CN109606709A - A kind of exhaust pipe mounting structure for helicopter - Google Patents
A kind of exhaust pipe mounting structure for helicopter Download PDFInfo
- Publication number
- CN109606709A CN109606709A CN201811355600.4A CN201811355600A CN109606709A CN 109606709 A CN109606709 A CN 109606709A CN 201811355600 A CN201811355600 A CN 201811355600A CN 109606709 A CN109606709 A CN 109606709A
- Authority
- CN
- China
- Prior art keywords
- jet pipe
- connect
- engine
- injection section
- helicopter
- 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
- 238000002347 injection Methods 0.000 claims abstract description 16
- 239000007924 injection Substances 0.000 claims abstract description 16
- 239000010425 asbestos Substances 0.000 claims description 4
- 239000004744 fabric Substances 0.000 claims description 4
- 229910052895 riebeckite Inorganic materials 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000009423 ventilation Methods 0.000 abstract description 3
- 239000000243 solution Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Exhaust Silencers (AREA)
Abstract
This application provides a kind of engine exhaust pipe mounting structures for helicopter comprising central tube, main jet pipe and mixing tube, the central tube are connect with engine, and the main jet pipe is connect by clip with engine；The mixing tube includes injection section and second level jet pipe, and injection section one end is connect with firewall after piggyback pod, and the injection section other end and the second level jet pipe overlap, and the second level jet pipe is connect by the cornual plate being fixed on exhaust cabin radome fairing with airframe structure.The exhaust pipe mounting structure for helicopter of the application can guarantee that under all flight conditions, exhaust system can work normally, and meet the requirement of piggyback pod ventilation quantity, effectively reduce nuisance vibration, dismounting, operation and maintenance convenient for exhaust pipe；Meet structural intergrity design requirement.
Description
Technical field
The application belongs to helicopter structure design field, in particular to a kind of exhaust pipe for helicopter installs knot
Structure.
Background technique
Engine exhaust system is that the tail gas of engine emission is exported extra-organismal system.The exhaust pipe of engine both needs full
The exhaust requirements of sufficient engine consider the ventilating and cooling of piggyback pod again.On the basis of determining aerodynamic configuration, mixing tube is in machine
On mounting means must pay attention to.For traditional installation method by exhaust pipe support, except need to consider to vibration water
Flat control also needs to consider the influence that severe temperature environment generates stent fatigue life.Simultaneously as exhaust pipe and bracket
Tie point is located in exhaust cabin radome fairing, how under the premise of not dismantling radome fairing, realizes the dismounting and maintenance to exhaust pipe
Also it must pay attention to.
Summary of the invention
There is provided a kind of engine exhaust pipe mounting structures for helicopter for the purpose of the application, to solve above-mentioned
One problem.
The technical solution of the application is: a kind of engine exhaust pipe mounting structure for helicopter comprising central tube,
Main jet pipe and mixing tube, the central tube are connect with engine, and the main jet pipe is connect by clip with engine；The mixing
Pipe includes injection section and second level jet pipe, and injection section one end connect with firewall after piggyback pod, the injection section other end and
The second level jet pipe overlap joint, the second level jet pipe are connect by the cornual plate being fixed on exhaust cabin radome fairing with airframe structure.
In this application, there is asbestos cloth between the injection section and the second level jet pipe.
The exhaust pipe mounting structure for helicopter of the application can guarantee under all flight conditions, exhaust system energy
It is enough to work normally, meet the requirement of piggyback pod ventilation quantity, effectively reduce nuisance vibration, convenient for exhaust pipe dismounting, use and tie up
Shield；Meet structural intergrity design requirement.
Detailed description of the invention
In order to illustrate more clearly of technical solution provided by the present application, attached drawing will be briefly described below.It is aobvious and easy
Insight, drawings discussed below are only some embodiments of the present application.
Fig. 1 is the exhaust pipe mounting structure schematic diagram of the application.
Fig. 2 is that the mixing tube of the application dismantles schematic diagram.
Appended drawing reference:
1- central tube, 2- clip, 3- main jet pipe, 4- injection section, 5- asbestos cloth, 6- second level jet pipe, 7- cornual plate, 8- piggyback pod
Firewall afterwards, 9- exhaust cabin radome fairing, 10- bolt, 11- gasket, 12- nut.
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 description of the present application, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is that orientation based on the figure or position are closed
System is merely for convenience of description the application and simplifies description, rather than the device or element of indication or suggestion meaning must have
Specific orientation is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application protection scope.
As shown in Figure 1, this application provides a kind of engine exhaust pipe mounting structure for helicopter, engine exhaust
Pipe mounting structure includes central tube 1, main jet pipe 3, mixing tube, and central tube 1 is directly connected to engine, and main jet pipe 3 passes through clip 2
It is directly connected to engine.Mixing tube includes injection section 4 and second level jet pipe 6, after 4 left end of injection section is by installation side and piggyback pod
Firewall 8 connects, and 4 right end of injection section and second level jet pipe 6 overlap.The middle part of second level jet pipe 6 is by being fixed on exhaust cabin radome fairing 9
On cornual plate 7 connect with airframe structure.
In this application, there is asbestos cloth 5 between injection section 4 and second level jet pipe 6, can prevent fires.
