705A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2237069A (en) * | 1989-10-20 | 1991-04-24 | Kershaw H A | Gas turbine engine |
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN202001139U (en) * | 2010-08-12 | 2011-10-05 | 靳北彪 | Stamping engine with pneumatic turbine |
| CN103221674A (en) * | 2010-11-23 | 2013-07-24 | 斯奈克玛公司 | Combined turbojet and ramjet engine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113309636A (en) * | 2021-07-01 | 2021-08-27 | 西北工业大学 | Double-duct injection device for aircraft engine |
| CN113309636B (en) * | 2021-07-01 | 2022-07-29 | 西北工业大学 | Double-duct injection device for aircraft engine |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170405 |
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| WD01 | Invention patent application deemed withdrawn after publication |