CN206519268U - Aero-engine washer jet and purging system - Google Patents

Aero-engine washer jet and purging system Download PDF

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Publication number
CN206519268U
CN206519268U CN201621448572.7U CN201621448572U CN206519268U CN 206519268 U CN206519268 U CN 206519268U CN 201621448572 U CN201621448572 U CN 201621448572U CN 206519268 U CN206519268 U CN 206519268U
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CN
China
Prior art keywords
engine
aero
nozzle
washer jet
airscoop shroud
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Active
Application number
CN201621448572.7U
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Chinese (zh)
Inventor
颜维
马立恒
郭攀峰
刘鹏
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AECC South Industry Co Ltd
Original Assignee
China National South Aviation Industry Co Ltd
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Publication date
Application filed by China National South Aviation Industry Co Ltd filed Critical China National South Aviation Industry Co Ltd
Priority to CN201621448572.7U priority Critical patent/CN206519268U/en
Application granted granted Critical
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Abstract

The utility model discloses a kind of aero-engine washer jet and purging system, the washer jet includes nozzle body and is used for the support plate of installation on nozzle body, nozzle body includes being used for connecting in aero-engine the arrival end of detergent line and for stretching into nozzle end of the airscoop shroud inwall of aero-engine to be cleaned to gas channel, and nozzle end is provided with multiple spray orifices being obliquely installed and nozzle end integrally in bulb shape.By the way that the nozzle end that airscoop shroud inwall is stretched on nozzle to be cleaned to gas channel is designed as into bulb shape, and the spout of nozzle end is obliquely installed, improve the water inlet percentage of cleaning fluid, and the nozzle end of bulb shape ensures that air input of engine by air is basically unchanged, so as to both not interfere with the service behaviour of engine, it is beneficial to periodically removing again and is attached to deposit and salt marsh on gas channel parts, improves adaptability of the engine to use environment.

