CN204783324U - Fanjet with integration of aircraft structure - Google Patents
Fanjet with integration of aircraft structure Download PDFInfo
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- CN204783324U CN204783324U CN201520509224.5U CN201520509224U CN204783324U CN 204783324 U CN204783324 U CN 204783324U CN 201520509224 U CN201520509224 U CN 201520509224U CN 204783324 U CN204783324 U CN 204783324U
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Abstract
The utility model provides a fanjet with integration of aircraft structure, this fanjet is including the engine blower that sets gradually, the compressor, the combustion chamber, turbine and interior spray tube, set up interior duct between engine blower and the compressor, the interior duct wall outside is the by -pass air duct, fanjet by -pass air duct wall is connected with the outer wall integration of aircraft, the engine blower front end is connected with air inlet unit, external air current from the air inlet unit entering, two parts air current has been formed through the engine blower after, duct in partly the entering, and through the compressor, the combustion chamber, turbine and interior spray tube, another part gets into the by -pass air duct of outer wall of aircraft and the formation of interior duct wall to final and interior spray tube spun high temperature high -velocity air mixing blowout forms reaction force. With the outer wall integration greatly reduced of fanjet by -pass air duct wall and aircraft totality weight to aircraft contour dimension has been reduced.
Description
Technical field
The utility model relates to a kind of turbofan engine structure, particularly relates 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 utility model technical issues that need to address 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 utility model, the technical solution adopted in the utility model 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.
The beneficial effects of the utility model: 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 utility model 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 utility model is described in further detail.Following examples, only for illustration of the utility model, are not used for limiting protection domain of the present utility model.
As shown in Figure 1, a kind of turbofan engine integrated with Flight Vehicle Structure of the present utility model, 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 utility model, 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 utility model, 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 |
|---|---|---|---|
| CN201520509224.5U CN204783324U (en) | 2015-07-15 | 2015-07-15 | Fanjet with integration of aircraft structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520509224.5U CN204783324U (en) | 2015-07-15 | 2015-07-15 | Fanjet with integration of aircraft structure |
Publications (1)
| Publication Number | Publication Date |
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| CN204783324U true CN204783324U (en) | 2015-11-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520509224.5U Active CN204783324U (en) | 2015-07-15 | 2015-07-15 | Fanjet with integration of aircraft structure |
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| CN (1) | CN204783324U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104975984A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Turbofan engine structurally integrated with aircraft |
| CN109460628A (en) * | 2018-12-14 | 2019-03-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of air intake duct and the cooperative flow matches appraisal procedure of engine |
| CN113027609A (en) * | 2021-03-23 | 2021-06-25 | 天津鱼羊文化传播有限公司 | Turbofan engine |
-
2015
- 2015-07-15 CN CN201520509224.5U patent/CN204783324U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104975984A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Turbofan engine structurally integrated with aircraft |
| CN109460628A (en) * | 2018-12-14 | 2019-03-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of air intake duct and the cooperative flow matches appraisal procedure of engine |
| CN109460628B (en) * | 2018-12-14 | 2023-05-26 | 中国航空工业集团公司西安飞机设计研究所 | Flow matching evaluation method for joint work of air inlet channel and engine |
| CN113027609A (en) * | 2021-03-23 | 2021-06-25 | 天津鱼羊文化传播有限公司 | Turbofan engine |
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