CN113530857A - Electric driving type sand discharging device for particle separator of aircraft engine - Google Patents

Electric driving type sand discharging device for particle separator of aircraft engine Download PDF

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Publication number
CN113530857A
CN113530857A CN202110972985.4A CN202110972985A CN113530857A CN 113530857 A CN113530857 A CN 113530857A CN 202110972985 A CN202110972985 A CN 202110972985A CN 113530857 A CN113530857 A CN 113530857A
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CN
China
Prior art keywords
shell
impeller
air outlet
motor
particle separator
Prior art date
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Pending
Application number
CN202110972985.4A
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Chinese (zh)
Inventor
牛佳佳
谢买祥
徐弘历
刘媛
张翼飞
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Hunan Aviation Powerplant Research Institute AECC
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Hunan Aviation Powerplant Research Institute AECC
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Application filed by Hunan Aviation Powerplant Research Institute AECC filed Critical Hunan Aviation Powerplant Research Institute AECC
Priority to CN202110972985.4A priority Critical patent/CN113530857A/en
Publication of CN113530857A publication Critical patent/CN113530857A/en
Pending legal-status Critical Current

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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
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • F02C7/052—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/008—Stop safety or alarm devices, e.g. stop-and-go control; Disposition of check-valves
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/5806—Cooling the drive system
    • 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
    • F04D29/703—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps specially for fans, e.g. fan guards
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K9/00—Arrangements for cooling or ventilating
    • H02K9/02—Arrangements for cooling or ventilating by ambient air flowing through the machine
    • H02K9/04—Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium
    • H02K9/06—Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Power Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses an electrically driven sand discharge device for an aircraft engine particle separator, which comprises: the impeller mechanism, the driving mechanism and the control mechanism; the impeller mechanism is connected with the driving mechanism; the driving mechanism is electrically connected with the control mechanism; the impeller mechanism is used for sucking the separated airflow containing the sand and the dust; the driving mechanism is used for driving the impeller mechanism to rotate; and the control mechanism is used for controlling the driving mechanism to start or close. Through motor control electrically-driven sand discharge device, can select to start or close electrically-driven sand discharge device according to actual operating environment, can close electrically-driven sand discharge device under non-dust environment, make most air current get into the engine, improve the power of engine under the non-dust environment, can also practice thrift the output of engine, remove the coupling of electrically-driven sand discharge device and engine transmission system, can reduce the security and the reliability risk of engine because of electrically-driven sand discharge device trouble brings to a certain extent.

Description

Electric driving type sand discharging device for particle separator of aircraft engine
Technical Field
The invention belongs to the technical field of engines, and particularly relates to an electrically-driven sand discharging device for an aircraft engine particle separator.
Background
Helicopters are often required to take off, land and hover for flight in special environments with a diffuse sand fog, such as mountainous areas, deserts, ice and snow grounds and sea surfaces, and the working environment of the engine is more and more demanding. At this time, a large amount of foreign matters such as sand, ice and snow or salt fog on the sea are sucked into the engine, and if protective measures are not taken in advance, the dust and sand can bring serious harm to the helicopter and the engine: compressor blade erosion and the resulting deterioration of engine performance, i.e., reduced power and increased fuel consumption, ultimately results in a shortened engine life. Therefore, an air Inlet protective device, i.e. an Inlet Particle Separator (Inlet Particle Separator), is usually added in front of the engine to separate solid particles in an impurity-containing air flow, so as to protect the engine, ensure the working stability of the engine and prolong the service life of the engine.
Existing particle separators concentrate and expel the sand and dust from the engine inlet air stream out of the engine by sacrificing a portion of the air stream. The air flow with the sand dust is discharged out of the engine through a sand discharge device, and the sand-containing air flow is discharged out of the engine by adopting an ejector or an air blower on the existing engine. The existing sand-discharging blower drives the blower to run by mutually meshing a rotating shaft and an accessory transmission shaft and connecting the rotating shaft and an engine power output shaft through an accessory transmission system, low pressure is formed at a sand-dust outlet of a particle separator, sand-dust is discharged out of the engine, the power of the blower is extracted from the engine, and the working state of the blower completely depends on the working state of the engine. In a non-dust environment, the inlet airflow hardly contains dust, the dust in the airflow does not need to be separated, the blower still continuously operates to extract shaft power, the power of the engine is wasted, the inlet airflow is sacrificed under unnecessary conditions, the output power of the engine is reduced, and the safety and reliability risks of the engine caused by the fault of the blower are increased. Therefore, in order to make the blower independent of the power of the engine shaft and independently control the working condition of the blower, a new sand discharge device needs to be developed.
