CN203604064U - Turbojet engine - Google Patents
Turbojet engine Download PDFInfo
- Publication number
- CN203604064U CN203604064U CN201320699493.3U CN201320699493U CN203604064U CN 203604064 U CN203604064 U CN 203604064U CN 201320699493 U CN201320699493 U CN 201320699493U CN 203604064 U CN203604064 U CN 203604064U
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- Prior art keywords
- main
- engine
- high pressure
- guan
- zhu
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- 239000001301 oxygen Substances 0.000 claims abstract description 15
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 15
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 14
- 239000007789 gas Substances 0.000 claims description 13
- 239000007921 spray Substances 0.000 claims description 6
- 238000002485 combustion reaction Methods 0.000 abstract description 8
- 238000005507 spraying Methods 0.000 abstract description 7
- 230000009194 climbing Effects 0.000 abstract description 2
- 239000002737 fuel gas Substances 0.000 abstract 1
- 239000000567 combustion gas Substances 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 150000002926 oxygen Chemical class 0.000 description 1
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Abstract
The utility model discloses a turbojet engine. The turbojet engine is mainly characterized in that an auxiliary tail spraying pipe of an auxiliary engine is communicated with a main tail spraying pipe of a main engine through a connecting pipe, a double-air-inlet turbojet engine is formed, the auxiliary engine sucks air from atmosphere, the air is rapidly adjusted and compressed in the auxiliary tail spraying pipe, pressure and temperature of air flow rise, the air flow passes through an oxygen volatilization device to form oxygen-enriched air flow, the oxygen-enriched air flow is expanded, is discharged from a spraying opening of the auxiliary tail spraying pipe at high speed, and is sprayed into the main tail spraying pipe of the main engine through the connecting pipe, oxygen is sprayed to a main combustion chamber of the main engine, fuel gas which is not fully combusted in the main combustion chamber is fully combusted, and power of the main engine is effectively increased, so that pushing force of the engine is effectively improved, and the climbing height of an airplane and the flight of the airplane are effectively improved.
Description
Technical field
The utility model relates to a kind of turbogenerator, particularly a kind of turbojet engine.Mainly be applicable to Aviation Industry.
Background technique
Conventionally the turbojet engine adopting on high speed space shuttle is single intake duct turbojet engine, it is by intake duct and connected jet pipe, the low-pressure turbine that is positioned at jet pipe and be connected by rotatingshaft and low pressure compressor, the fan being connected with low pressure compressor, and the high pressure turbine and the high-pressure compressor that are connected with rotatingshaft sleeve pipe, combuster in the respective cavities in jet pipe and between high pressure turbine and high-pressure compressor and forming.Because this turbojet engine is single intake duct, exist deficiency of air, thrust is inadequate, and the insufficient height climbing is high, can exert an adverse impact to the flight performance of aircraft like this.
Summary of the invention
The purpose of this utility model is to provide a kind of turbojet engine, and it can overcome the deficiency of prior art, can effectively increase air input of engine by air, improves thrust and climb altitude and the voyage of motor.
Its solution is: turbojet engine comprises master motor and assistant engine two-part, and the secondary jet pipe of assistant engine is connected with the main jet pipe of master motor by connecting tube, form twin-inlet turbojet engine, be master motor input air-flow by assistant engine, increase the thrust of master motor.Described master motor is by main air intake and connected main jet pipe, the primary low turbo machine that is positioned at main jet pipe and be connected by main rotary shaft and primary low gas compressor, the main fan being connected with primary low gas compressor, and the main high pressure turbine and the main high-pressure compressor that are connected by the quill being connected to by suit on main rotary shaft, in the respective cavities between main jet pipe and main high pressure turbine and main high-pressure compressor, there is main combustion chamber and form.
Described assistant engine is by secondary intake duct and connected secondary jet pipe, the secondary depression turbo machine that is positioned at secondary jet pipe and be connected by secondary rotatingshaft and secondary depression gas compressor, the secondary fan being connected with secondary depression gas compressor, and the secondary high pressure turbine and the secondary high-pressure compressor that are connected by the secondary case tubular axis being connected to by suit on secondary rotatingshaft, in the respective cavities between secondary jet pipe and secondary high pressure turbine and secondary high-pressure compressor, there is oxygen volatilizer and form.
