CN113586529B - Working method of two-stage thermal-state cleaning device for aircraft engine - Google Patents
Working method of two-stage thermal-state cleaning device for aircraft engine Download PDFInfo
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- CN113586529B CN113586529B CN202110950225.3A CN202110950225A CN113586529B CN 113586529 B CN113586529 B CN 113586529B CN 202110950225 A CN202110950225 A CN 202110950225A CN 113586529 B CN113586529 B CN 113586529B
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- casing
- centrifugal compressor
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- axial flow
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
- F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/02—Cleaning by the force of jets or sprays
- B08B3/022—Cleaning travelling work
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
- F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
- F04D29/705—Adding liquids
Abstract
The invention relates to a working method of a two-stage thermal state cleaning device of an aircraft engine, which comprises the following steps: the first-stage cleaning nozzle and the second-stage cleaning nozzle are respectively communicated with a water pipe, an aqueous solution for cleaning enters the air inlet casing from the first-stage cleaning nozzle, the axial flow compressor rotor is in a rotating state, the aqueous solution sprayed out by the first-stage cleaning nozzle enters the axial flow compressor casing to perform thermal cleaning on the axial flow compressor rotor, and the aqueous solution flowing out from the axial flow compressor casing enters between the centrifugal compressor casing and flows out from the air bleed valve; meanwhile, the water solution for cleaning enters the casing in the centrifugal compressor from the secondary cleaning nozzle, the rotor of the centrifugal compressor is in a rotating state, and the water solution sprayed out of the secondary cleaning nozzle is used for carrying out thermal cleaning on the rotor of the centrifugal compressor and flowing out of the casing in the centrifugal compressor.
Description
Technical Field
The invention relates to the technical field of aero-engine parts, in particular to a working method of a two-stage thermal-state cleaning device of an aero-engine.
Background
The air inlet channel of the engine needs to be cleaned after the last flight every day is finished, salt particles are removed, the waiting time of a conventional cold cleaning mode is long, and great inconvenience is brought to the use and maintenance of a user.
A cleaning system is additionally arranged on the engine, so that hot cleaning is realized, the cleaning time can be greatly shortened, and the maintenance efficiency is improved. However, because the air bleeding valves arranged between the axial flow compressor and the centrifugal compressor of the engine are used for inter-stage air bleeding, for a single-stage cleaning nozzle, cleaning liquid can be discharged from the air bleeding valves, and the cleaning effect cannot be achieved for the following stages of compressors.
Disclosure of Invention
The invention aims to provide a two-stage thermal-state cleaning device for an aircraft engine and a working method thereof, wherein the two-stage thermal-state cleaning device is simple in structure and good in cleaning effect.
In order to solve the technical problem, the invention adopts two-stage cleaning nozzles, wherein one stage of the cleaning nozzles is designed on an air inlet casing of an engine to clean a rotor of the axial flow compressor; the centrifugal compressor is designed in front of the centrifugal compressor in a first-stage mode, the centrifugal compressor rotor is cleaned, and the axial flow compressor rotor and the centrifugal compressor rotor are cleaned through two stages of cleaning nozzles respectively.
The two-stage thermal state cleaning device comprises an air inlet casing, an axial flow compressor casing and a centrifugal compressor casing which are connected in sequence, wherein a rotatable axial flow compressor rotor is arranged in the axial flow compressor casing, the centrifugal compressor casing is fixedly arranged in the centrifugal compressor casing, the rotatable centrifugal compressor rotor is arranged in the centrifugal compressor casing, at least 2 first-stage cleaning nozzles are arranged in the middle of the air inlet casing, at least 2 second-stage cleaning nozzles are arranged at the front end of the centrifugal compressor casing, the first-stage cleaning nozzles and the second-stage cleaning nozzles are identical in structure, jet holes are formed in the centrifugal compressor casing, the water outlet end of each first-stage cleaning nozzle extends into the air inlet casing, the water outlet end of each second-stage cleaning nozzle extends into the centrifugal compressor casing and is communicated with the jet holes in the centrifugal compressor casing, so that the first-stage cleaning nozzles can spray and clean the axial flow compressor rotor in the axial flow compressor casing, and the second-stage cleaning nozzles can spray and clean the centrifugal compressor rotor in the centrifugal compressor casing.
