CN104002967A - Fluid director structure of airplane engine nacelle - Google Patents
Fluid director structure of airplane engine nacelle Download PDFInfo
- Publication number
- CN104002967A CN104002967A CN201410192985.2A CN201410192985A CN104002967A CN 104002967 A CN104002967 A CN 104002967A CN 201410192985 A CN201410192985 A CN 201410192985A CN 104002967 A CN104002967 A CN 104002967A
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- CN
- China
- Prior art keywords
- ring
- ring body
- flap
- installation
- installation ring
- 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.)
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- 239000012530 fluid Substances 0.000 title abstract 4
- 238000009434 installation Methods 0.000 claims abstract description 44
- 238000010586 diagram Methods 0.000 description 4
- 238000003032 molecular docking Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- Wind Motors (AREA)
Abstract
The invention discloses a fluid director structure of an airplane engine. The fluid director structure comprises a diversion vane and an installation ring. The diversion vane is a triangular wing-shaped structure, one side of the triangular wing-shaped structure is open and the other side of the triangular wing-shaped structure is fixed to the airplane body. The front end of the diversion vane is in an abutting joint relationship with the installation ring so that an integral structure is formed. The fluid director structure is characterized in that the installation ring is a detachable structure and comprises an upper ring and a lower ring, the front end of the diversion vane is in a fixed abutting joint relationship with the upper ring, and the diversion vane is detachable from the lower ring.
Description
Technical field
The present invention relates to aeroplane structure design, be specifically applied to the flow-guiding device structure design of aero-engine nacelle.
Background technology
Its topology layout of engine nacelle according to driving engine installation site, change that requirement, daily attention require and other related requests carry out comprehensive Design, its structure is comprised of driving engine hanging, nacelle skeleton, lid, air deflector; Skeleton is comprised of frame, beam, side plate part, outside face by a plurality of large-scale fast opens begin to speak lid and bottom rectification form.
Air deflector is the continuity of aero-engine nacelle and is comprised of flap and installation ring; it is in the periphery of engine tail nozzle; the exhaust of driving engine is played certain valve action and protected fuselage lateral margin to avoid from the infringement of the hot gas of engine tail nozzle ejection; because installation ring is enclosed in the periphery of driving engine; so during dismounting driving engine; must remove installation ring; after driving engine installation; installation ring could be installed, so the quality of installation ring dismounting property directly has influence on used time and the difficulty or ease that driving engine is changed.
In traditional integral type flow-guiding device structure, there is following problem:
While installing due to driving engine, adopt vertical lifting, during dismounting driving engine, must first remove installation ring, and the prerequisite that removes and installs ring is first to dismantle flap, and installation ring and flap volume and quality are all larger, during assembling, use screw more, so increased the work capacity of a lot of dismountings, installation, to more reengining and have a significant impact.
Summary of the invention
The object of the present invention is to provide a kind of flow-guiding device structure of aero-engine nacelle, can solve and more reengine in process, the problem that air deflector dismounting, installation run into.
A kind of flow-guiding device structure of aero-engine, described air deflector is comprised of flap and installation ring, flap is a triangle body wings, one side is opened wide, and opposite side is fixed on airframe, and the front end of flap docks and is structure as a whole with installation ring, it is characterized in that described installation ring is a detachable structure, upper ring body and lower ring body, consist of, the fore-end of flap is fixedly docked on upper ring body, is also detachable structure between flap and lower ring body.
The upper lower ring body of described installation ring is comprised of curved ring frame forming of plate, grooved frame and long purlin and covering, and upper ring body and lower ring body are detachably connected by attaching parts.And attaching parts is comprised of covering abutting plate, docking angle section, frame abutting plate, during assembling, attaching parts is riveted together with rivet and installation ring upper ring body, between attaching parts and installation ring lower ring body, adopt screw to be connected with plate nut, for removably connecting.
The application's beneficial effect is: can independent dismounting between installation ring and flap, reduced the quantity of dismounting member, and can actv. improve driving engine and change efficiency, the work capacity of reduce dismounting, installing.
Below in conjunction with specific embodiment and accompanying drawing, this application is described in further detail:
Accompanying drawing explanation
Fig. 1 is engine nacelle flow-guiding device structure schematic diagram
Fig. 2 is the upper and lower ring body separation relation schematic diagram of installation ring
Fig. 3 is the lower ring body of installation ring and the separation relation schematic diagram of air deflector
Number description: 1, engine nacelle frame; 2, upper ring body; 3, lower ring body; 4, covering abutting plate; 5, guide ring covering abutting plate; 6, frame abutting plate; 7, docking angle section; 8, flap; 9, airframe; 10, driving engine;
Specific embodiment
Referring to accompanying drawing, the air deflector of aero-engine is comprised of flap 8 and installation ring, flap is a triangle body wings, one side is opened wide, and opposite side is fixed on airframe 9, and the front end of flap 8 docks and is structure as a whole with installation ring, in enforcement, installation ring is a detachable structure, upper ring body 2 and lower ring body 3, consist of, the fore-end of flap 8 is fixedly docked on upper ring body 2, between flap 8 and lower ring body 3, is also detachable structure.
