CN107503860B - A kind of high temperature resistant jet pipe - Google Patents

A kind of high temperature resistant jet pipe Download PDF

Info

Publication number
CN107503860B
CN107503860B CN201710531153.2A CN201710531153A CN107503860B CN 107503860 B CN107503860 B CN 107503860B CN 201710531153 A CN201710531153 A CN 201710531153A CN 107503860 B CN107503860 B CN 107503860B
Authority
CN
China
Prior art keywords
nozzle
exhaust pipe
support frame
pipe
spray piece
Prior art date
Application number
CN201710531153.2A
Other languages
Chinese (zh)
Other versions
CN107503860A (en
Inventor
张和平
汪雷
张锐
Original Assignee
芜湖市海联机械设备有限公司
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 芜湖市海联机械设备有限公司 filed Critical 芜湖市海联机械设备有限公司
Priority to CN201710531153.2A priority Critical patent/CN107503860B/en
Publication of CN107503860A publication Critical patent/CN107503860A/en
Application granted granted Critical
Publication of CN107503860B publication Critical patent/CN107503860B/en

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78Other construction of jet pipes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78Other construction of jet pipes
    • F02K1/82Jet pipe walls, e.g. liners

Abstract

The invention discloses a kind of high temperature resistant jet pipes, including exhaust pipe, inner nozzle, tail spray piece, the first support frame, the second support frame, semicircle buckle, fixing hoop and fixed screw, inner nozzle is equipped in the exhaust pipe, the left hand external of the inner nozzle is equipped with circular baffle plate, circular baffle plate is blocked at the port of exhaust pipe, and exhaust pipe left end and inner nozzle be fixedly connected by fixed screw, the first support frame of middle part of the inner nozzle and the second support frame are fixedly connected with exhaust inside pipe wall respectively, and the right end of the exhaust pipe is equipped with a tail spray piece.High temperature resistant jet pipe of the invention; design is reasonable; equipped with inner nozzle and tail spray piece; the inner nozzle is made of titanium alloy material resistant to high temperature; it can not only work long hours under severe working environment; and since the unique profile structure of inner nozzle can provide bigger power for entire turbogenerator, while it being equipped with flexible tail spray piece, entire jet pipe can be effectively protected.

