CN104975984A - Turbofan engine structurally integrated with aircraft - Google Patents
Turbofan engine structurally integrated with aircraft Download PDFInfo
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- CN104975984A CN104975984A CN201510412652.0A CN201510412652A CN104975984A CN 104975984 A CN104975984 A CN 104975984A CN 201510412652 A CN201510412652 A CN 201510412652A CN 104975984 A CN104975984 A CN 104975984A
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- turbofan engine
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Abstract
The invention discloses a turbofan engine structurally integrated with an aircraft. The turbofan engine comprises an engine fan, an air compressor, a combustion chamber, a turbine and an inner spray pipe, all of which are arranged in sequence. An inner duct is arranged between the engine fan and the air compressor. An outer duct is arranged on the outer side of the wall of the inner duct. The wall of the outer duct of the turbofan engine is integrally connected with the outer wall of the aircraft. The front end of the engine fan is connected with an air inlet device. Outside airflow entering the air inlet device passes through the engine fan to form two parts of airflow; one part enters the inner duct and passes through the air compressor, the combustion chamber, the turbine and the inner spray pipe; the other part enters the outer duct formed by the outer wall of the aircraft and the wall of the inner duct, and finally is mixed with high-temperature high-speed airflow sprayed out of the inner spray pipe to be sprayed out to form counteracting force. The wall of the outer duct of the turbine engine and the outer wall of the aircraft are integrated, that is, the new outer duct is formed by the wall of the inner duct of the engine and the outer wall of the aircraft. By means of the method, the total weight of the aircraft is greatly reduced, and the overall dimension of the aircraft is reduced.
Description
Technical field
The present invention relates to a kind of turbofan engine structure, particularly relate to a kind of turbofan engine integrated with Flight Vehicle Structure.
Background technique
Turbofan engine, is called for short " turbofan engine ".Be on the basis of turbojet engine, installed the fan that driven by turbine additional and covered the by-pass air duct of fan and a kind of air breathing jet engine of forming.Turbofan engine has that oil consumption is low, exhaust stream infrared intensity is low, total efficiency advantages of higher, but owing to which increasing the parts such as fan, by-pass air duct, its absolute weight is larger.At present, turbofan engine has been widely used on various cruise vehicle.
The weight and volume of aircraft is a key factor of its indicators of overall performance of restriction.The weight and volume of turbofan engine itself is then an important restriction of aircraft performance, when the loss of weight measure of engine body has been in bottleneck, in order to retain some advantages of turbofan engine itself, reduce again weight and volume restriction requirement, be an important design direction simultaneously.
Therefore, need to provide a kind of new technological scheme to solve the problems referred to above.
Summary of the invention
In order to reduce aircraft weight, reduce aircraft overall sizes, the technical issues that need to address of the present invention are to provide turbofan engine that is a kind of and Flight Vehicle Structure integrated design, low in reservation turbofan engine oil consumption, exhaust stream infrared intensity is low, under the prerequisite of total efficiency advantages of higher, reduce turbofan engine weight and by turbofan engine by-pass air duct and aircraft integrated design, reduce aircraft weight and overall sizes, improve aircraft overall performance.
For solving technical problem of the present invention, the technical solution used in the present invention is:
A kind of turbofan engine integrated with Flight Vehicle Structure, this turbofan engine comprises the engine blower set gradually, gas compressor, firing chamber, turbine and inner nozzle, between described engine blower and gas compressor, main duct is set, it is by-pass air duct outside main duct wall, turbofan engine by-pass air duct wall is integrated with aircraft outer wall to be connected, described engine blower front end is connected with air inlet system, from the external air flow that air inlet system enters, two-part air-flow is defined after by engine blower, a part enters main duct, and through gas compressor, firing chamber, turbine and inner nozzle, another part enters the by-pass air duct that aircraft outer wall and main duct wall are formed, and the high-temperature high-speed airflow blending that final and inner nozzle sprays sprays and forms reaction force.
Beneficial effect of the present invention: be separated containing passage inside and outside turbofan engine, connect integrated with aircraft outer wall for turbofan engine by-pass air duct wall, eliminate former turbofan engine by-pass air duct wall, former turbofan engine by-pass air duct and the space between motor and aircraft are merged, using the passage between main duct wall and aircraft wall as turbofan engine " by-pass air duct ", this method greatly reduces air vehicle overall weight, and reduces aircraft overall sizes.