Further, one-level washing nozzle/second grade washing nozzle includes nozzle inlet sleeve and nozzle outlet sleeve that integrated into one piece set up, set up the intake antrum of cylinder in the nozzle inlet sleeve, set up the injection chamber and the pressure boost chamber of awl cylindric in the nozzle outlet sleeve, the injection chamber is including spraying chamber stub end and spraying chamber stub end, the pressure boost chamber is including pressure boost chamber stub end and pressure boost chamber stub end, pressure boost chamber stub end links to each other with the intake antrum, pressure boost chamber stub end links to each other with spraying chamber stub end, so that the pressure boost chamber forms the contraction section with the junction that sprays the chamber, because bore diminishing water pressure increase when aqueous solution arrives pressure boost chamber stub end by pressure boost chamber stub end, and acceleratedly get into and spray the chamber, jet out by spraying chamber stub end.
Furthermore, a flange plate is arranged on the periphery of the middle part of the nozzle inlet sleeve, screw holes are symmetrically formed in the flange plate, and the primary cleaning nozzle/the secondary cleaning nozzle can be conveniently installed.
Furthermore, the end part of the water inlet cavity is provided with a connecting ring platform which is used for being connected with an external water pipe.
Furthermore, the periphery of the nozzle outlet sleeve is provided with a sheath, and the sheath is in plug-in fit with the corresponding air inlet casing or the centrifugal compressor outer casing during assembly.
The working method of the two-stage thermal state cleaning device for the aircraft engine comprises the following steps: the first-stage cleaning nozzle and the second-stage cleaning nozzle are respectively communicated with a water pipe, an aqueous solution for cleaning enters the air inlet casing from the first-stage cleaning nozzle, the axial flow compressor rotor is in a rotating state, the aqueous solution sprayed out by the first-stage cleaning nozzle enters the axial flow compressor casing to perform thermal cleaning on the axial flow compressor rotor, and the aqueous solution flowing out from the axial flow compressor casing enters between the centrifugal compressor casing and flows out from the air bleed valve; meanwhile, the water solution for cleaning enters the casing in the centrifugal compressor from the secondary cleaning nozzle, the rotor of the centrifugal compressor is in a rotating state, and the water solution sprayed out of the secondary cleaning nozzle is used for carrying out thermal cleaning on the rotor of the centrifugal compressor and flowing out of the casing in the centrifugal compressor.
The invention has the technical effects that: (1) Compared with the prior art, the two-stage thermal state cleaning device for the aircraft engine respectively realizes the thermal state cleaning of the rotor of the axial flow compressor and the rotor of the centrifugal compressor through the two-stage cleaning nozzles, can effectively solve the problem that cleaning liquid is discharged from devices such as an interstage bleed valve of the compressor and the like and cannot achieve the cleaning effect on the compressors of the next stages when the conventional one-stage cleaning nozzle is used for cleaning, and thus improves the cleaning effect of the engine; (2) The first-stage cleaning nozzle and the second-stage cleaning nozzle are arranged on the corresponding casings through flanges and screws, and are easy to assemble; (3) One-level washing nozzle, second grade washing nozzle are through all setting up the pressure boost chamber and spraying the chamber to the cone cylindric, and the little head end in pressure boost chamber links to each other with spraying the chamber little head end for aqueous solution forms the pressure boost in pressure boost intracavity, forms at spraying the intracavity and sprays, has improved the cleaning performance by a wide margin.
Drawings
The invention is described in further detail below with reference to the drawings:
FIG. 1 is a schematic assembled structural view of a two-stage thermal state cleaning device for an aircraft engine according to the present invention;
FIG. 2 is a schematic cross-sectional view of a nozzle;
FIG. 3 is an axial structural view of the nozzle;
FIG. 4 is an axial schematic view of a centrifugal compressor;
fig. 5 isbase:Sub>A schematic sectional view along the linebase:Sub>A-base:Sub>A in fig. 4.