Description

A kind of high temperature resistant jet pipe
Technical field
The present invention relates to a kind of jet pipe more particularly to a kind of high temperature resistant jet pipes.
Background technique
Jet pipe is one of component part of turbojet engine of jet plane, and main function is to fire jet plane Product such as carbon dioxide, sulfur dioxide, carbon monoxide, nitrogen oxides, imperfect combustion small molecule hydrocarbon after oil firing Matter ejects, and plays the role of waste air, while also pushing aircraft using the reaction force that air when injection generates, but In turboprop, jet pipe provide thrust be aircraft power a part, the main power of aircraft be by The driving propeller of turboprop provides.
A kind of high temperature resistant jet pipe is now provided, design rationally, is equipped with inner nozzle and tail spray piece, which uses high temperature resistant Titanium alloy material be made, can not only work long hours under severe working environment, and due to the unique profile of inner nozzle Structure can provide bigger power for entire turbogenerator, while be equipped with flexible tail spray piece, can be effectively protected entire Jet pipe.
Summary of the invention
The purpose of the present invention is to provide high temperature resistant jet pipes, to solve the problems mentioned in the above background technology.
The purpose of the present invention is be achieved by following technical proposals: a kind of high temperature resistant jet pipe, including exhaust pipe, interior Jet pipe, tail spray piece, the first support frame, the second support frame, semicircle buckle, fixing hoop and fixed screw, in the exhaust pipe Equipped with inner nozzle, the left hand external of the inner nozzle is equipped with block plate, and circular baffle plate is blocked at the port of exhaust pipe, and exhaust pipe Left end and inner nozzle are fixedly connected by fixed screw, the first support frame of middle part of the inner nozzle and the second support frame point It is not fixedly connected with exhaust inside pipe wall, the right end of the exhaust pipe is equipped with a tail spray piece, and the left end of the tail spray piece passes through semicircle Buckle is connect with the tail portion of exhaust pipe, and the tail portion junction of exhaust pipe is correspondingly provided with fixing hoop.
Further, the tail spray piece is flexible tail spray piece.
Further, the shape of the inner nozzle is in goblet shape, and cup body knee two sides are respectively equipped with the first support The fixed angle of frame and the second support frame, first support frame and right side exhaust inside pipe wall is spent for 120 degree -160, and described second The fixed angle of support frame and right side exhaust inside pipe wall is 35 degree of -65 degree.
Further, the exhaust pipe tail portion is equipped with circle semicircle card slot corresponding with semicircle buckle.
Further, the inner nozzle is made of titanium alloy material.
Compared with prior art, the beneficial effects of the invention are as follows the high temperature resistant jet pipe of the invention, design rationally, is equipped with interior Jet pipe and tail spray piece, the inner nozzle are made of titanium alloy material resistant to high temperature, can not only be grown under severe working environment Time service, and since the unique profile structure of inner nozzle can provide bigger power for entire turbogenerator, it sets simultaneously There is flexible tail spray piece, entire jet pipe can be effectively protected.
Detailed description of the invention
Fig. 1 is high temperature resistant jet pipe overall effect figure of the present invention;
Fig. 2 is high temperature resistant jet pipe overall structure figure of the present invention;
In figure: 1, exhaust pipe, 2, inner nozzle, 3, tail spray piece, the 4, first support frame, the 5, second support frame, 6, semicircle buckle, 7, fixing hoop, 8, fixed screw.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments, is based on Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other Embodiment shall fall within the protection scope of the present invention.
As shown in Figs. 1-2, the invention discloses a kind of high temperature resistant jet pipe, including exhaust pipe 1, inner nozzle 2, tail spray piece 3, First support frame 4, the second support frame 5, semicircle buckle 6, fixing hoop 7 and fixed screw 8, the exhaust pipe 1 are interior equipped with interior The left end of jet pipe 2, the inner nozzle 2 is equipped with block plate, and circular baffle plate is blocked at the port of exhaust pipe 1, and a left side for exhaust pipe 1 End is fixedly connected with inner nozzle 2 by fixed screw 8, middle part the first support frame 4 of the inner nozzle 2 and the second support frame 5 are fixedly connected with 1 inner wall of exhaust pipe respectively, and the right end of the exhaust pipe 1 is equipped with a tail spray piece 3, and the left end of the tail spray piece 3 is logical It crosses semicircle buckle 6 to connect with the tail portion of exhaust pipe 1, and the tail portion junction of exhaust pipe 1 is correspondingly provided with fixing hoop 7, passes through card Hoop 7 connects exhaust pipe 1 and tail spray piece 3 stronger.
Tail spray piece 3 in the present invention is flexible tail spray piece, and entire jet pipe can be effectively protected;The inner nozzle 2 Shape be in goblet shape, and cup body knee two sides are respectively equipped with the first support frame 4 and the second support frame 5, first support The fixed angle of frame 4 and 1 inner wall of right side exhaust pipe is 120 degree of -160 degree, second support frame 5 and 1 inner wall of right side exhaust pipe Fixed angle be 35 degree -65 degree, fix inner nozzle 2 and exhaust pipe 1 and be linked together, keep entire jet pipe more stable.Institute 1 tail portion of exhaust pipe stated is equipped with a circle and buckles 6 corresponding semicircle card slots with semicircle.The inner nozzle 2 uses titanium alloy material It is made, can not only work long hours under severe working environment, and since the unique profile structure of inner nozzle can be whole A turbogenerator provides bigger power.
The high temperature resistant jet pipe of the invention, design rationally, are equipped with inner nozzle and tail spray piece, the inner nozzle is using resistant to high temperature Titanium alloy material is made, and can not only work long hours under severe working environment, and due to the unique profile knot of inner nozzle Structure can provide bigger power for entire turbogenerator, while be equipped with flexible tail spray piece, and entire tail can be effectively protected Jet pipe.
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, Er Qie In the case where without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter From the point of view of which point, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power Benefit requires rather than above description limits, it is intended that all by what is fallen within the meaning and scope of the equivalent elements of the claims Variation is included within the present invention.Any reference signs in the claims should not be construed as limiting the involved claims.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should It considers the specification as a whole, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art The other embodiments being understood that.