In Fig. 2, on installation ring, the structure type of attachment of lower ring body inner side is: covering abutting plate 4 is by rivet and installation ring upper ring body place covering riveting, frame abutting plate 6 is by rivet and 2 riveted joints of installation ring upper ring body, and installation ring lower ring body place covering is formed and removably connected by plate nut, screw and covering abutting plate 4, frame abutting plate 6.
In Fig. 2, on installation ring, the structure type of attachment in lower ring body outside is: guide ring covering abutting plate 5 passes through rivet with installation ring upper ring body guide ring place covering, docking angle section 7 is with installation ring upper ring body guide ring place L-type material by rivet, and installation ring lower ring body guide ring place covering is formed and removably connected by plate nut, screw and covering abutting plate 5, butted section bars 7.
Figure 3 shows that installation ring lower ring body 3 pulls down rear schematic diagram from the body having assembled, the two place's screws that during dismounting, installation ring lower ring body 3 are connected with installation ring upper ring body and the screw being connected with flap 8, engine nacelle frame, fuselage are backed out, then installation ring lower ring body 3 is downward, outwards (away from fuselage direction) is mobile again, just installation ring lower ring body 3 can be taken off; And installation ring, flap 8 all need be disassembled from aircraft need not dismantle as integral type air deflector time, reduced to a great extent the work capacity of assembling, dismounting, improved the efficiency of more reengining.
Claims (2)
1. the flow-guiding device structure of an aero-engine, described air deflector is comprised of flap and installation ring, flap is a triangle body wings, one side is opened wide, and opposite side is fixed on airframe, and the front end of flap docks and is structure as a whole with installation ring, it is characterized in that described installation ring is a detachable structure, upper ring body and lower ring body, consist of, the fore-end of flap is fixedly docked on upper ring body, is also detachable structure between flap and lower ring body.
2. the flow-guiding device structure of aero-engine as claimed in claim 1, the upper lower ring body that it is characterized in that described installation ring is comprised of curved ring frame forming of plate, grooved frame and long purlin and covering, and upper ring body and lower ring body are detachably connected by attaching parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410192985.2A CN104002967A (en) | 2014-05-08 | 2014-05-08 | Fluid director structure of airplane engine nacelle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410192985.2A CN104002967A (en) | 2014-05-08 | 2014-05-08 | Fluid director structure of airplane engine nacelle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104002967A true CN104002967A (en) | 2014-08-27 |
Family
ID=51363931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410192985.2A Pending CN104002967A (en) | 2014-05-08 | 2014-05-08 | Fluid director structure of airplane engine nacelle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104002967A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4173960A1 (en) * | 2021-10-28 | 2023-05-03 | Honeywell International Inc. | Pylon system for coupling engine to vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5906097A (en) * | 1997-03-28 | 1999-05-25 | The Boeing Company | Engine flow control device |
| US6983912B2 (en) * | 2002-04-30 | 2006-01-10 | The Boeing Company | Hybrid exhaust heat shield for pylon mounted gas turbine engines |
| US20090098321A1 (en) * | 2007-10-11 | 2009-04-16 | The Boeing Company | Composite Heat Shield |
| WO2010062494A1 (en) * | 2008-11-26 | 2010-06-03 | Mra Systems, Inc. | Nacelle and method of assembling the same |
| CN103204235A (en) * | 2013-04-24 | 2013-07-17 | 哈尔滨飞机工业集团有限责任公司 | Locking mechanism for radome |
-
2014
- 2014-05-08 CN CN201410192985.2A patent/CN104002967A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5906097A (en) * | 1997-03-28 | 1999-05-25 | The Boeing Company | Engine flow control device |
| US6983912B2 (en) * | 2002-04-30 | 2006-01-10 | The Boeing Company | Hybrid exhaust heat shield for pylon mounted gas turbine engines |
| US20090098321A1 (en) * | 2007-10-11 | 2009-04-16 | The Boeing Company | Composite Heat Shield |
| WO2010062494A1 (en) * | 2008-11-26 | 2010-06-03 | Mra Systems, Inc. | Nacelle and method of assembling the same |
| CN103204235A (en) * | 2013-04-24 | 2013-07-17 | 哈尔滨飞机工业集团有限责任公司 | Locking mechanism for radome |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4173960A1 (en) * | 2021-10-28 | 2023-05-03 | Honeywell International Inc. | Pylon system for coupling engine to vehicle |
| US12024305B2 (en) | 2021-10-28 | 2024-07-02 | Honeywell International Inc. | Pylon system for coupling engine to vehicle |
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| 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: 20140827 |