CN109606644A - A kind of asymmetric exhaust structure of lift fan - Google Patents
A kind of asymmetric exhaust structure of lift fan Download PDFInfo
- Publication number
- CN109606644A CN109606644A CN201811524186.5A CN201811524186A CN109606644A CN 109606644 A CN109606644 A CN 109606644A CN 201811524186 A CN201811524186 A CN 201811524186A CN 109606644 A CN109606644 A CN 109606644A
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- CN
- China
- Prior art keywords
- jet pipe
- asymmetric
- lift fan
- exhaust structure
- switching casing
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- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/001—Shrouded propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
- B64C29/04—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded characterised by jet-reaction propulsion
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to aircraft engine field of structural design, in particular to a kind of asymmetric exhaust structure of lift fan.It include: asymmetric tail bone (4), switching casing (5) and jet pipe (6).The switching casing (5) is provided with fairing group section, wherein one end of the fairing group section is connect with the asymmetric tail bone (4), and the end and lift fan are coaxial；The other end of the fairing group section is connect with the jet pipe (6), and the end and the jet pipe (6) are coaxial；The middle part of the fairing group section is smooth curved sections.The asymmetric exhaust structure of the lift fan of the application connects asymmetric tail bone and jet pipe using the switching casing for being provided with fairing group section, can reduce lift fan discharge loss, guarantee nozzle performance and fan aeroperformance.
Description
Technical field
The application belongs to aircraft engine field of structural design, in particular to a kind of asymmetric exhaust structure of lift fan.
Background technique
Short takeoff vertical landing aircraft power lift fan is a kind of by the dynamic of spout generation lift vertically downward
Force system component provides certain vector ability, keeps spout exhaust airstream direction certain to the forward and backward swing of heading
Angle, to complete the specific action of aircraft.Lift fan exhaust airstream flows into jet pipe from fan outlet, and jet pipe itself is difficult to live
It is dynamic, a kind of small size, the light-weight jet pipe with vector regulating power are needed, and jet pipe need to have stable flow, from wind
Fan, which exports to nozzle exit, will reduce windage loss, to guarantee the performance of lift fan.
The exhaust structure of lift fan generally comprises: lift fan tail bone, switching casing, jet pipe.Lift fan air-flow is logical
Cross after intermediary's supporting plate and to enter exhaust structure, exhaust be by by lift fan tail bone and switching machine box at runner, enter
The jet pipe of end.Transfer casing structure is discontinuous or the pneumatic mismatch of tail bone, jet pipe, will cause air-flow in switching casing
It is interior to generate biggish performance loss, and then lift fan performance is influenced, especially when the center of jet pipe and the center of fan be not one
When in a axial location, aerodynamic loss is more prominent.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
The purpose of the application there is provided a kind of asymmetric exhaust structure of lift fan, with solve it is of the existing technology extremely
A few problem.
The technical solution of the application is:
A kind of asymmetric exhaust structure of lift fan, comprising: asymmetric tail bone, switching casing and spray, the switching machine
Casket is provided with fairing group section, wherein
One end of the fairing group section is connect with the asymmetric tail bone, and the end and lift fan are coaxial；
The other end of the fairing group section is connect with the jet pipe, and the end and the jet pipe are coaxial；
The middle part of the fairing group section is smooth curved sections.
Optionally, the switching casing is that circle turns square structure, the switching casing connect with the asymmetric tail bone one
End section is rounded, and the end section connecting with the jet pipe is square.
Optionally, the jet pipe is boxlike jet pipe.
Optionally, the jet pipe is adjustable nozzle ring square box structure.
Optionally, the jet pipe is connect with leaf grating vector control system, and the leaf grating vector control system is by changing leaf
Grid turn to the direction for adjusting the jet pipe discharge air-flow.
Optionally, fan outlet channel is formed after the switching casing is connect with the asymmetric tail bone.
Optionally, the both ends of the switching casing are provided with connecting flange.
Optionally, the asymmetric tail bone with the switching casing passes through flanged joint.
Optionally, the jet pipe and the switching casing pass through flanged joint.
Optionally, the switching casing is integrally in convergent contour.