In the figure: the cleaning device comprises an air inlet casing 1, an axial flow compressor casing 2, a primary cleaning nozzle 3, a contraction section 30, a flange plate 31, a screw hole 32, a nozzle inlet sleeve 33, a nozzle outlet sleeve 34, a sheath 35, a spraying cavity 36, a pressurization cavity 37, a water inlet cavity 38, a connecting ring platform 39, a centrifugal compressor casing 4, a deflation valve 41, a centrifugal compressor casing 42, a connecting part 43, a jet hole 44 and a secondary cleaning nozzle 5.
Detailed Description
Example 1
As shown in fig. 1 to fig. 5, the two-stage thermal cleaning device for an aircraft engine of the embodiment includes an air inlet casing 1, an axial flow compressor casing 2, and a centrifugal compressor casing 4, which are connected in sequence.
The rotatable axial-flow compressor rotor is arranged in the axial-flow compressor casing 2, the centrifugal compressor casing 42 is fixedly arranged in the centrifugal compressor casing 4, the air release valve 41 is arranged on the centrifugal compressor casing 4, the outer wall of the centrifugal compressor casing 42 is fixedly connected with the inner wall of the centrifugal compressor casing 4 through 2 connecting parts 43, the rotatable centrifugal compressor rotor is arranged in the centrifugal compressor casing 42, the middle part of the air inlet casing 1 is provided with 2 first-stage cleaning nozzles 3, and the front end of the centrifugal compressor casing 4 is provided with 2 second-stage cleaning nozzles 5.
The structure that one-level washing nozzle 3 and second grade washing nozzle 5 are the same, and one-level washing nozzle 3, second grade washing nozzle 5 all include nozzle inlet sleeve 33 and nozzle outlet sleeve 34 that integrated into one piece set up, set up cylindrical intake antrum 38 in the nozzle inlet sleeve 33, and the tip of intake antrum 38 sets up the connecting ring platform 39, and the water pipe of peripheral hardware can be fixed through the welding after pegging graft the cooperation with connecting ring platform 39 for be used for abluent water pipe and intake antrum 38 to communicate with each other.
The nozzle outlet sleeve 33 is internally provided with a conical barrel-shaped injection cavity 36 and a pressurizing cavity 37, the injection cavity 36 comprises an injection cavity big head end and an injection cavity small head end, the pressurizing cavity 37 comprises a pressurizing cavity big head end and a pressurizing cavity small head end, the pressurizing cavity big head end is connected with the water inlet cavity 38, the inner diameter of the pressurizing cavity big head end is the same as that of the water inlet cavity 38, the pressurizing cavity small head end is connected with the injection cavity small head end, so that a contraction section 30 is formed at the joint of the pressurizing cavity 37 and the injection cavity 36, when the water solution reaches the pressurizing cavity small head end from the pressurizing cavity big head end, the water pressure is increased due to the reduction of the caliber, and the water solution enters the injection cavity 36 in an accelerating manner and is ejected from the injection cavity big head end.
The periphery of the middle part of the nozzle inlet sleeve 33 is provided with a flange plate 31, screw holes 32 are symmetrically arranged on two sides of the flange plate 31, the periphery of the nozzle outlet sleeve 33 is provided with a sheath 35, the air inlet casing 1 and the centrifugal compressor outer casing 4 are provided with assembly holes matched with the sheath 35, sunken grooves matched with the flange plate 31 are arranged on the periphery of the assembly holes, and mounting screw holes matched with the screw holes 32 are arranged on two sides of the assembly holes, so that after the sheath 35 of the primary cleaning nozzle 3/secondary cleaning nozzle 5 is inserted into the assembly holes, the flange plate 31 is arranged in the sunken grooves, the flange plate 31 and the corresponding air inlet casing 1 or the centrifugal compressor outer casing 4 are in threaded connection by screws, and the mounting is convenient.