Disclosure of Invention
In order to solve the problems, the invention discloses an electrically-driven sand discharge device for an aircraft engine particle separator, which comprises: the impeller mechanism, the driving mechanism and the control mechanism;
the impeller mechanism is connected with the driving mechanism; the driving mechanism is electrically connected with the control mechanism;
the impeller mechanism is used for sucking the separated airflow containing the sand and the dust;
the driving mechanism is used for driving the impeller mechanism to rotate;
and the control mechanism is used for controlling the driving mechanism to start or close.
Still further, an air intake housing is also included;
the outer surface of the air inlet shell is provided with a mounting seat, and the air inlet shell is fixedly mounted on an engine through the mounting seat; the air inlet shell is in a bent column shape, one end of the air inlet shell is a conical opening, and an annular boss is arranged at the edge of the outer wall of the conical opening; the annular boss end of the air inlet shell is connected with the impeller mechanism, and the other end of the annular boss end of the air inlet shell is connected with a clearing flow channel of the particle separator.
Furthermore, the air outlet shell is also included;
the air outlet shell comprises an inner shell, an outer shell and guide vanes, wherein the inner shell is barrel-shaped, the outer shell is horn-shaped, the diameter of the inner shell is smaller than that of the outer shell, a part of the inner shell is arranged in the outer shell, and the inner shell and the outer shell are coaxially arranged and fixedly connected through the guide vanes;
an annular boss is arranged at the edge of the outer wall at one end of the outer shell of the air outlet shell; a guide vane is arranged between the inner shell and the outer shell of the air outlet shell; the guide vanes are hollow vanes and are circumferentially and uniformly distributed at the airflow inlet of the air outlet shell;
the annular boss end of the air outlet shell is connected with the air inlet shell and the impeller mechanism;
and a channel for discharging the air flow containing the sand and the dust is formed between the inner shell and the outer shell of the air outlet shell.
Still further, the impeller mechanism comprises an impeller shaft, a coupling and an oblique flow impeller;
one end of the impeller shaft is connected with the coupler, and the other end of the impeller shaft is fixedly connected with the oblique flow impeller;
the impeller shaft is connected with the driving mechanism through a coupler;
the impeller shaft is used for driving the oblique flow impeller to rotate;
the inclined flow impeller is used for forming a low-pressure area at the outlet of the cleaning flow channel, sucking the air flow containing the sand and the dust into the air inlet shell from the cleaning flow channel of the particle separator and further discharging the air flow from the air outlet shell.
Furthermore, the impeller mechanism also comprises a quick-release clamp and a rotor case;
the rotor casing is arranged on the periphery of the oblique flow impeller;
the rotor case is connected with the air inlet shell and the air outlet shell through quick-release clamps.
Still further, the impeller mechanism further comprises a grate ring, a bearing and a bearing seat assembly;
the grate ring is arranged between the inner shell of the air outlet shell and the impeller shaft; the bearing is arranged in the bearing seat component; the bearing seat assembly is arranged at the front end of the inner shell of the air outlet shell through a bolt; the comb tooth ring, the bearing and the bearing seat assembly are coaxially arranged;
the grate ring is used for preventing sand and dust;
the bearing and bearing seat assembly is used for fixing the impeller shaft.
Still further, the drive mechanism includes a junction box and a motor;
the junction box is arranged on the outer surface of the outer shell of the air outlet shell; the motor is arranged in the annular inner cavity of the inner shell of the air outlet shell and fixedly connected to the inner surface of the inner shell of the air outlet shell through bolts or welding; the lead of the motor is connected to the junction box through the guide vane;
and a motor shaft of the motor is connected with the impeller shaft through a coupler.
Still further, the drive mechanism further comprises an end cover and a cooling fan;
the end cover is fixedly connected with the inner shell of the air outlet shell through bolts or welding; a bearing is arranged at the center of the end cover; one end of a motor shaft of the motor penetrates through the bearing and is fixedly connected with the cooling fan through a bolt;
the cooling fan is used for cooling the motor.