Accompanying drawing explanation
Fig. 1 is that turbofan engine of the present invention contains wall and aircraft outer wall integral structure schematic diagram outward.
1, air inlet system, 2, aircraft outer wall, 3, main duct, 4, main duct wall, 5, by-pass air duct, 6, engine blower, 7, gas compressor, 8, firing chamber, 9, turbine, 10, inner nozzle, 11, motor by-pass air duct wall.
Embodiment
Below in conjunction with the drawings and specific embodiments, the invention will be further described.Following examples, only for illustration of the present invention, are not used for limiting the scope of the invention.
As shown in Figure 1, a kind of turbofan engine integrated with Flight Vehicle Structure of the present invention, this turbofan engine comprises the engine blower 6 set gradually, gas compressor 7, firing chamber 8, turbine 9 and inner nozzle 10, main duct 3 is set between engine blower 6 and gas compressor 7, it is by-pass air duct 5 outside main duct wall 4, turbofan engine by-pass air duct wall 11 is integrated with aircraft outer wall 2 to be connected, engine blower 6 front end is connected with air inlet system 1, from the external air flow that air inlet system 1 enters, two-part air-flow is defined after by engine blower 6, a part enters main duct 3, and through gas compressor 7, firing chamber 8, turbine 9 and inner nozzle 10, another part enters the by-pass air duct that aircraft outer wall 2 is formed with main duct wall 4, and finally and the high-temperature high-speed airflow blending that sprays of inner nozzle 10 spray and form reaction force.
In the present invention, air inlet system 1 is mainly intake duct and carries out with engine intake casing the supporting section that is mechanically connected.Intake duct is the streamline ductwork of one section of geometry profile complexity, and the air of aircraft exterior is introduced motor; Supporting section is fixed intake duct, and is connected with engine intake by intake duct.
Turbofan engine is contained wall outward and aircraft outer wall carries out integrated design, eliminate original turbofan engine by-pass air duct wall, aircraft outer wall is formed new " by-pass air duct " as by-pass air duct wall together with motor main duct wall, reduces aircraft outer wall dimension.The fan part of turbofan engine, compressor part, combustion chamber components, turbine part and change for jet pipe parts etc. do not do.
Its working procedure is: the air of being come in by aircraft air inlet system 1, enter motor and by being divided into two-way after fan, the gas compressor 7 of motor main duct, firing chamber 8, turbine 9 and inner nozzle 10 are flow through in one tunnel, another road enters " by-pass air duct " that former turbofan main duct outer wall and aircraft wall are formed, and eventually through main duct outer wall in aircraft wall, former turbofan engine and main duct spout tail cone, Gas Mixing in Cross flow is formed reaction force.
A kind of turbofan engine integrated with Flight Vehicle Structure of the present invention, by integrated with aircraft outer wall for turbofan engine by-pass air duct wall, namely motor main duct wall and aircraft outer wall are formed new " by-pass air duct ".This method greatly reduces air vehicle overall weight, and reduces aircraft overall sizes.