The water outlet end of the primary cleaning nozzle 3 extends into the air inlet casing 1, the assembly of the secondary cleaning nozzle 5 is different from the assembly of the primary cleaning nozzle 3 in that an assembly hole on the centrifugal compressor casing 4 corresponds to the connecting part 43, the connecting part 43 of the centrifugal compressor casing 42 is provided with a jet hole 44 leading to the centrifugal compressor casing 42, the water outlet end of the secondary cleaning nozzle 5 extends into the centrifugal compressor casing 4 and is connected with the connecting part 43, so that the injection cavity 36 of the secondary cleaning nozzle 5 is communicated with the jet hole 44 of the centrifugal compressor casing 42, the primary cleaning nozzle 3 can perform injection cleaning on the axial compressor rotor in the axial compressor casing 2, the secondary cleaning nozzle 5 can perform injection cleaning on the centrifugal compressor rotor in the centrifugal compressor casing 42, and most of the water solution flowing out of the axial compressor casing 2 flows between the centrifugal compressor casing 4 and the centrifugal compressor casing 42, so that sealing treatment is not needed between the secondary cleaning nozzle 5 and the jet hole 44.
Example 2
The working method of the two-stage thermal state cleaning device for the aircraft engine comprises the following steps: the primary cleaning nozzle 3 and the secondary cleaning nozzle 5 are respectively communicated with a water pipe, an aqueous solution for cleaning enters the air inlet casing 1 from the primary cleaning nozzle 3, the axial flow compressor rotor is in a rotating state, the aqueous solution sprayed out by the primary cleaning nozzle 3 enters the axial flow compressor casing 2 to perform thermal cleaning on the axial flow compressor rotor, and the aqueous solution flowing out of the axial flow compressor casing 2 enters between the centrifugal compressor casing 4 and the centrifugal compressor casing 42 and flows out from the air bleed valve 41; meanwhile, the water solution for cleaning enters the casing 42 in the centrifugal compressor from the secondary cleaning nozzle 5, the rotor of the centrifugal compressor is in a rotating state, and the water solution sprayed out by the secondary cleaning nozzle 5 is used for thermally cleaning the rotor of the centrifugal compressor and flows out of the casing 42 in the centrifugal compressor.
It should be understood that the above examples are only for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And such obvious variations or modifications which fall within the spirit of the invention are intended to be covered by the scope of the present invention.
Claims (1)
1. The working method of the two-stage thermal state cleaning device of the aircraft engine is characterized by comprising an air inlet casing, an axial flow compressor casing and a centrifugal compressor casing which are sequentially connected, wherein a rotatable axial flow compressor rotor is arranged in the axial flow compressor casing, the centrifugal compressor casing is fixedly arranged in the centrifugal compressor casing, the rotatable centrifugal compressor rotor is arranged in the centrifugal compressor casing, at least 2 first-stage cleaning nozzles are arranged in the middle of the air inlet casing, at least 2 second-stage cleaning nozzles are arranged at the front end of the centrifugal compressor casing, the first-stage cleaning nozzles and the second-stage cleaning nozzles are identical in structure, jet holes are formed in the centrifugal compressor casing, the water outlet end of the first-stage cleaning nozzle extends into the air inlet casing, the water outlet end of the second-stage cleaning nozzle extends into the centrifugal compressor casing and is communicated with the jet holes in the centrifugal compressor casing, so that the first-stage cleaning nozzles can jet and clean the compressor rotor in the axial flow compressor casing, and the second-stage cleaning nozzles can jet and clean the centrifugal compressor rotor in the centrifugal compressor casing;
the working method of the two-stage thermal state cleaning device for the aircraft engine comprises the following steps:
the first-stage cleaning nozzle and the second-stage cleaning nozzle are respectively communicated with a water pipe, an aqueous solution for cleaning enters the air inlet casing from the first-stage cleaning nozzle, the axial flow compressor rotor is in a rotating state, the aqueous solution sprayed out by the first-stage cleaning nozzle enters the axial flow compressor casing to perform thermal cleaning on the axial flow compressor rotor, and the aqueous solution flowing out from the axial flow compressor casing enters between the centrifugal compressor casing and flows out from the air bleed valve; meanwhile, the water solution for cleaning enters the casing in the centrifugal compressor from the secondary cleaning nozzle, the rotor of the centrifugal compressor is in a rotating state, and the water solution sprayed out of the secondary cleaning nozzle is used for carrying out thermal cleaning on the rotor of the centrifugal compressor and flowing out of the casing in the centrifugal compressor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110950225.3A CN113586529B (en) | 2020-07-02 | 2020-07-02 | Working method of two-stage thermal-state cleaning device for aircraft engine |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110950225.3A CN113586529B (en) | 2020-07-02 | 2020-07-02 | Working method of two-stage thermal-state cleaning device for aircraft engine |
| CN202010634083.5A CN111734689B (en) | 2020-07-02 | 2020-07-02 | Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device |
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| CN202010634083.5A Division CN111734689B (en) | 2020-07-02 | 2020-07-02 | Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device |
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| CN113586529A CN113586529A (en) | 2021-11-02 |
| CN113586529B true CN113586529B (en) | 2023-04-18 |
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| CN202010634083.5A Active CN111734689B (en) | 2020-07-02 | 2020-07-02 | Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device |
| CN202110950225.3A Active CN113586529B (en) | 2020-07-02 | 2020-07-02 | Working method of two-stage thermal-state cleaning device for aircraft engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6553753B1 (en) * | 1998-07-24 | 2003-04-29 | General Electric Company | Control systems and methods for water injection in a turbine engine |
| DK1715964T3 (en) * | 2004-02-16 | 2010-12-13 | Gas Turbine Efficiency Ab | Method and apparatus for cleaning a gas turbine engine with turbo blower |
| EP1754862A1 (en) * | 2005-08-17 | 2007-02-21 | ABB Turbo Systems AG | Compressor, compressor wheel, washing attachment and exhaust turbocharger |
| WO2007102738A1 (en) * | 2006-03-08 | 2007-09-13 | Dynatrend As | A method and device for cleaning an axial compressor |
| JP2008151030A (en) * | 2006-12-18 | 2008-07-03 | Mitsubishi Heavy Ind Ltd | Cleaning device of compressor and cleaning method |
| JP5461143B2 (en) * | 2009-10-23 | 2014-04-02 | 三菱重工業株式会社 | Centrifugal compressor |
| CN202338516U (en) * | 2011-12-13 | 2012-07-18 | 沈阳透平机械股份有限公司 | Water spray type washing system of compressor |
| US20150159559A1 (en) * | 2013-12-06 | 2015-06-11 | General Electric Company | Method and System for Compressor On Line Water Washing With Anticorrosive Solution |
| JP5869044B2 (en) * | 2014-05-15 | 2016-02-24 | 三菱重工業株式会社 | Centrifugal compressor |
| US20160169107A1 (en) * | 2014-12-12 | 2016-06-16 | General Electric Company | Systems and methods for injecting fluids at one or more stages of a multi-stage component |
| WO2016121046A1 (en) * | 2015-01-29 | 2016-08-04 | 三菱重工コンプレッサ株式会社 | Centrifugal-compressor casing and centrifugal compressor |
| US9951647B2 (en) * | 2015-12-17 | 2018-04-24 | General Electric Company | System and method for in situ cleaning of internal components of a gas turbine engine and a related plug assembly |
| US20170239692A1 (en) * | 2016-02-19 | 2017-08-24 | General Electric Company | Auxiliary Cleaning System for Gas Turbine Engines |
| CN205858800U (en) * | 2016-07-19 | 2017-01-04 | 武汉钢铁股份有限公司 | Centrifugal compressor impeller fouling online treatment device |
| CN206519268U (en) * | 2016-12-27 | 2017-09-26 | 中国南方航空工业(集团)有限公司 | Aero-engine washer jet and purging system |
| CN107476831A (en) * | 2017-09-30 | 2017-12-15 | 中国航发沈阳发动机研究所 | Aircraft engine support case with cleaning function |
| CN108104953A (en) * | 2017-12-14 | 2018-06-01 | 中国航发沈阳发动机研究所 | A kind of low-pressure compressor blade cleaning equipment |
| KR102139266B1 (en) * | 2018-11-20 | 2020-07-29 | 두산중공업 주식회사 | Gas turbine |
| CN110064615B (en) * | 2019-05-14 | 2022-07-22 | 中国航发沈阳发动机研究所 | Flow passage cleaning device and cleaning method |
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- 2020-07-02 CN CN202010634083.5A patent/CN111734689B/en active Active
- 2020-07-02 CN CN202110950225.3A patent/CN113586529B/en active Active
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| Publication number | Publication date |
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| CN111734689A (en) | 2020-10-02 |
| CN113586529A (en) | 2021-11-02 |
| CN111734689B (en) | 2021-09-17 |
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