Description

Aero-engine washer jet and purging system
Technical field
The utility model is related to aero-engine field, especially, is related to a kind of aero-engine washer jet.This Outside, the utility model further relates to a kind of aero-engine purging system including above-mentioned washer jet.
Background technology
Due to adverse circumstances such as regional, the coastal moist salt fogs of many dirt, easily cause on engine air circulation road parts Corrosion and incrustation.Corrosion can cause parts intensity decreases, and tired source can be formed when serious, is thus cracked, incrustation is serious Engine performance, influence flight safety and comprehensive fight capability can be influenceed.
Existing engine washing nozzle support plate 1 ' and nozzle 2 ' as shown in figure 1, be made up of, provided with nozzle in nozzle 2 ' Chamber 3 ', nozzle 2 ' is the washer jet with multiple straight hole spray orifices 4 '.The cleaning fluid atomizing effect that straight hole spray orifice sprays is poor;And do not have There is the spray angle for considering spray orifice, cleaning fluid easily faces accessory drive gearbox support plate, causes cleaning fluid to flow back out, cleaning fluid Water inlet reduces the cleaning performance of engine air circulation road than small.
Utility model content
The utility model provides a kind of aero-engine washer jet and purging system, is sent out with solving existing aviation The easy incrustation of gas channel of motivation and corrosion, influence the technical problem of engine performance.
The technical solution adopted in the utility model is as follows:
According to one side of the present utility model there is provided a kind of aero-engine washer jet, including nozzle body and It is used for the support plate installed on nozzle body, nozzle body includes the arrival end for being used to connect detergent line in aero-engine And for stretching into nozzle end of the airscoop shroud inwall of aero-engine to be cleaned to gas channel, nozzle end inclines provided with multiple The spray orifice and nozzle end tiltedly set is in integrally bulb shape.
Further, spray orifice is provided for strengthening the chamfering of atomizing effect in its exit.
Further, the axis of spray orifice forms an angle with installation place wall tangent line.
Further, angle is 10~30 °.
Further, support plate is provided with the first end face for being used for being connected with detergent line and is connected for the outer wall with airscoop shroud Second end face, first end face matched with the export-oriented face of detergent line, and second end face is matched with the type face of the outer wall of airscoop shroud.
Further, provided with the sealing gasket that cushioning effect is abutted and risen with air inlet cover outer wall at second end face.
According to another aspect of the present utility model, a kind of aero-engine purging system is also provided, for aeroplane engine The cleaning of machine overdraught passage, including the annular detergent line in aero-engine, in addition to it is circumferentially arranged in aviation Multiple aero-engine washer jets on the airscoop shroud of engine, the arrival end connection annular cleaning pipe of multiple washer jets Road, the nozzle end of multiple washer jets is stretched into the airscoop shroud of aero-engine.
Further, annular detergent line connects the cleaning vehicle for providing cleaning fluid.
The utility model has the advantages that:
The utility model aero-engine washer jet and purging system, by will be stretched on nozzle airscoop shroud inwall with The nozzle end cleaned to gas channel is designed as bulb shape, and the spout of nozzle end is obliquely installed, and improves cleaning fluid Water inlet percentage, and the nozzle end of bulb shape ensures that air input of engine by air is basically unchanged, so as to both not interfere with the work of engine Make performance, periodically removing is beneficial to again and is attached to deposit and salt marsh on gas channel parts, engine is improved to using The adaptability of environment.
In addition to objects, features and advantages described above, the utility model also has other purposes, feature and excellent Point.Below with reference to accompanying drawings, the utility model is described in further detail.
Brief description of the drawings
The accompanying drawing for constituting the part of the application is used for providing further understanding to of the present utility model, of the present utility model Schematic description and description is used to explain the utility model, does not constitute to improper restriction of the present utility model.In accompanying drawing In:
Fig. 1 is the structural representation of existing washer jet;
Fig. 2 is the structural representation of the utility model preferred embodiment aero-engine washer jet;
Fig. 3 be Fig. 2 along A to structural representation;
Fig. 4 is schematic cross-sectional views of the Fig. 3 along B-B;
Fig. 5 is schematic cross-sectional views of the Fig. 3 along C-C;
Fig. 6 is the structural representation of the utility model preferred embodiment aero-engine purging system.
Description of reference numerals:
1st, nozzle body;11st, arrival end;12nd, nozzle end;13rd, spray orifice;14th, chamfering;15th, inner chamber;
2nd, support plate;
3rd, annular detergent line;
4th, airscoop shroud.
Embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase Mutually combination.Describe the utility model in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Reference picture 2 and Fig. 3, preferred embodiment of the present utility model provide a kind of aero-engine washer jet, bag Include nozzle body 1 and be used for the support plate 2 of installation on nozzle body 1, nozzle body 1 includes being used to connect aero-engine The arrival end 11 of detergent line and for stretching into shower nozzle of the airscoop shroud inwall of aero-engine to be cleaned to gas channel In end 12, the present embodiment, nozzle end 12 is provided with multiple spray orifices 13 being obliquely installed and nozzle end 12 is overall in bulb shape.This implementation Example by the nozzle end that airscoop shroud inwall is stretched on nozzle to be cleaned to gas channel by being designed as bulb shape, and nozzle end Spout be obliquely installed, improve the water inlet percentage of cleaning fluid, and the nozzle end of bulb shape ensures that air input of engine by air is basic It is constant, so as to both not interfere with the service behaviour of engine, periodically removing is beneficial to again and is attached to sinking on gas channel parts Product thing and salt marsh, improve adaptability of the engine to use environment.
In the present embodiment, it is preferable that reference picture 4 and Fig. 5, spray orifice 13 is provided for strengthening atomizing effect in its exit Chamfering 14, its atomizing effect that can effectively solve cleaning fluid and water inlet percentage, so as to reach preferable cleaning performance.
In the present embodiment, axis and the installation place wall tangent line of spray orifice 13 form an angle.I.e. the axially bored line of spray orifice 13 with Corresponding installation place wall tangent line is formed an angle on airscoop shroud, during cleaning, and the cleaning fluid in inner chamber 15 is ejected from spray orifice 13, and Mounting surface is angled, and is atomized through chamfering 14, it is to avoid the cleaning fluid of injection is just rushed to accessory drive gearbox support plate and by cleaning fluid The engine part of erosion, so as to improve cleaning fluid water inlet percentage and engine effect.Preferably, by verification experimental verification, folder Angle selects 10~30 °, and cleaning performance is good.
In the present embodiment, support plate 2 is provided with the first end face for being used to be connected with detergent line and for the outer wall with airscoop shroud The second end face of connection, wherein, first end face is matched with the export-oriented face of detergent line, the outer wall of second end face and airscoop shroud Type face is matched so that washer jet is connected reliably with being engaged port or part.Preferably, it is provided with second end face and air inlet Cover outer wall is abutted and risen in the sealing gasket of cushioning effect, the present embodiment, and sealing gasket selects asbestos pad, to meet high temperature resistant, sealing Reliable demand.In the present embodiment, it is connected between the outlet of arrival end 1 and detergent line through conical surface seal, and through first end Face and the export-oriented face of detergent line are positioned, it is ensured that connection reliability.
Fig. 6 shows the structural representation of the utility model preferred embodiment aero-engine purging system, for navigating The cleaning of empty engine overdraught passage, including the annular detergent line 3 in aero-engine, in addition to it is circumferentially arranged In multiple aero-engine washer jets on the airscoop shroud of aero-engine, the washer jet is sprayed using the cleaning of embodiment Mouth, the arrival end 11 of multiple washer jets connects annular detergent line 3, and the nozzle end 12 of multiple washer jets stretches into aeroplane engine In the airscoop shroud of machine.In the present embodiment, 6 washer jets are connected by support plate 2 with annular detergent line 3, and is installed It is arranged on airscoop shroud 4, then by the airscoop shroud 4 for having installed washer jet and annular detergent line in aero-engine, finally Annular detergent line is connected with cleaning vehicle, cold forwarding motivation is cleaned to it.Cleaning fluid is cleaned from cleaning vehicle by annular Pipeline, cleaning fluid is sprayed into the inner chamber 15 of washer jet, then from the spray orifice with chamfering.
The present embodiment purging system is applied to the aero-engine that turbo-propeller is retrofited, and it can effectively remove and be attached to The deposit and salt marsh of gas channel parts, can recover the performance of engine to a certain extent, improve engine to using ring The adaptability in border.
Preferred embodiment of the present utility model is the foregoing is only, the utility model is not limited to, for this For the technical staff in field, the utility model can have various modifications and variations.It is all it is of the present utility model spirit and principle Within, any modification, equivalent substitution and improvements made etc. should be included within protection domain of the present utility model.