At least there are following advantageous effects in invention:
The asymmetric exhaust structure of the lift fan of the application, it is non-right to be connected using the switching casing for being provided with fairing group section
Claim tail bone and jet pipe, lift fan discharge loss can be reduced, guarantees nozzle performance and fan aeroperformance.
Detailed description of the invention
Fig. 1 is the asymmetric exhaust structure schematic diagram of lift fan of one embodiment of the application.
Wherein:
1- fan outlet channel；2- fan center axis；3- two axial lines distance；The asymmetric tail bone of 4-；5- switching casing；6-
Jet pipe；7- jet pipe central axis.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 couple of the application is described in further details with reference to the accompanying drawing.
This application provides a kind of asymmetric exhaust structures of lift fan, comprising: asymmetric tail bone 4, switching casing 5 and
Jet pipe 6.
Specifically, switching casing 5 is provided with fairing group section, wherein one end of fairing group section and asymmetric tail bone 4 connect
It connects, and the end and lift fan are coaxial；The other end of fairing group section is connect with jet pipe 6, and the end and jet pipe 6 are coaxial；Fairing
The middle part of group section is smooth curved sections.
In the embodiment of the application, switching casing 5 is that circle turns square structure, switching casing 5 and asymmetric tail bone 4
One end section of connection is rounded, and the end section connecting with jet pipe 6 is square.Jet pipe 6 is boxlike jet pipe, is provided with adjustable leaf
Grid square box structure, adjustable nozzle ring square box structure are connect with leaf grating vector control system, and leaf grating vector control system is by changing leaf
Grid turn to the direction that air-flow is discharged in adjustment jet pipe 6.
In the present embodiment, the both ends of switching casing 5 are provided with connecting flange, asymmetric tail bone 4 and jet pipe 6 and switching machine
Casket 5 passes through flanged joint.
In the present embodiment, whole switching casing 5 is in convergent contour, for enhancing fan lift.
As shown in Figure 1, the asymmetric exhaust structure of lift fan in the application, after switching casing 5 is connect with asymmetric tail bone 4
Formed fan outlet channel 1, fan airstream from fan outlet channel 1 enter exhaust structure, transfer casing 5 fairing group section by
Fan center's axis 2 is transitioned into jet pipe central axis 7, so that asymmetric tail bone 4 is provided with the inclined of two axial lines distance 3 to jet pipe 6
Shifting amount.The application can be made by the design of the unsymmetric structure of asymmetric tail bone 4 and the fairing group section of switching casing 5 from wind
The air-flow being discharged in fan exit passageway 1 enters jet pipe 6 with lower loss.
The asymmetric exhaust structure of the lift fan of the application, it is non-right to be connected using the switching casing for being provided with fairing group section
Claim tail bone and jet pipe, lift fan discharge loss can be reduced, guarantees nozzle performance and fan aeroperformance.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of asymmetric exhaust structure of lift fan characterized by comprising asymmetric tail bone (4), switching casing (5) with
And jet pipe (6), the switching casing (5) are provided with fairing group section, wherein
One end of the fairing group section is connect with the asymmetric tail bone (4), and the end and lift fan are coaxial；
The other end of the fairing group section is connect with the jet pipe (6), and the end and the jet pipe (6) are coaxial；
The middle part of the fairing group section is smooth curved sections.
2. the asymmetric exhaust structure of lift fan according to claim 1, which is characterized in that the switching casing (5) is
Circle turns square structure, and the end section that switching casing (5) connect with the asymmetric tail bone (4) is rounded, with the jet pipe
(6) end section connected is square.
3. the asymmetric exhaust structure of lift fan according to claim 2, which is characterized in that the jet pipe (6) is boxlike
Jet pipe.
4. the asymmetric exhaust structure of lift fan according to claim 3, which is characterized in that the jet pipe (6) is adjustable
Leaf grating square box structure.
5. the asymmetric exhaust structure of lift fan according to claim 4, which is characterized in that the jet pipe (6) and leaf grating
Air-flow is discharged by changing the leaf grating steering adjustment jet pipe (6) in vector control system connection, the leaf grating vector control system
Direction.
6. the asymmetric exhaust structure of lift fan according to claim 1, which is characterized in that the switching casing (5) with
Fan outlet channel (1) is formed after asymmetric tail bone (4) connection.
