CN105240159B - A kind of jet engine - Google Patents
A kind of jet engine Download PDFInfo
- Publication number
- CN105240159B CN105240159B CN201510721762.5A CN201510721762A CN105240159B CN 105240159 B CN105240159 B CN 105240159B CN 201510721762 A CN201510721762 A CN 201510721762A CN 105240159 B CN105240159 B CN 105240159B
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- Prior art keywords
- hollow axle
- turbine
- handling system
- electromotor
- main duct
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Abstract
The invention discloses a kind of jet engine, including shell, compressor, combustor, turbine and main duct gas handling system, described main duct gas handling system is made up of the centrifugal impeller in the hollow axle and hollow axle of electromotor, on the hollow axle of the turbine portion at described electromotor rear portion or turbo blade is provided with the gas outlet being connected with space in hollow axle, the present invention had both avoided many of turbofan quickly completely using the by-pass air duct fan mode that main duct gas handling system instead of fanjet and had manufactured and designed a difficult problem, the efficiency high of fanjet is remained again, fuel-efficient advantage, return turbine and drop temperature, and which also has the simple structure of turbojet, the good advantage of high speed performance.
Description
Technical field
The present invention relates to a kind of jet engine.
Background technology
Turbojet is a kind of turbogenerator, and feature is to be completely dependent on combustion gas stream to produce thrust, is typically used as
The power of high-speed aircraft, oil consumption are higher than turbofan, are mainly used in fight, and Concord, such as Concorde.
Turbofan compares turbogenerator, has the advantages that efficiency high, oil consumption be low, flight is just remote,
But while also have the shortcomings that high speed performance not as turbojet, complex structure, design difficulty is big, involve great expense.
The content of the invention
For the deficiencies in the prior art, the present invention provide it is a kind of both had simple turbojet architecture, small volume,
Manufacturing technology requires relatively low advantage, and part has a kind of spray of the efficiency high of turbofan, fuel-efficient advantage
Gas formula electromotor.
The technical scheme is that what is be achieved in that：A kind of jet engine, including shell, compressor, combustor,
Turbine and main duct gas handling system, described main duct gas handling system is by the centrifugal impeller in the hollow axle and hollow axle of electromotor
Composition, on the hollow axle of the turbine portion at described electromotor rear portion or turbo blade is provided with and is connected with space in hollow axle
Gas outlet.
Described centrifugal impeller is located in the hollow axle of the turbine portion at electromotor rear portion.
The present invention has following good effect：The present invention instead of the outer of fanjet using main duct gas handling system
Ducted fan pattern had both avoided many of turbofan quickly completely and had manufactured and designed a difficult problem, remained fanjet again
Efficiency high, fuel-efficient advantage, return turbine and have dropped temperature, and which also has the simple structure of turbojet, at a high speed
The good advantage of performance.
Description of the drawings
Fig. 1 is the structural representation of the present invention.
Specific embodiment
As illustrated, a kind of jet engine, including shell 1, compressor 2, combustor 3, turbine 4 and main duct air inlet
System, described main duct gas handling system are provided with 6 He of receded disk impeller in the hollow axle 5 and hollow axle 5 of air inlet 8 for front end
The gas outlet 7 that turbine 4 is provided with constitutes.
In carrying out practically, gas enters 3 burning expansion of combustor Jing after compressor 2 is by gas compression and passes through the present invention
Spray after turbine 4 and produce thrust, combustion gas portion of energy when turbine 4 is converted into mechanical energy, drives hollow axle 5 and hollow axle 5
Interior receded disk impeller 6 and compressor 2 rotate, while the rotation of receded disk impeller 6 gets rid of the air-flow entered from air inlet 8 to whirlpool
Spray in wheel 4 and from gas outlet 7, the air-flow sprayed from gas outlet 7 has both dropped temperature to turbine 4 and expanded further through high temperature is absorbed
Acting produces thrust, and continues expansion, with high speed along engine shaft to being discharged from spout backward, this speed ratio in jet pipe
The speed that air-flow enters electromotor is much bigger, makes electromotor obtain more thrusts.