Claims (1)
1. a turbofan engine integrated with Flight Vehicle Structure, is characterized in that: this turbofan engine comprise set gradually engine blower, gas compressor, firing chamber, turbine and inner nozzle,
Between described engine blower and gas compressor, main duct is set, it is by-pass air duct outside main duct wall, turbofan engine by-pass air duct wall is integrated with aircraft outer wall to be connected, described engine blower front end is connected with air inlet system, from the external air flow that air inlet system enters, after by engine blower, define two-part air-flow, a part enters main duct, and through gas compressor, firing chamber, turbine and inner nozzle; Another part enters the by-pass air duct that aircraft outer wall and main duct wall are formed, and the high-temperature high-speed airflow blending that final and inner nozzle sprays sprays and forms reaction force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510412652.0A CN104975984A (en) | 2015-07-15 | 2015-07-15 | Turbofan engine structurally integrated with aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510412652.0A CN104975984A (en) | 2015-07-15 | 2015-07-15 | Turbofan engine structurally integrated with aircraft |
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| CN104975984A true CN104975984A (en) | 2015-10-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201510412652.0A Pending CN104975984A (en) | 2015-07-15 | 2015-07-15 | Turbofan engine structurally integrated with aircraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107696812A (en) * | 2017-10-10 | 2018-02-16 | 中国人民解放军国防科技大学 | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same |
| CN108533418A (en) * | 2018-04-28 | 2018-09-14 | 上海啸风航空科技有限公司 | A kind of double duct mixing exhaust fanjets of novel microminiature |
| CN109080837A (en) * | 2018-07-23 | 2018-12-25 | 西北工业大学 | Small-sized unmanned aircraft |
| CN111520253A (en) * | 2020-04-30 | 2020-08-11 | 朱凤梅 | Jet engine structure for airplane based on wind power change |
| CN114518229A (en) * | 2020-11-20 | 2022-05-20 | 北京航天试验技术研究所 | Double-duct diffuser for supersonic free jet test of air-breathing engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1314597A (en) * | 1961-12-16 | 1963-01-11 | Hamburger Flugzeugbau Gmbh | Installation of jet engines in the tail of aircraft |
| DE1146761B (en) * | 1961-06-28 | 1963-04-04 | Messerschmitt Ag | Arrangement of jet engines in the end of the fuselage of an aircraft |
| US20070215751A1 (en) * | 2006-03-20 | 2007-09-20 | Robbins Brent A | Asymmetrical VTOL UAV |
| FR2965250A1 (en) * | 2010-09-28 | 2012-03-30 | Snecma | Installation for engines i.e. turbojet engines, at back of fuselage of twin-jet engine aircraft, has engines whose axles are directed in oblique manner with respect to longitudinal plane of aircraft for forming equal angles |
| CN102826227A (en) * | 2012-08-22 | 2012-12-19 | 冯加伟 | Unmanned space fighter |
| CN204783324U (en) * | 2015-07-15 | 2015-11-18 | 江西洪都航空工业集团有限责任公司 | Fanjet with integration of aircraft structure |
-
2015
- 2015-07-15 CN CN201510412652.0A patent/CN104975984A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1146761B (en) * | 1961-06-28 | 1963-04-04 | Messerschmitt Ag | Arrangement of jet engines in the end of the fuselage of an aircraft |
| FR1314597A (en) * | 1961-12-16 | 1963-01-11 | Hamburger Flugzeugbau Gmbh | Installation of jet engines in the tail of aircraft |
| US20070215751A1 (en) * | 2006-03-20 | 2007-09-20 | Robbins Brent A | Asymmetrical VTOL UAV |
| FR2965250A1 (en) * | 2010-09-28 | 2012-03-30 | Snecma | Installation for engines i.e. turbojet engines, at back of fuselage of twin-jet engine aircraft, has engines whose axles are directed in oblique manner with respect to longitudinal plane of aircraft for forming equal angles |
| CN102826227A (en) * | 2012-08-22 | 2012-12-19 | 冯加伟 | Unmanned space fighter |
| CN204783324U (en) * | 2015-07-15 | 2015-11-18 | 江西洪都航空工业集团有限责任公司 | Fanjet with integration of aircraft structure |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107696812A (en) * | 2017-10-10 | 2018-02-16 | 中国人民解放军国防科技大学 | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same |
| CN107696812B (en) * | 2017-10-10 | 2019-06-28 | 中国人民解放军国防科技大学 | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same |
| CN108533418A (en) * | 2018-04-28 | 2018-09-14 | 上海啸风航空科技有限公司 | A kind of double duct mixing exhaust fanjets of novel microminiature |
| CN109080837A (en) * | 2018-07-23 | 2018-12-25 | 西北工业大学 | Small-sized unmanned aircraft |
| CN111520253A (en) * | 2020-04-30 | 2020-08-11 | 朱凤梅 | Jet engine structure for airplane based on wind power change |
| CN114518229A (en) * | 2020-11-20 | 2022-05-20 | 北京航天试验技术研究所 | Double-duct diffuser for supersonic free jet test of air-breathing engine |
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Application publication date: 20151014 |