CN109606709A - A kind of exhaust pipe mounting structure for helicopter - Google Patents

A kind of exhaust pipe mounting structure for helicopter Download PDF

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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
Application number
CN201811355600.4A
Other languages
Chinese (zh)
Inventor
张宇沛
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
China Helicopter Research and Development Institute
Original Assignee
China Helicopter Research and Development Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by China Helicopter Research and Development Institute filed Critical China Helicopter Research and Development Institute
Priority to CN201811355600.4A priority Critical patent/CN109606709A/en
Publication of CN109606709A publication Critical patent/CN109606709A/en
Pending legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes

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  • 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

A kind of exhaust pipe mounting structure for helicopter
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).
CN201811355600.4A 2018-11-14 2018-11-14 A kind of exhaust pipe mounting structure for helicopter Pending CN109606709A (en)

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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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

Patent Citations (8)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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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Application publication date: 20190412