As shown in Fig. 2, need to only unclamp the angle on second level jet pipe 6 and radome fairing when dismantling to the exhaust pipe of engine
The connection of bolt 10, gasket 11 and nut 12 between piece 7, can be by second level jet pipe from the opening on exhaust cabin radome fairing 9
The disassembly to mixing tube is completed in extraction.
The engine exhaust pipe mounting structure of the application is able to achieve exhaust system and can work normally, and meets piggyback pod ventilation
The requirement of amount, while nuisance vibration is effectively reduced, dismounting, operation and maintenance convenient for exhaust pipe meet structural intergrity design
It is required that.
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 (2)
1. a kind of engine exhaust pipe mounting structure for helicopter, which is characterized in that including central tube (1), main jet pipe (3)
And mixing tube, the central tube (1) connect with engine, the main jet pipe (3) is connect by clip (2) with engine；It is described
Mixing tube includes injection section (4) and second level jet pipe (6), and described injection section (4) one end is connect with firewall after piggyback pod (8), institute
It states injection section (4) other end and the second level jet pipe (6) overlaps, the second level jet pipe (6) is by being fixed on exhaust cabin radome fairing
(9) cornual plate (7) on is connect with airframe structure.
2. being used for the engine exhaust pipe mounting structure of helicopter as described in claim 1, which is characterized in that the injection section
(4) have between the second level jet pipe (6) asbestos cloth (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811355600.4A CN109606709A (en) | 2018-11-14 | 2018-11-14 | A kind of exhaust pipe mounting structure for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811355600.4A CN109606709A (en) | 2018-11-14 | 2018-11-14 | A kind of exhaust pipe mounting structure for helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109606709A true CN109606709A (en) | 2019-04-12 |
Family
ID=66003466
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811355600.4A Pending CN109606709A (en) | 2018-11-14 | 2018-11-14 | A kind of exhaust pipe mounting structure for helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109606709A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110877746A (en) * | 2019-12-09 | 2020-03-13 | 中航沈飞民用飞机有限责任公司 | Auxiliary power device blast pipe supports supporting device |
| CN112160804A (en) * | 2020-09-25 | 2021-01-01 | 中国直升机设计研究所 | Engine exhaust pipe fairing |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6109562A (en) * | 1998-04-22 | 2000-08-29 | Pratt & Whitney Canada Corp. | Aircraft construction |
| CN102689691A (en) * | 2011-03-18 | 2012-09-26 | 奥格斯塔韦斯兰股份公司 | Aircraft capable of hovering |
| CN106988850A (en) * | 2017-03-15 | 2017-07-28 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft engine blast pipe and the aircraft with it |
| CN107878764A (en) * | 2017-11-29 | 2018-04-06 | 中国直升机设计研究所 | A kind of radome fairing fire wall blast pipe whole slide structure |
| CN108087147A (en) * | 2017-11-29 | 2018-05-29 | 中国直升机设计研究所 | A kind of non-homogeneous injection ejector exhaust pipe |
| FR3059301A1 (en) * | 2016-11-29 | 2018-06-01 | Safran Power Units | EXHAUST SYSTEM OF AN AUXILIARY POWER MOTOR |
| CN207568685U (en) * | 2017-12-03 | 2018-07-03 | 中国直升机设计研究所 | A kind of helicopter exhaust system |
| CN108625964A (en) * | 2017-03-16 | 2018-10-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of exhaust pipe of engine and the aircraft with it |
-
2018
- 2018-11-14 CN CN201811355600.4A patent/CN109606709A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6109562A (en) * | 1998-04-22 | 2000-08-29 | Pratt & Whitney Canada Corp. | Aircraft construction |
| CN102689691A (en) * | 2011-03-18 | 2012-09-26 | 奥格斯塔韦斯兰股份公司 | Aircraft capable of hovering |
| FR3059301A1 (en) * | 2016-11-29 | 2018-06-01 | Safran Power Units | EXHAUST SYSTEM OF AN AUXILIARY POWER MOTOR |
| CN106988850A (en) * | 2017-03-15 | 2017-07-28 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft engine blast pipe and the aircraft with it |
| CN108625964A (en) * | 2017-03-16 | 2018-10-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of exhaust pipe of engine and the aircraft with it |
| CN107878764A (en) * | 2017-11-29 | 2018-04-06 | 中国直升机设计研究所 | A kind of radome fairing fire wall blast pipe whole slide structure |
| CN108087147A (en) * | 2017-11-29 | 2018-05-29 | 中国直升机设计研究所 | A kind of non-homogeneous injection ejector exhaust pipe |
| CN207568685U (en) * | 2017-12-03 | 2018-07-03 | 中国直升机设计研究所 | A kind of helicopter exhaust system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110877746A (en) * | 2019-12-09 | 2020-03-13 | 中航沈飞民用飞机有限责任公司 | Auxiliary power device blast pipe supports supporting device |
| CN110877746B (en) * | 2019-12-09 | 2023-02-10 | 中航沈飞民用飞机有限责任公司 | Auxiliary power device blast pipe supports supporting device |
| CN112160804A (en) * | 2020-09-25 | 2021-01-01 | 中国直升机设计研究所 | Engine exhaust pipe fairing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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 |