Furthermore, the driving mechanism further comprises a dustproof mesh enclosure;
the dustproof mesh enclosure is arranged on the side of the cooling fan and fixedly arranged at the tail end of the inner shell of the air outlet shell;
the dustproof mesh enclosure is used for preventing the discharged sand and dust from entering the motor.
Still further, the control mechanism includes a motor controller;
the motor controller is arranged in the cockpit;
the motor controller is electrically connected with the motor through a junction box;
and the motor controller is used for controlling the motor to be started or closed.
Compared with the prior art, the invention has the beneficial effects that:
1. the electrically-driven sand discharging device is controlled by the motor, can be selectively started or stopped according to the actual working environment, and can be stopped in a non-sand environment, so that most of air flow enters the engine, and the power of the engine in the non-sand environment is improved;
2. the electrically-driven sand discharge device is closed in a non-dust environment, so that the output power of the engine can be saved;
3. the coupling between the electrically-driven sand discharge device and an engine transmission system is removed by controlling the electrically-driven sand discharge device through the motor, so that the safety and reliability risks of the engine caused by the fault of the electrically-driven sand discharge device can be reduced to a certain extent.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
FIG. 1 illustrates a schematic structural view of an electrically driven sand discharge apparatus according to an embodiment of the present invention;
fig. 2 shows a schematic operation of an electrically driven sand discharge device according to an embodiment of the present invention.
In the figure: 1. an air intake housing; 2-1, impeller shaft; 2-2, a comb ring; 2-3, quickly disassembling the clamp; 2-4, a rotor case; 2-5, a coupler; 2-6, an oblique flow impeller; 2-7, a bearing; 2-8, bearing seat components; 3. an air outlet shell; 3-1, guide vanes; 4-1, a junction box; 4-2, a motor; 4-3, end cover; 4-4, a cooling fan; 4-5, a dustproof mesh enclosure; 5. a motor controller; 6. a particle separator; 6-1, an air inlet channel; 6-2, clearing a flow channel; 6-3, a main gas flow channel; 7. an electrically driven sand discharge device; 8. an engine.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 1 shows a schematic configuration of an electrically driven sand discharge device according to an embodiment of the present invention. As shown in fig. 1, the present invention provides an electrically driven sand discharging device for an aircraft engine particle separator, comprising: the impeller mechanism, the driving mechanism, the control mechanism, the air inlet shell 1 and the air outlet shell 3;
the impeller mechanism is connected with the driving mechanism; the driving mechanism is electrically connected with the control mechanism;
the impeller mechanism is used for sucking the separated airflow containing the sand and the dust;
the driving mechanism is used for driving the impeller mechanism to rotate;
and the control mechanism is used for controlling the driving mechanism to start or close.
3-5 mounting seats are arranged on the outer surface of the air inlet shell 1, the air inlet shell 1 is fixedly mounted on an engine 8 through the mounting seats, 3 mounting seats are arranged in the embodiment, the 3 mounting seats are mounted on the engine 8 through bolts, and the air inlet shell 1 can be welded on the engine 8 in other design modes; the air inlet shell 1 is in a bent column shape, one end of the air inlet shell is a conical opening, and an annular boss is arranged at the edge of the outer wall of the conical opening; the annular boss end of the air inlet shell 1 is connected with the impeller mechanism, and the other end of the air inlet shell is fixedly connected with a clearing flow channel 6-2 of the particle separator 6 through welding or screw connection to form a channel for discharging air flow containing sand and dust.
The air outlet shell 3 comprises an inner shell, an outer shell and guide vanes 3-1, wherein the inner shell is barrel-shaped, the outer shell is horn-shaped, the diameter of the inner shell is smaller than that of the outer shell, and a part of the inner shell is arranged in the outer shell. The inner shell and the outer shell are coaxially arranged and fixedly connected through the guide vanes 3-1. Preferably, the air outlet housing 3 is formed by casting and integral molding or 3D printing.
The edge of the outer wall of one end of the outer shell of the air outlet shell 3 is provided with an annular boss, a guide vane 3-1 is arranged between the inner shell and the outer shell of the air outlet shell 3, the guide vane 3-1 is a hollow vane and is circumferentially and uniformly distributed at an airflow inlet of the air outlet shell 3, and the number of the vanes is 8-15. The guide vanes 3-1 are mainly used to adjust the direction of the deflected airflow to axial flow. The guide vane 3-1 is C-shaped, and the horizontal section is wing-shaped.
