CN205078365U - Jet engine - Google Patents
Jet engine Download PDFInfo
- Publication number
- CN205078365U CN205078365U CN201520853312.7U CN201520853312U CN205078365U CN 205078365 U CN205078365 U CN 205078365U CN 201520853312 U CN201520853312 U CN 201520853312U CN 205078365 U CN205078365 U CN 205078365U
- Authority
- CN
- China
- Prior art keywords
- hollow shaft
- turbine
- engine
- jet engine
- centrifugal impeller
- 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
Links
- 238000010304 firing Methods 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 12
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Abstract
The utility model relates to a jet engine, including shell, compressor, combustion chamber, turbine and interior duct air intake system, interior duct air intake system form by the hollow shaft of engine and the centrifugal impeller in the hollow shaft, the hollow shaft of turbine part at engine rear portion on or be equipped with the gas outlet that is linked together with the hollow shaft inner space on the turbine blade, the utility model discloses remain turbofan engine's the low advantage of efficient, oil consumption, returned the turbine and fallen the temperature, its simple structure who still has turbojet moreover, advantage that high speed performance is good.
Description
Technical field
The utility model relates to a kind of jet engine.
Background technique
Turbojet engine is a kind of turbogenerator, and feature relies on gas flow completely to produce thrust, and be typically used as the power of high-speed aircraft, oil consumption is higher than turbofan engine, is mainly used in fight and supersonic airliner, such as Concorde
.
Turbojet engine,
havethe advantage that efficiency is high, oil consumption is low, flight is just far away, but simultaneously also have high speed performance to be not so good as turbojet engine, complex structure, design difficulty are large, involve great expense shortcoming.
Summary of the invention
For the deficiencies in the prior art, the utility model provides a kind of and had both had the advantage that turbojet architecture is simple, volume is little, manufacturing technology requirement is lower, and part has again
turbofan enginea kind of jet engine of high, the fuel-efficient advantage of efficiency.
The technical solution of the utility model is achieved in that a kind of jet engine, comprise shell, gas compressor, firing chamber, turbine and main duct gas handling system, described main duct gas handling system is made up of the centrifugal impeller in the hollow shaft of motor and hollow shaft, on the hollow shaft of the turbine portion at described motor rear portion or turbine blade be provided with the air outlet be connected with space in hollow shaft.
Described centrifugal impeller is located in the hollow shaft of the turbine portion at motor rear portion.
The utility model has following good effect: the by-pass air duct fan mode that the utility model utilizes main duct gas handling system to instead of turbofan engine had both avoided the many of turbofan quickly completely and manufactured and designed a difficult problem, remain again high, the fuel-efficient advantage of efficiency of turbofan engine, return turbine and fall temperature, and its structure also with turbojet engine is simple, the advantage that high speed performance is good.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Embodiment
As shown in the figure, a kind of jet engine, comprise shell 1, gas compressor 2, firing chamber 3, turbine 4 and main duct gas handling system, described main duct gas handling system is that front end is provided with the air outlet 7 that centrifugal impeller 6 in the hollow shaft 5 of suction port 8 and hollow shaft 5 and turbine 4 be provided with and forms.
The utility model is when carrying out practically, gas will enter firing chamber 3 burning expansion through gas compressor 2 and sprays after turbine 4 and produces thrust after gas compression, combustion gas portion of energy when turbine 4 is converted into mechanical energy, the centrifugal impeller 6 in hollow shaft 5 and hollow shaft 5 and gas compressor 2 is driven to rotate, the simultaneously rotation of centrifugal impeller 6 is got rid of the air-flow entered from suction port 8 in turbine 4 and is sprayed from air outlet 7, the air-flow sprayed from air outlet 7 has not only fallen temperature to turbine 4 but also pass through absorption high temperature and expansion work generation thrust, and continue to expand in jet pipe, to discharge backward along engine shaft to from spout at a high speed, the speed that this speed enters motor than air-flow is much bigger, motor is made to obtain more thrust.
Claims (2)
1. a jet engine, comprise shell, gas compressor, firing chamber, turbine and main duct gas handling system, it is characterized in that: described main duct gas handling system is made up of the centrifugal impeller in the hollow shaft of motor and hollow shaft, on the hollow shaft of the turbine portion at described motor rear portion or turbine blade be provided with the air outlet be connected with space in hollow shaft.
2. a kind of jet engine according to claim 1, is characterized in that: described centrifugal impeller is located in the hollow shaft of the turbine portion at motor rear portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520853312.7U CN205078365U (en) | 2015-10-30 | 2015-10-30 | Jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520853312.7U CN205078365U (en) | 2015-10-30 | 2015-10-30 | Jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205078365U true CN205078365U (en) | 2016-03-09 |
Family
ID=55430779
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520853312.7U Expired - Fee Related CN205078365U (en) | 2015-10-30 | 2015-10-30 | Jet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205078365U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240159A (en) * | 2015-10-30 | 2016-01-13 | 常胜 | Jet engine |
-
2015
- 2015-10-30 CN CN201520853312.7U patent/CN205078365U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240159A (en) * | 2015-10-30 | 2016-01-13 | 常胜 | Jet engine |
| CN105240159B (en) * | 2015-10-30 | 2017-03-29 | 常胜 | A kind of jet engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160309 Termination date: 20171030 |