Claims (8)

1. a kind of aero-engine washer jet, including nozzle body (1) and it is used to install on the nozzle body (1) Support plate (2), the nozzle body (1) include be used for connect the arrival end (11) of detergent line in aero-engine and for stretching The nozzle end (12) for entering the airscoop shroud inwall of aero-engine to clean gas channel, it is characterised in that the shower nozzle (12) are held provided with multiple spray orifices (13) being obliquely installed and the nozzle end (12) is in integrally bulb shape.
2. aero-engine washer jet according to claim 1, it is characterised in that
The spray orifice (13) is provided for strengthening the chamfering (14) of atomizing effect in its exit.
3. aero-engine washer jet according to claim 2, it is characterised in that
The axis of the spray orifice (13) forms an angle with installation place wall tangent line.
4. aero-engine washer jet according to claim 3, it is characterised in that
The angle is 10~30 °.
5. according to any described aero-engine washer jet of Claims 1-4, it is characterised in that
The support plate (2) is provided with what is be used for the first end face being connected with detergent line and be connected for the outer wall with the airscoop shroud Second end face, the first end face is matched with the export-oriented face of the detergent line, the second end face and the airscoop shroud The type face matching of outer wall.
6. aero-engine washer jet according to claim 5, it is characterised in that
Provided with the sealing gasket that cushioning effect is abutted and risen with the air inlet cover outer wall at the second end face.
7. a kind of aero-engine purging system, sends out for the cleaning of aero-engine overdraught passage, including located at aviation Annular detergent line in motivation, in addition to it is circumferentially arranged on the airscoop shroud of aero-engine such as claim 1 to 6 times Aero-engine washer jet described in one, the arrival end (11) of multiple washer jets connects the annular detergent line, The nozzle end (12) of multiple washer jets is stretched into the airscoop shroud of the aero-engine.
8. aero-engine purging system according to claim 7, it is characterised in that
The annular detergent line connects the cleaning vehicle for providing cleaning fluid.
CN201621448572.7U 2016-12-27 2016-12-27 Aero-engine washer jet and purging system Active CN206519268U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201621448572.7U CN206519268U (en) 2016-12-27 2016-12-27 Aero-engine washer jet and purging system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201621448572.7U CN206519268U (en) 2016-12-27 2016-12-27 Aero-engine washer jet and purging system

Publications (1)

Publication Number Publication Date
CN206519268U true CN206519268U (en) 2017-09-26

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Application Number Title Priority Date Filing Date
CN201621448572.7U Active CN206519268U (en) 2016-12-27 2016-12-27 Aero-engine washer jet and purging system

Country Status (1)

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CN (1) CN206519268U (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111734689A (en) * 2020-07-02 2020-10-02 中国航发常州兰翔机械有限责任公司 Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device
CN113145541A (en) * 2021-04-15 2021-07-23 中国航发湖南动力机械研究所 Quick-release type cleaning joint for aircraft engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111734689A (en) * 2020-07-02 2020-10-02 中国航发常州兰翔机械有限责任公司 Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device
CN113145541A (en) * 2021-04-15 2021-07-23 中国航发湖南动力机械研究所 Quick-release type cleaning joint for aircraft engine

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CP01 Change in the name or title of a patent holder

Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan

Patentee after: China Hangfa South Industrial Co. Ltd.

Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan

Patentee before: China Southern Airlines Industry (Group) Co., Ltd.