The utility model adopts technique scheme, because the secondary jet pipe of assistant engine is connected with the main jet pipe of master motor by connecting tube, forms twin-inlet turbojet engine.Assistant engine is by the air of inspiration from atmosphere, in secondary jet pipe, carry out speed adjustment, compression, make after the pressure and temperature rising of air-flow, form oxygen-enriched stream through oxygen volatilizer, this oxygen-enriched stream is after expanding, at full speed discharge in connecting tube sprays into the main jet pipe of master motor from the spout of secondary jet pipe, in the main combustion chamber of master motor, spray into oxygen, not clean-burning combustion gas in main combustion chamber is fully burned, can effectively increase the power of master motor, thereby can effectively improve the thrust of motor, can make climb altitude and the flight voyage of aircraft be effectively improved.
Accompanying drawing explanation
Accompanying drawing is a kind of structural representation of turbojet engine.
Embodiment
Describe embodiment of the present utility model in detail below in conjunction with accompanying drawing.
In accompanying drawing, turbojet engine comprises master motor 21 and assistant engine 20 two-part.And the secondary jet pipe spout 11 of the secondary jet pipe 16 of assistant engine 20 is by connecting tube 10, be connected with the main jet pipe 8 of master motor 21, form twin-inlet turbojet engine.Described master motor 21 is by main air intake 22 and coupled logical main jet pipe 8, be positioned at main jet pipe 8 the primary low turbo machine 6 being connected by main rotary shaft 3 and primary low gas compressor 1, the main fan 23 being connected with primary low gas compressor 1, and the main high pressure turbine 5 and the main high-pressure compressor 2 that are connected by the quill 4 being connected to by suit on main rotary shaft 3, in the respective cavities between main jet pipe 8 and main high pressure turbine 5 and main high-pressure compressor 2, be provided with main combustion chamber 9 and form.Described assistant engine 20 is by secondary intake duct 19 and coupled logical secondary jet pipe 16, be positioned at secondary jet pipe 16 the secondary depression turbo machine 12 being connected by secondary rotatingshaft and secondary depression gas compressor 17, the secondary fan 18 being connected with secondary depression gas compressor 17, and the secondary high pressure turbine 13 and the secondary high-pressure compressor 15 that are connected by the secondary case tubular axis being connected to by suit on secondary rotatingshaft, in the respective cavities between secondary jet pipe 16 and secondary high pressure turbine 13 and secondary high-pressure compressor 15, be provided with oxygen volatilizer 14 and form.
When assistant engine is under the rotation status of secondary fan 18, by its secondary intake duct 19, the air of inspiration from atmosphere is carried out to incoming flow adjustment, it is adjusted into after suitable speed, through gas compressor, air-flow is compressed, make after the pressure and temperature rising of air-flow, under the effect of oxygen volatilizer 14, form oxygen-enriched stream, this air flow stream is crossed same gas compressor and is contained in the turbo machine on same rotatingshaft, after expanding in turbo machine, flow out, in jet pipe, continue to expand, with high speed axially discharging backward from secondary jet pipe spout 11 along assistant engine 20, in connecting tube 10 enters the main jet pipe 8 of master motor 21, in main combustion chamber 9, spray into oxygen, not clean-burning combustion gas in main combustion chamber 9 is burnt again with the oxygen mix spraying into, thereby can increase widely the thrust of motor.
