CN102787945A - Secondary booster jet engine - Google Patents
Secondary booster jet engine Download PDFInfo
- Publication number
- CN102787945A CN102787945A CN2011101303559A CN201110130355A CN102787945A CN 102787945 A CN102787945 A CN 102787945A CN 2011101303559 A CN2011101303559 A CN 2011101303559A CN 201110130355 A CN201110130355 A CN 201110130355A CN 102787945 A CN102787945 A CN 102787945A
- Authority
- CN
- China
- Prior art keywords
- air breathing
- suction tude
- breathing engine
- secondary booster
- jet pipe
- 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.)
- Pending
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a secondary booster jet engine which comprises more than two jet engines, an air inlet pipe, an ascending pipe and an effuser, wherein one end of each of the air inlet pipe and the effuser is conical; the air inlet pipe is inserted into one end of the ascending pipe; the effuser is arranged at the other end of the ascending pipe; the jet engines are arranged on the inner wall of the air inlet pipe in a clockwise or anticlockwise manner. According to the secondary booster jet engine, existing jet engines such as a turbofan or a turbine are improved, and the jetted high-speed gas is subjected to secondary supercharging and then ejected to increase the power.
Description
Technical field
The present invention relates to the air breathing engine field, particularly relate to a kind of air breathing engine that can carry out secondary booster.
Background technique
Present air breathing engine generally comprises turbofan engine, turbogenerator etc.; It mainly is made up of intake duct, gas compressor, firing chamber, gas turbine and jet pipe; Air gets into gas compressor from intake duct, gets into the firing chamber after compression, and fuel is mixed combustion in pressurized air.Pressurized gas part after the burning drives turbine to supply with gas compressor and impeller power, and a part provides thrust from the jet pipe ejection.The principal element of restriction motor power is air inflow, air pressure, combustion gas initial temperature etc., and the present invention innovates from air inflow, supercharging aspect, and will assemble the multi-section air breathing engine, and its whole jet power significantly increases.
Summary of the invention
The objective of the invention is provides a kind of secondary booster air breathing engine in order to solve the deficiency of above-mentioned technology.The present invention improves air breathing engines such as existing turbofan or turbine, and the high speed hot gas of its ejection is carried out secondary booster, and ejection then is to strengthen its power.
The technological scheme that the present invention adopted is:
A kind of secondary booster air breathing engine comprises two above air breathing engines, suction tude, pressure inlet, jet pipe, and an end of said suction tude and jet pipe is respectively taper, is fitted with suction tude in the end of said pressure inlet, and its other end is equipped with jet pipe; Said air breathing engine is clockwise or is installed in counterclockwise on the inwall of suction tude; The high-speed gas of air breathing engine ejection is rotated into eddy current at pressure inlet; The vacuum that is formed centrally in the eddy current makes air be inhaled into from suction tude to reach pressurized effect, spray from jet pipe then.
Further, said pressure inlet and jet pipe are structure as a whole.
Further, said air breathing engine is a turbofan engine.
Further, said air breathing engine is a turbogenerator.
Adopt technique scheme, technique effect of the present invention has:
1, the present invention's stability is strong, and wherein the multi-section motor of device such as fruit part air breathing engine damage, and the present invention still can stability operate;
2, the present invention is simple in structure, and is practical, air breathing engines such as existing turbine or turbofan directly added load onto pressure inlet etc. and get final product;
3, power of the present invention is powerful, can at least two motors be assembled, and through links such as make-up gas superchargings, its jet power significantly increases.
Description of drawings
Fig. 1 is a structure cross-sectional schematic of the present invention;
Fig. 2 is the arrange embodiment schematic representation of air breathing engine of the present invention on suction tude;
Wherein: 1 air breathing engine, 2 suction tude, 3 pressure inlets, 4 jet pipes.
Embodiment
Below in conjunction with description of drawings embodiment of the present invention.