7. the asymmetric exhaust structure of lift fan according to claim 1, which is characterized in that switching casing (5)
Both ends are provided with connecting flange.
8. the asymmetric exhaust structure of lift fan according to claim 7, which is characterized in that the asymmetric tail bone (4)
Pass through flanged joint with the switching casing (5).
9. the asymmetric exhaust structure of lift fan according to claim 8, which is characterized in that the jet pipe (6) with it is described
Switching casing (5) passes through flanged joint.
10. the asymmetric exhaust structure of lift fan according to claim 1, which is characterized in that the switching casing (5) is whole
Body is in convergent contour.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811524186.5A CN109606644A (en) | 2018-12-13 | 2018-12-13 | A kind of asymmetric exhaust structure of lift fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811524186.5A CN109606644A (en) | 2018-12-13 | 2018-12-13 | A kind of asymmetric exhaust structure of lift fan |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109606644A true CN109606644A (en) | 2019-04-12 |
Family
ID=66008474
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811524186.5A Pending CN109606644A (en) | 2018-12-13 | 2018-12-13 | A kind of asymmetric exhaust structure of lift fan |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109606644A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113532837A (en) * | 2021-08-19 | 2021-10-22 | 中国航发贵阳发动机设计研究所 | Test tool structure for verifying pressure of special-shaped spray pipe |
| CN113685272A (en) * | 2021-10-26 | 2021-11-23 | 中国航发四川燃气涡轮研究院 | Asymmetric round-square-turning casing with large-size thin wall |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB844179A (en) * | 1957-10-16 | 1960-08-10 | Rolls Royce | Improvements in or relating to nozzles for jet propulsion purposes |
| US4050631A (en) * | 1976-03-26 | 1977-09-27 | The Boeing Company | Jet engine nozzle for controlling the direction of thrust |
| GB2366265B (en) * | 1995-05-30 | 2002-06-19 | Rolls Royce Plc | Vtol aircraft nozzle |
| CN1465862A (en) * | 2002-06-20 | 2004-01-07 | 王建钧 | Improved end blade guiding propeller |
| CN1530562A (en) * | 2003-03-13 | 2004-09-22 | 尤洛考普特公司 | Connecting flange system for quill shaft |
| CN103448910A (en) * | 2013-08-31 | 2013-12-18 | 西北工业大学 | Aircraft capable of vertically taking off and landing at high speed |
| CN105697194A (en) * | 2014-11-28 | 2016-06-22 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary plug type spray pipe with reactive thrust function |
-
2018
- 2018-12-13 CN CN201811524186.5A patent/CN109606644A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB844179A (en) * | 1957-10-16 | 1960-08-10 | Rolls Royce | Improvements in or relating to nozzles for jet propulsion purposes |
| US4050631A (en) * | 1976-03-26 | 1977-09-27 | The Boeing Company | Jet engine nozzle for controlling the direction of thrust |
| GB2366265B (en) * | 1995-05-30 | 2002-06-19 | Rolls Royce Plc | Vtol aircraft nozzle |
| CN1465862A (en) * | 2002-06-20 | 2004-01-07 | 王建钧 | Improved end blade guiding propeller |
| CN1530562A (en) * | 2003-03-13 | 2004-09-22 | 尤洛考普特公司 | Connecting flange system for quill shaft |
| CN103448910A (en) * | 2013-08-31 | 2013-12-18 | 西北工业大学 | Aircraft capable of vertically taking off and landing at high speed |
| CN105697194A (en) * | 2014-11-28 | 2016-06-22 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary plug type spray pipe with reactive thrust function |
Non-Patent Citations (1)
| Title |
|---|
| 高丽敏，马驰，李瑞宇: "F-35B对转升力风扇研究进展", 《风机技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113532837A (en) * | 2021-08-19 | 2021-10-22 | 中国航发贵阳发动机设计研究所 | Test tool structure for verifying pressure of special-shaped spray pipe |
| CN113685272A (en) * | 2021-10-26 | 2021-11-23 | 中国航发四川燃气涡轮研究院 | Asymmetric round-square-turning casing with large-size thin wall |
| CN113685272B (en) * | 2021-10-26 | 2021-12-24 | 中国航发四川燃气涡轮研究院 | Asymmetric round-square-turning casing with large-size thin wall |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190412 |