The annular boss end of the air outlet shell 3 is connected with the air inlet shell 1 and the impeller mechanism, and a channel for discharging air flow containing sand and dust is formed between the inner shell and the outer shell of the air outlet shell 3. Meanwhile, when the air flow containing the sand and the dust flows through the air outlet shell 3, the heat generated when the motor 4-2 works can be taken away, and the motor 4-2 is cooled. Preferably, in order to improve the heat dissipation efficiency, the air outlet housing 3 is made of a high heat conduction material, such as an aluminum alloy ZL 114A.
The impeller mechanism comprises an impeller shaft 2-1, a coupler 2-5 and an oblique flow impeller 2-6;
one end of the impeller shaft 2-1 is connected with the coupler 2-5, and the other end of the impeller shaft is fixedly connected with the oblique flow impeller 2-6;
the impeller shaft 2-1 is connected with a driving mechanism through a coupler 2-5;
the impeller shaft 2-1 is used for driving the oblique flow impeller 2-6 to rotate;
the inclined flow impeller 2-6 is used for forming a low-pressure area at the outlet of the cleaning flow channel 6-2, and sucking the air flow containing the sand and the dust from the cleaning flow channel 6-2 of the particle separator 6 into the air inlet shell 1 and further discharging the air flow from the air outlet shell 3.
The impeller mechanism also comprises a quick-release clamp 2-3 and a rotor case 2-4;
the rotor case 2-4 is arranged at the periphery of the oblique flow impeller 2-6 and provides an outer wall for an airflow channel;
and the rotor case 2-4 is connected with the air inlet shell 1 and the air outlet shell 3 through a quick-release clamp 2-3. In another design mode, holes are formed in the air inlet shell 1, the air outlet shell 3 and the rotor case 2-4, and the air inlet shell 1, the air outlet shell 3 and the rotor case 2-4 are fixedly connected through bolts.
The impeller mechanism also comprises a comb tooth ring 2-2, a bearing 2-7 and a bearing seat component 2-8;
the comb tooth ring 2-2 is arranged between the inner shell of the air outlet shell 3 and the impeller shaft 2-1; the bearings 2-7 are arranged in the bearing seat assemblies 2-8; the bearing seat assemblies 2-8 are arranged at the front end of the inner shell of the air outlet shell 3 through bolts; the grate ring 2-2, the bearing 2-7 and the bearing seat assembly 2-8 are coaxially arranged;
the grate ring 2-2 is used for sealing the motor 4-2 and preventing air flow containing sand and dust from entering the motor 4-2;
the bearing 2-7 and the bearing seat assembly 2-8 are used for fixing the impeller shaft 2-1, reducing friction and ensuring long-time stable operation of the oblique flow impeller 2-6.
The driving mechanism comprises a junction box 4-1 and a motor 4-2;
the junction box 4-1 is arranged on the outer surface of the outer shell of the air outlet shell 3; the motor 4-2 is arranged in an annular inner cavity of the inner shell of the air outlet shell 3 and fixedly connected to the inner surface of the inner shell of the air outlet shell 3 through bolts or welding; a lead of the motor 4-2 penetrates through the hollow guide vane 3-1 to be connected to the junction box 4-1;
one end of a motor shaft of the motor 4-2 is connected with the impeller shaft 2-1 through a coupler 2-5, and the motor 4-2 drives the impeller shaft 2-1 to rotate through the coupler 2-5.
The driving mechanism also comprises an end cover 4-3 and a cooling fan 4-4;
the end cover 4-3 is fixedly connected with the tail end of the inner shell of the air outlet shell 3 through bolts or welding; a through hole is formed in the center of the end cover 4-3, and a bearing is arranged in the through hole; one end of a motor shaft of the motor 4-2 penetrates through the bearing and is fixedly connected with the cooling fan 4-4 through a bolt; the motor 4-2 drives the cooling fan 4-4 to rotate through a motor shaft, and then the cooling fan 4-4 generates cooling air flow to take away heat generated when the motor 4-2 operates, so as to cool the motor 4-2.
The driving mechanism also comprises a dustproof mesh enclosure 4-5; the dustproof mesh enclosure 4-5 is arranged on the side of the cooling fan 4-4 and fixedly arranged at the tail end of the inner shell of the air outlet shell 3; and the dustproof mesh enclosure 4-5 is used for preventing the discharged sand and dust from entering the motor 4-2. Preferably, the power of the motor is 10-30 KW, and the rotating speed of the rotating shaft is about 10000-40000 rpm.
