CN111734689A - Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device - Google Patents
Two-stage thermal-state cleaning device for aircraft engine and working method of two-stage thermal-state cleaning device Download PDFInfo
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- CN111734689A CN111734689A CN202010634083.5A CN202010634083A CN111734689A CN 111734689 A CN111734689 A CN 111734689A CN 202010634083 A CN202010634083 A CN 202010634083A CN 111734689 A CN111734689 A CN 111734689A
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- centrifugal compressor
- casing
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- cleaning
- nozzle
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a two-stage thermal state cleaning device of an aero-engine and a working method thereof, the two-stage thermal state cleaning device of the aero-engine comprises an air inlet casing and an axial flow air compressor casing which are connected in sequence, the centrifugal compressor comprises a centrifugal compressor outer case, wherein a rotatable axial compressor rotor is arranged in the axial compressor outer case, the centrifugal compressor inner case is fixedly arranged in the centrifugal compressor outer case, the rotatable centrifugal compressor rotor is arranged in the centrifugal compressor inner case, at least 2 first-stage cleaning nozzles are arranged in the middle of the centrifugal compressor outer case, at least 2 second-stage cleaning nozzles are arranged at the front end of the centrifugal compressor outer case, the first-stage cleaning nozzles and the second-stage cleaning nozzles are identical in structure, jet holes are formed in the centrifugal compressor inner case, the water outlet end of each first-stage cleaning nozzle extends into the air inlet case, and the water outlet end of each second-stage cleaning nozzle extends into the centrifugal compressor outer case and is communicated with the jet holes in the centrifugal compressor outer case.
Description
Technical Field
The invention relates to the technical field of aero-engine parts, in particular to a two-stage thermal-state cleaning device for an aero-engine and a working method thereof.
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.
The cleaning system is additionally arranged on the engine, so that thermal cleaning is realized, the cleaning time can be greatly shortened, and the maintenance efficiency is improved. However, because the air bleeding valves are arranged between the axial-flow compressor and the centrifugal compressor of the engine 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 compressors of the following stages.
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, a jet hole is 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 hole in the centrifugal compressor casing, so that the first-stage cleaning nozzle can jet and clean the axial flow compressor rotor in the axial flow compressor casing, the secondary cleaning nozzle can perform jet cleaning on a centrifugal compressor rotor in a casing of the centrifugal compressor.
Further, one-level washing nozzle/second grade washing nozzle include 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 major-axis end and spraying chamber tip end, the pressure boost chamber is including pressure boost chamber major-axis end and pressure boost chamber tip end, pressure boost chamber major-axis end links to each other with the intake antrum tip end, so that the pressure boost chamber forms the contraction section with the junction that sprays the chamber, when aqueous solution reaches pressure boost chamber tip end by pressure boost chamber major-axis end, because bore diminishing water pressure increase, and acceleratedly get into the injection chamber, jet out by spraying chamber major-axis 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 of the specification:
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 is a schematic sectional view taken along the line a-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 5, the two-stage thermal cleaning device for an aircraft engine of the present 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.
Set up the cylindric injection chamber 36 and the pressure boost chamber 37 of awl in nozzle outlet sleeve 33, injection chamber 36 is including injecting the big head end of chamber and injecting the chamber tip end, pressure boost chamber 37 is including the big head end of pressure boost chamber and the pressure boost chamber tip end, the big head end of pressure boost chamber links to each other with intake antrum 38, and the internal diameter of the big head end of pressure boost chamber is the same with the internal diameter of intake antrum 38, the pressure boost chamber tip end links to each other with the injection chamber tip end, so that pressure boost chamber 37 forms the contraction section 30 with the junction of injecting chamber 36, water solution is increased because bore diminishing water pressure when reaching the pressure boost chamber tip end by the big head end of pressure boost chamber, and get into injection chamber 36 with higher speed, jet out by the.
The periphery of the middle part of the nozzle inlet sleeve 33 is provided with a flange 31, the two sides of the flange 31 are symmetrically provided with screw holes 32, 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, the periphery of the assembly holes is provided with sinking grooves matched with the flange 31, and the two sides of the assembly holes are provided with mounting screw holes matched with the screw holes 32, so that after the sheath 35 of the primary cleaning nozzle 3/secondary cleaning nozzle 5 is inserted into the assembly holes, the flange 31 is arranged in the sinking grooves, the flange 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 jet 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 jet and clean the axial compressor rotor in the axial compressor casing 2, the secondary cleaning nozzle 5 can jet and clean the centrifugal compressor rotor in the centrifugal compressor casing 42, and most of the water solution flowing out from the axial compressor casing 2 flows between the centrifugal compressor casing 4 and the centrifugal compressor casing 42, therefore, no sealing process is required between the secondary cleaning nozzle 5 and the injection 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 inner casing 42 of 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 of the secondary cleaning nozzle 5 is used for carrying out thermal cleaning on the rotor of the centrifugal compressor and flows out of the inner casing 42 of 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 (6)
1. A two-stage thermal state cleaning device for an aircraft engine is characterized by comprising 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, a jet hole is 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 hole in the centrifugal compressor casing, so that the first-stage cleaning nozzles can jet and clean the axial flow compressor rotor in the axial flow compressor casing, the secondary cleaning nozzle can perform jet cleaning on a centrifugal compressor rotor in a casing of the centrifugal compressor.
2. The two-stage thermal cleaning device for the aircraft engine according to claim 1, wherein the one-stage cleaning nozzle/the two-stage cleaning nozzle comprises a nozzle inlet sleeve and a nozzle outlet sleeve which are integrally formed, a cylindrical water inlet cavity is arranged in the nozzle inlet sleeve, a conical spray cavity and a booster cavity are arranged in the nozzle outlet sleeve, the spray cavity comprises a spray cavity large end and a spray cavity small end, the booster cavity comprises a booster cavity large end and a booster cavity small end, the booster cavity large end is connected with the water inlet cavity, the booster cavity small end is connected with the spray cavity small end, so that a contraction section is formed at the joint of the booster cavity and the spray cavity, and when the water solution reaches the booster cavity small end from the booster cavity large end, the water pressure is increased due to the reduction of the caliber, and the water solution is accelerated to enter the spray cavity and is sprayed out from the spray cavity large end.
3. A two-stage thermal cleaning apparatus for an aircraft engine as claimed in claim 2, wherein the nozzle inlet sleeve has a flange around the periphery of the central portion thereof, the flange having screw holes formed therein.
4. A two-stage thermal state cleaning device for an aircraft engine according to claim 2 or 3, wherein the end of the water inlet chamber is provided with a connecting ring platform.
5. A two-stage thermal state cleaning apparatus for an aircraft engine according to claim 4, characterised in that the nozzle outlet sleeve is provided with a jacket around its periphery.
6. A method of operating an aircraft engine two-stage thermal cleaning apparatus according to claim 5, comprising the steps of: 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 (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
| 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 (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| CN202110950225.3A Division CN113586529B (en) | 2020-07-02 | 2020-07-02 | Working method of two-stage thermal-state cleaning device for aircraft engine |
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| CN111734689A true CN111734689A (en) | 2020-10-02 |
| CN111734689B CN111734689B (en) | 2021-09-17 |
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| CN202110950225.3A Active CN113586529B (en) | 2020-07-02 | 2020-07-02 | Working method of two-stage thermal-state cleaning device for aircraft engine |
| 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 |
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| 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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Also Published As
| Publication number | Publication date |
|---|---|
| CN111734689B (en) | 2021-09-17 |
| CN113586529A (en) | 2021-11-02 |
| CN113586529B (en) | 2023-04-18 |
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