Claims (4)

1. a kind of high temperature resistant jet pipe, it is characterised in that: including exhaust pipe (1), inner nozzle (2), tail spray piece (3), the first support Frame (4), the second support frame (5), semicircle buckle (6), fixing hoop (7) and fixed screw (8), the exhaust pipe (1) is interior to be set Having inner nozzle (2), the left hand external of the inner nozzle (2) is equipped with block plate, and circular baffle plate is blocked at the port of exhaust pipe (1), and The left end of exhaust pipe (1) is fixedly connected with inner nozzle (2) by fixed screw (8), the middle part first of the inner nozzle (2) Support frame (4) and the second support frame (5) are fixedly connected with exhaust pipe (1) inner wall respectively, and the right end of the exhaust pipe (1) is equipped with one The left end of tail spray piece (3), the tail spray piece (3) is connect by semicircle buckle (6) with the tail portion of exhaust pipe (1), and exhaust pipe (1) Tail portion junction be correspondingly provided with fixing hoop (7), the shape of the inner nozzle (2) is in goblet shape, and cup body knee two Side is respectively equipped with the first support frame (4) and the second support frame (5), first support frame (4) and right side exhaust pipe (1) inner wall Fixed angle is 120 degree -160 and spends that the fixed angle of second support frame (5) and right side exhaust pipe (1) inner wall is 35 degree -65 Degree.
2. a kind of high temperature resistant jet pipe according to claim 1, it is characterised in that: the tail spray piece (3) is flexible tail Spray piece.
3. a kind of high temperature resistant jet pipe according to claim 1, it is characterised in that: described exhaust pipe (1) tail portion is equipped with One circle semicircle card slot corresponding with semicircle buckle (6).
4. a kind of high temperature resistant jet pipe according to claim 1, it is characterised in that: the inner nozzle (2) is closed using titanium Golden material is made.
CN201710531153.2A 2017-07-03 2017-07-03 A kind of high temperature resistant jet pipe CN107503860B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710531153.2A CN107503860B (en) 2017-07-03 2017-07-03 A kind of high temperature resistant jet pipe

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710531153.2A CN107503860B (en) 2017-07-03 2017-07-03 A kind of high temperature resistant jet pipe

Publications (2)

Publication Number Publication Date
CN107503860A CN107503860A (en) 2017-12-22
CN107503860B true CN107503860B (en) 2019-09-03

Family

ID=60679662

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710531153.2A CN107503860B (en) 2017-07-03 2017-07-03 A kind of high temperature resistant jet pipe

Country Status (1)

Country Link
CN (1) CN107503860B (en)

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN2095201U (en) * 1991-06-29 1992-02-05 中国科学院化工冶金研究所 Premixing type coal oxygen mine fusion agent spray gun
CN1532395A (en) * 2003-03-18 2004-09-29 浦晓亭 AIr jet engine attached device
CN101633081A (en) * 2008-12-29 2010-01-27 北京智创联合科技有限公司 Manufacturing of composite sandwich nozzle by dynamic pressurizing transient liquid phase diffusion welding
CN101737200A (en) * 2008-11-10 2010-06-16 北京航空航天大学 Modularized heat-capacity type thrust chamber
KR20120027864A (en) * 2010-09-13 2012-03-22 국방과학연구소 Nozzle device exposed in high temperature and high velocity gas and rocket having the same
CN104963789A (en) * 2015-07-11 2015-10-07 杜善骥 Working method of Laval nozzle effect stamping oxygen production rocket
CN205048446U (en) * 2015-08-11 2016-02-24 河南汇金智能装备有限公司 Durable burner nozzle
CN105773082A (en) * 2016-05-10 2016-07-20 南京航空航天大学 Manufacturing method of engine composite exhaust nozzle
CN104493033B (en) * 2014-10-31 2016-08-17 西北有色金属研究院 A kind of integral forming technique of TC4 titanium alloy jet pipe
CN206206011U (en) * 2016-10-31 2017-05-31 北京航天动力研究所 A kind of liquid rocket engine thrust chamber sandwich for strengthening bushing with throat