Claims (2)
1. a turbojet engine, it is characterized in that comprising Zhu Fa Dong Ji ﹙ 21 ﹚ and Fu Fa Dong Ji ﹙ 20 ﹚ two-part, and secondary Wei Pen Guan ﹙ 16 ﹚ of Fu Fa Dong Ji ﹙ 20 ﹚ are connected with main Wei Pen Guan ﹙ 8 ﹚ of Zhu Fa Dong Ji ﹙ 21 ﹚ by Lian Jie Guan ﹙ 10 ﹚, form twin-inlet turbojet engine, described master sends out machine ﹙ 21 ﹚ by Zhu Jin gas road ﹙ 22 ﹚ and connected main tail spray pipe ﹙ 8 ﹚, primary low Wo Lun Ji ﹙ 6 ﹚ that are positioned at main Wei Pen Guan ﹙ 8 ﹚ and be connected by Zhu Zhuan Dong Zhou ﹙ 3 ﹚ and primary low Ya Qi Ji ﹙ 1 ﹚, main Feng Shan ﹙ 23 ﹚ that are connected with primary low Ya Qi Ji ﹙ 1 ﹚, and main high pressure Wo Lun Ji ﹙ 5 ﹚ that are connected by Zhu Tao Guan Zhou ﹙ 4 ﹚ that are connected to by suit on Zhu Zhuan Dong Zhou ﹙ 3 ﹚ and main high pressure Ya Qi Ji ﹙ 2 ﹚, in respective cavities between main Wei Pen Guan ﹙ 8 ﹚ and main high pressure Wo Lun Ji ﹙ 5 ﹚ and main high pressure Ya Qi Ji ﹙ 2 ﹚, there are Zhu Ran Shao Shi ﹙ 9 ﹚ and form.
2. a kind of turbojet engine as claimed in claim 1, pair described in it is characterized in that is sent out machine ﹙ 20 ﹚ by Fu Jin gas road ﹙ 19 ﹚ and connected secondary tail spray pipe ﹙ 16 ﹚, secondary depression Wo Lun Ji ﹙ 12 ﹚ that are positioned at secondary Wei Pen Guan ﹙ 16 ﹚ and be connected by secondary rotatingshaft and secondary depression Ya Qi Ji ﹙ 17 ﹚, secondary Feng Shan ﹙ 18 ﹚ that are connected with secondary depression Ya Qi Ji ﹙ 17 ﹚, and secondary high pressure Wo Lun Ji ﹙ 13 ﹚ that are connected by the secondary case tubular axis being connected to by suit on secondary rotatingshaft and secondary high pressure Ya Qi Ji ﹙ 15 ﹚, in the respective cavities between ﹙ 16 ﹚ and secondary high pressure whirlpool wheel machine ﹙ 13 ﹚ and secondary high pressure gas machine ﹙ 15 ﹚ is managed in secondary tail spray, having oxygen to wave sends out device ﹙ 14 ﹚ and forms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320699493.3U CN203604064U (en) | 2013-11-08 | 2013-11-08 | Turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320699493.3U CN203604064U (en) | 2013-11-08 | 2013-11-08 | Turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203604064U true CN203604064U (en) | 2014-05-21 |
Family
ID=50716740
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320699493.3U Expired - Lifetime CN203604064U (en) | 2013-11-08 | 2013-11-08 | Turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203604064U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106368851A (en) * | 2016-09-13 | 2017-02-01 | 中国民用航空飞行学院 | Multi-fan propelling device |
| WO2017197544A1 (en) * | 2016-05-18 | 2017-11-23 | 葛明龙 | Four aeronautic/astronautic turbofan engines |
| CN109209644A (en) * | 2018-07-31 | 2019-01-15 | 中国航发湖南动力机械研究所 | Blade tip turbogenerator |
| CN110294104A (en) * | 2019-07-02 | 2019-10-01 | 刘璐 | It is a kind of can VTOL the stealthy Fixed Wing AirVehicle of high speed |
-
2013
- 2013-11-08 CN CN201320699493.3U patent/CN203604064U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017197544A1 (en) * | 2016-05-18 | 2017-11-23 | 葛明龙 | Four aeronautic/astronautic turbofan engines |
| US10563619B2 (en) | 2016-05-18 | 2020-02-18 | Minglong GE | Aerospace turbofan engines |
| CN106368851A (en) * | 2016-09-13 | 2017-02-01 | 中国民用航空飞行学院 | Multi-fan propelling device |
| CN109209644A (en) * | 2018-07-31 | 2019-01-15 | 中国航发湖南动力机械研究所 | Blade tip turbogenerator |
| CN109209644B (en) * | 2018-07-31 | 2020-06-23 | 中国航发湖南动力机械研究所 | Blade tip turbine engine |
| CN110294104A (en) * | 2019-07-02 | 2019-10-01 | 刘璐 | It is a kind of can VTOL the stealthy Fixed Wing AirVehicle of high speed |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140521 |