Claims (1)
1. a kind of jet engine, including shell, compressor, combustor, turbine and main duct gas handling system, its feature exist
In：Described main duct gas handling system is made up of the centrifugal impeller in the hollow axle and hollow axle of electromotor, described electromotor
On the hollow axle of the turbine portion at rear portion or turbo blade is provided with the gas outlet being connected with space in hollow axle, it is described from
Lobus cardiacus wheel is located in the hollow axle of the turbine portion at electromotor rear portion, the centrifugal leaf in driven by engine hollow axle and hollow axle
Wheel rotation, the rotation of receded disk impeller are got rid of the air-flow entered from air inlet into turbine and are sprayed from gas outlet, from gas outlet
The air-flow of ejection has both dropped temperature to turbine, and further through absorption high temperature, expansion work produces thrust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721762.5A CN105240159B (en) | 2015-10-30 | 2015-10-30 | A kind of jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721762.5A CN105240159B (en) | 2015-10-30 | 2015-10-30 | A kind of jet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105240159A CN105240159A (en) | 2016-01-13 |
| CN105240159B true CN105240159B (en) | 2017-03-29 |
Family
ID=55037939
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510721762.5A Active CN105240159B (en) | 2015-10-30 | 2015-10-30 | A kind of jet engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN105240159B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111636975B (en) * | 2020-06-08 | 2021-12-07 | 清华大学 | Two-duct turbine jet engine with bearing cooling function |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201196120Y (en) * | 2008-04-22 | 2009-02-18 | 聂振傲 | Hollow shaft turbojet engine |
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN102434218A (en) * | 2011-11-27 | 2012-05-02 | 王政玉 | Fluid turbine engine |
| EP2540991A2 (en) * | 2011-06-28 | 2013-01-02 | United Technologies Corporation | Mechanism for turbine engine start from low spool |
| CN103306736A (en) * | 2012-04-30 | 2013-09-18 | 王政玉 | Power turbine and power machine of the power turbine |
| CN103306735A (en) * | 2012-04-28 | 2013-09-18 | 王政玉 | Hybrid power machine |
| CN205078365U (en) * | 2015-10-30 | 2016-03-09 | 常胜 | Jet engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2385382B (en) * | 2002-02-13 | 2006-02-15 | Rolls Royce Plc | A cowl structure for a gas turbine engine |
-
2015
- 2015-10-30 CN CN201510721762.5A patent/CN105240159B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201196120Y (en) * | 2008-04-22 | 2009-02-18 | 聂振傲 | Hollow shaft turbojet engine |
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| EP2540991A2 (en) * | 2011-06-28 | 2013-01-02 | United Technologies Corporation | Mechanism for turbine engine start from low spool |
| CN102434218A (en) * | 2011-11-27 | 2012-05-02 | 王政玉 | Fluid turbine engine |
| CN103306735A (en) * | 2012-04-28 | 2013-09-18 | 王政玉 | Hybrid power machine |
| CN103306736A (en) * | 2012-04-30 | 2013-09-18 | 王政玉 | Power turbine and power machine of the power turbine |
| CN205078365U (en) * | 2015-10-30 | 2016-03-09 | 常胜 | Jet engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105240159A (en) | 2016-01-13 |
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| TR01 | Transfer of patent right |
Effective date of registration: 20201113 Address after: No.10 Da'an Road, si'en Town, Huanjiang Maonan Autonomous County, Hechi City, Guangxi Zhuang Autonomous Region Patentee after: Yao Wenmao Address before: Changyuan county south Pu District Zhuang Kecun Xinxiang city in Henan province 453400 3 groups Patentee before: Chang Sheng |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211118 Address after: 273300 101, East first floor, Pingyi County Economic Development Zone Management Committee, Linyi City, Shandong Province Patentee after: Pingyi Jingfa Industry Development Co.,Ltd. Address before: No.10 Da'an Road, si'en Town, Huanjiang Maonan Autonomous County, Hechi City, Guangxi Zhuang Autonomous Region Patentee before: Yao Wenmao |