Secondary booster air breathing engine as shown in Figure 1; Comprise suction tude 2, pressure inlet 3, jet pipe 4; Suction tude 2 is taper with jet pipe 4; Suction tude 2 is inserted in the end of pressure inlet 3, and its tapered tip portion (being the osculum end) is in suction tude 2, and its afterbody (being big opening end) is packed in the end of suction tude 2.Jet pipe 4 is installed in the other end of pressure inlet 3, and the afterbody (being its big opening end) of concrete is jet pipe 4 is fixed in the end of pressure inlet 3, and its tapered tip portion (being the osculum end) is towards pressure inlet 3 outsides.During use multi-section air breathing engine 1 (can be turbine or turbofan engine etc.) being perhaps counterclockwise clockwise spiral is installed on the inwall of suction tude 2; The high-speed gas of air breathing engine 1 ejection is rotated into eddy current at pressure inlet 3; The vacuum that is formed centrally in the eddy current makes air be inhaled into from suction tude 2 to reach pressurized effect, then from jet pipe 4 ejections.
Above-mentioned pressure inlet 3 can be straight tubular or taper, and the tapering of its taper is less than the tapering of suction tude 2.During making, can pressure inlet 3 and jet pipe 4 be made of one structure.
Be the concrete use embodiment of example with four turbofan engines, as shown in Figure 2, four turbofan engine bolts are installed on the suction tude 2, and jet in pressure inlet 2.The high temperature and high pressure gas that after motor is through links such as turbofan, gas compressor, firing chambers, sprays; Spray into pressure inlet 2 from the cone tip part of suction tude 2; Gas rotates the generation eddy current of advancing rapidly in suction tude 2, be formed centrally vacuum in its eddy current, sucks gases in a large number from the outside by suction tude 2; The certain gas of the volume of pressure inlet 2 increases causes its air pressure sharply to strengthen, and the gas that carries out secondary booster is sprayed by the jet pipe 4 of afterbody rapidly.Present embodiment has been assembled 4 turbofan engines, and its jet gas has been carried out secondary booster, and its jet power is more than 4 times of common turbofan engine.
The present invention can be applied to a plurality of fields, like fighter of aviation field etc.Main core of the present invention is to form the middle part vacuum through jet generation eddy current; And then make-up gas carries out spraying behind the secondary booster; If one one or several engine failure in this device, remaining motor still can jet formation eddy current, can remain in operation.
What should explain at last is; Above embodiment is only unrestricted in order to technological scheme of the present invention to be described; Although with reference to preferred embodiment the present invention is specified, those of ordinary skill in the art should be appreciated that and can make amendment or be equal to replacement technological scheme of the present invention; And not breaking away from the spirit and the scope of technological scheme of the present invention, it all should be encompassed in the middle of the claim scope of the present invention.
Claims (4)
1. secondary booster air breathing engine; Comprise two above air breathing engines (1), suction tude (2), pressure inlet (3), jet pipe (4); It is characterized in that: an end of said suction tude (2) and jet pipe (4) is respectively taper; Be fitted with suction tude (2) in one end of said pressure inlet (3), its other end is equipped with jet pipe (4); Said air breathing engine (1) is clockwise or is installed in counterclockwise on the inwall of suction tude (2); The high-speed gas of air breathing engine (1) ejection is rotated into eddy current at pressure inlet (3); The vacuum that is formed centrally in the eddy current makes air be inhaled into from suction tude (2) to reach pressurized effect, spray from jet pipe (4) then.
2. secondary booster air breathing engine according to claim 1 is characterized in that: said pressure inlet (3) and jet pipe (4) are structure as a whole.
3. secondary booster air breathing engine according to claim 1 is characterized in that: said air breathing engine (1) is a turbofan engine.