The control mechanism comprises a motor controller 5;
the motor controller 5 is arranged in the cockpit; the motor controller 5 is electrically connected with the motor 4-2 through the junction box 4-1; and the motor controller 5 is used for controlling the motor 4-2 to be started or closed according to whether the content of the sand and dust in the actual operation environment exceeds a threshold value. Preferably, the threshold value of the dust content may be set to 53mg/m3。
Preferably, a sand and dust detection device is arranged in the air inlet 6-1 and is electrically connected with the motor 4-2. When the engine 8 runs, the sand and dust detection device is automatically started, the content value of sand and dust in the air sucked through the air inlet 6-1 is automatically detected, when the content of sand and dust in the sucked air is detected to exceed a threshold value, the motor 4-2 is immediately started, and the electrically-driven sand discharge device is started to discharge the sand and dust in the air to the atmosphere.
When the engine 8 runs in a sand environment, the motor controller 5 is started, the motor 4-2 drives the impeller shaft 2-1 to rotate through the coupler 2-5, the impeller shaft 2-1 drives the oblique flow impeller 2-6 to rotate through the spline, low pressure is formed at the outlet of the cleaning flow channel 6-2 of the particle separator 6, under the action of pressure difference, after air flow containing sand passes through the air inlet channel 6-1 of the particle separator 6, a sand-containing air flow (accounting for about 10% -20% of the total air input) which concentrates a large amount of sand enters the air inlet shell 1 through the cleaning flow channel 6-2, after the air flow direction is adjusted, after passing through the oblique flow impeller 2-6, the air is discharged into the atmosphere through the air outlet shell 3. When the air flow containing the sand and the dust passes through the air outlet shell 3, the heat generated by the motor 4.2 on the inner surface of the air outlet shell 3 during working is taken away, so that the purpose of cooling the motor 4-2 is realized, the cooling fan 4-4 and the motor 4-2 synchronously run, and the generated cooling air flow carries out double cooling on the motor 4-2.
Fig. 2 shows a schematic operation of an electrically driven sand discharge device according to an embodiment of the present invention. As shown in figure 2, the outlet of a cleaning flow channel 6-2 of the particle separator 6 is connected with the air inlet shell 1 of the electrically-driven sand discharging device 7, the outlet of a main flow channel 6-3 of the particle separator 6 is connected with the inlet of an engine 8, a motor controller 5 is electrically connected with a motor 4-2 and used for controlling starting or closing, and the motor controller 5 of the electrically-driven sand discharging device 7 is installed in a cockpit. When the engine 8 works in a sand and dust environment, the motor controller 5 can be opened, the electrically-driven sand discharging device 7 runs, after the air flow containing sand and dust passes through the air inlet channel 6-1 of the particle separator 6, the particle separator 6 divides the air flow containing sand and dust into two air flows, one air flow (accounting for about 10-20% of the total air inflow) containing sand and dust with a large amount of concentrated sand and dust is sucked by the electrically-driven sand discharging device 7 through the cleaning flow channel 6-2, passes through the air inlet shell 1 and the air outlet shell 3 in sequence and is discharged into the atmosphere, and the other air flow (accounting for about 80-90% of the total air inflow) containing almost no sand and dust enters the engine 8 through the main air flow channel 6-3 and is used by the engine 8. In a clean environment, the motor controller 5 can be closed, the electrically driven sand discharging device 7 does not operate, most of the air flow (which accounts for no less than 90% of the total air inlet amount) enters the engine 8 after passing through the particle separator 6 and is used by the engine 8, and less of the air flow (which accounts for no more than 10% of the total air inlet amount) flows into the atmosphere through the electrically driven sand discharging device 7.
According to the electrically-driven sand discharging device for the particle separator of the aircraft engine, the electrically-driven sand discharging device is controlled by the motor, the electrically-driven sand discharging device can be selectively started or stopped according to the actual environment, and the electrically-driven sand discharging device can be stopped in a non-sand environment, so that most of air flow enters the engine, and the power of the engine in the non-sand environment is improved; the electrically-driven sand discharge device is closed in a non-dust environment, so that the output power of the engine can be saved; the coupling between the electrically-driven sand discharge device and an engine transmission system is removed by controlling the electrically-driven sand discharge device through the motor, so that the safety and reliability risks of the engine caused by the fault of the electrically-driven sand discharge device can be reduced to a certain extent.