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN2095201U (en) * 1991-06-29 1992-02-05 中国科学院化工冶金研究所 Premixing type coal oxygen mine fusion agent spray gun
CN1532395A (en) * 2003-03-18 2004-09-29 浦晓亭 AIr jet engine attached device
CN101737200A (en) * 2008-11-10 2010-06-16 北京航空航天大学 Modularized heat-capacity type thrust chamber
CN101633081A (en) * 2008-12-29 2010-01-27 北京智创联合科技有限公司 Manufacturing of composite sandwich nozzle by dynamic pressurizing transient liquid phase diffusion welding
KR20120027864A (en) * 2010-09-13 2012-03-22 국방과학연구소 Nozzle device exposed in high temperature and high velocity gas and rocket having the same
CN104493033B (en) * 2014-10-31 2016-08-17 西北有色金属研究院 A kind of integral forming technique of TC4 titanium alloy jet pipe
CN104963789A (en) * 2015-07-11 2015-10-07 杜善骥 Working method of Laval nozzle effect stamping oxygen production rocket
CN205048446U (en) * 2015-08-11 2016-02-24 河南汇金智能装备有限公司 Durable burner nozzle
CN105773082A (en) * 2016-05-10 2016-07-20 南京航空航天大学 Manufacturing method of engine composite exhaust nozzle
CN206206011U (en) * 2016-10-31 2017-05-31 北京航天动力研究所 A kind of liquid rocket engine thrust chamber sandwich for strengthening bushing with throat

Also Published As

Publication number Publication date
CN107503860A (en) 2017-12-22

Similar Documents

Publication Publication Date Title
JP6290911B2 (en) Aircraft propelled by turbojet engine with counter rotating fan
US9599411B2 (en) Double-jet type film cooling structure
EP2862805B1 (en) Propulsion system nacelle with reduced number of external split lines
CN106368742B (en) For docking ceramic base composite material member to the method and system of hardware
ES2292685T5 (en) Double air inlet from a reactor
JP2017122445A (en) Cooling circuit for multi-wall blade
Lee et al. HH 212: Submillimeter array observations of a remarkable protostellar jet
JP2016509651A (en) Energy efficiency improvement device for turbomachinery
JP2008190534A (en) Gas turbine with hp and lp counter-rotating turbines
CN107521705B (en) Assembly for an aircraft comprising an engine with boundary layer suction propulsion
EP2586499A3 (en) Automatic fire extinguishing system with gaseous and dry powder fire suppression agents
US8757969B2 (en) Turbine exhaust plenum
RU2014113393A (en) ASSEMBLY FORMED BY THE TURBINE GUIDING NOZZLE DEVICE OR THE KKM COMPRESSOR REDUCING DEVICE FOR THE TURBO MACHINE AND THE RING - SUBSTRATE FOR THE WIPEABLE MATERIAL, AND THE TURBISHER IS COMPLETE
JP5967929B2 (en) A vane with a composite airfoil attached to a spar
EP3273010B1 (en) Mid-turbine frame
EP2228602A3 (en) Combustor liner cooling system
EP3043056B1 (en) Exhaust duct for a gas turbine engine
JP6026739B2 (en) A vane with a composite airfoil attached to a spar
DE60105531D1 (en) Gas turbine combustor, gas turbine and jet engine
EP2246628A3 (en) Fuel spray apparatus for gas turbine engine
RU2009117418A (en) Gondola for two-circuit turboreactive engine
MY138366A (en) Turbine vane collar seal
FR2980770B1 (en) AIRBORNE TURBINE ENGINE (S) FOR AIRCRAFT WITH SYSTEM FOR CHANGING THE PROPELLER STEP.
EP2184447A3 (en) A noise reduction device
CN104048324B (en) A kind of vapor flame holder

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
GR01 Patent grant
GR01 Patent grant