4. secondary booster air breathing engine according to claim 1 is characterized in that: said air breathing engine (1) is a turbogenerator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101303559A CN102787945A (en) | 2011-05-19 | 2011-05-19 | Secondary booster jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101303559A CN102787945A (en) | 2011-05-19 | 2011-05-19 | Secondary booster jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102787945A true CN102787945A (en) | 2012-11-21 |
Family
ID=47153477
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011101303559A Pending CN102787945A (en) | 2011-05-19 | 2011-05-19 | Secondary booster jet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102787945A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2968920A (en) * | 1959-01-28 | 1961-01-24 | Gen Electric | Engine mounting arrangement |
| US4217756A (en) * | 1977-12-27 | 1980-08-19 | Boeing Commercial Airplane Company | Vortex mixers for reducing the noise emitted by jet engines |
| US4592202A (en) * | 1983-02-15 | 1986-06-03 | Commonwealth Of Australia | Thrust augmentor |
| US5428954A (en) * | 1994-04-11 | 1995-07-04 | Cowan, Sr.; Howard H. | System for suppressing engine exhaust noise |
| US6415597B1 (en) * | 1999-11-10 | 2002-07-09 | National Aerospace Laboratory Of Science And Technology Agency | Switchably coupled turbofan engines for high speed aircraft |
| CN1858498A (en) * | 2006-05-16 | 2006-11-08 | 北京航空航天大学 | Tangential standing vortex burning chamber |
| US20090056309A1 (en) * | 2007-08-30 | 2009-03-05 | United Technologies Corp. | Gas Turbine Engine Systems and Related Methods Involving Multiple Gas Turbine Cores |
-
2011
- 2011-05-19 CN CN2011101303559A patent/CN102787945A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2968920A (en) * | 1959-01-28 | 1961-01-24 | Gen Electric | Engine mounting arrangement |
| US4217756A (en) * | 1977-12-27 | 1980-08-19 | Boeing Commercial Airplane Company | Vortex mixers for reducing the noise emitted by jet engines |
| US4592202A (en) * | 1983-02-15 | 1986-06-03 | Commonwealth Of Australia | Thrust augmentor |
| US5428954A (en) * | 1994-04-11 | 1995-07-04 | Cowan, Sr.; Howard H. | System for suppressing engine exhaust noise |
| US6415597B1 (en) * | 1999-11-10 | 2002-07-09 | National Aerospace Laboratory Of Science And Technology Agency | Switchably coupled turbofan engines for high speed aircraft |
| CN1858498A (en) * | 2006-05-16 | 2006-11-08 | 北京航空航天大学 | Tangential standing vortex burning chamber |
| US20090056309A1 (en) * | 2007-08-30 | 2009-03-05 | United Technologies Corp. | Gas Turbine Engine Systems and Related Methods Involving Multiple Gas Turbine Cores |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103184913B (en) | Close-coupled high pressure gas silencing means | |
| CN109139296B (en) | Rocket-based combined cycle engine | |
| CN104295406B (en) | A kind of rocket punching press combined engine with ring-like ejection structure | |
| CN106051821B (en) | A kind of shunting multi-pipe impulse detonation combustor | |
| CN105257429B (en) | Composite rocket engine | |
| CN107762661A (en) | A kind of pulse-knocking injection ultra-combustion ramjet combined engine | |
| CN104696102A (en) | Working method of rocket capable of generating oxygen through superposition aspiration | |
| CN204663701U (en) | A kind of exhaust mixer of turbofan engine | |
| CN108506111B (en) | Microminiature turbofan engine | |
| CN104775935A (en) | Working method of superposition pressing oxygen production rocket | |
| CN102893009B (en) | Device for reducing the noise emitted by the jet of an aircraft propulsion engine | |
| CN102619642B (en) | Efficient turbojet engine | |
| CN203604064U (en) | Turbojet engine | |
| CN204099074U (en) | A kind of rocket punching press combined engine with ring-like ejection structure | |
| CN104832318A (en) | Ramjet engine | |
| CN102979612A (en) | Fan two-stroke engine | |
| CN102787945A (en) | Secondary booster jet engine | |
| CN106523187A (en) | Divided flow gas turbine engine | |
| CN201739027U (en) | Turbofan rear-mounted engine | |
| CN102822492B (en) | Spout nozzles and jet engine | |
| CN104131915A (en) | Ramjet started in static state | |
| CN104929809A (en) | Working method of detonation ram rocket | |
| CN205592035U (en) | Combined cycle engine | |
| CN203685414U (en) | Ramjet engine | |
| CN105756806B (en) | A kind of axisymmetric nozzle with afterbunring function |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121121 |