In the description of the present invention, it is to be understood that the terms "upper", "side", "end", "outer", "inner", and the like, indicate orientation or positional relationship, are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced components or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be taken as limiting the present invention. As used herein, "include" and the like are open-ended terms, meaning including but not limited to. As used herein, "connected" and "electrically connected" include direct connection between two components, and also include indirect connection between two components through other components or circuits.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (10)

1. An aircraft engine particle separator is with electrically driven formula sand discharging device which characterized in that includes: the impeller mechanism, the driving mechanism and the control mechanism;
the impeller mechanism is connected with the driving mechanism; the driving mechanism is electrically connected with the control mechanism;
the impeller mechanism is used for sucking the separated airflow containing the sand and the dust;
the driving mechanism is used for driving the impeller mechanism to rotate;
and the control mechanism is used for controlling the driving mechanism to start or close.
2. Electrically driven sand discharge device for an aircraft engine particle separator according to claim 1, further comprising an air intake housing (1);
the outer surface of the air inlet shell (1) is provided with a mounting seat, and the air inlet shell (1) is fixedly mounted on an engine (8) through the mounting seat; the air inlet shell (1) is in a bent column shape, one end of the air inlet shell is a conical opening, and an annular boss is arranged at the edge of the outer wall of the conical opening; the end of the annular boss of the air inlet shell (1) is connected with the impeller mechanism, and the other end of the annular boss is connected with a clearing flow passage (6-2) of the particle separator (6).
3. Electrically driven sand discharge device for an aircraft engine particle separator according to claim 1, further comprising an air outlet housing (3);
the air outlet shell (3) comprises an inner shell, an outer shell and guide vanes (3-1), wherein the inner shell is barrel-shaped, the outer shell is horn-shaped, the diameter of the inner shell is smaller than that of the outer shell, a part of the inner shell is arranged in the outer shell, and the inner shell and the outer shell are coaxially arranged and fixedly connected through the guide vanes (3-1);
an annular boss is arranged at the edge of the outer wall of one end of the outer shell of the air outlet shell (3); a guide vane (3-1) is arranged between the inner shell and the outer shell of the air outlet shell (3); the guide vanes (3-1) are hollow vanes and are uniformly distributed at the airflow inlet of the air outlet shell (3) in the circumferential direction;
the annular boss end of the air outlet shell (3) is connected with the air inlet shell (1) and the impeller mechanism;
and a channel for discharging the air flow containing the sand and the dust is formed between the inner shell and the outer shell of the air outlet shell (3).
4. An electrically driven sand discharge device for an aircraft engine particle separator according to claim 3, wherein the impeller mechanism comprises an impeller shaft (2-1), a coupling (2-5) and a diagonal flow impeller (2-6);
one end of the impeller shaft (2-1) is connected with the coupler (2-5), and the other end of the impeller shaft is fixedly connected with the oblique flow impeller (2-6);
the impeller shaft (2-1) is connected with a driving mechanism through a coupling (2-5);
the impeller shaft (2-1) is used for driving the oblique flow impeller (2-6) to rotate;
the inclined flow impeller (2-6) is used for forming a low-pressure area at the outlet of the cleaning flow channel (6-2) and sucking the air flow containing the sand and the dust into the air inlet shell (1) from the cleaning flow channel (6-2) of the particle separator (6) and then discharging the air flow from the air outlet shell (3).
5. The electrically driven sand discharge device for an aircraft engine particle separator according to claim 4, wherein said impeller mechanism further comprises a quick release clip (2-3) and a rotor case (2-4);
the rotor case (2-4) is arranged at the periphery of the oblique flow impeller (2-6);
the rotor case (2-4) is connected with the air inlet shell (1) and the air outlet shell (3) through quick-release clamps (2-3).
6. The electrically driven sand discharge device for an aircraft engine particle separator according to claim 4, wherein the impeller mechanism further comprises a grate ring (2-2), a bearing (2-7) and a bearing housing assembly (2-8);
the comb tooth ring (2-2) is arranged between the inner shell of the air outlet shell (3) and the impeller shaft (2-1); the bearings (2-7) are arranged in the bearing seat assemblies (2-8); the bearing seat assemblies (2-8) are arranged at the front end of the inner shell of the air outlet shell (3) through bolts; the comb tooth ring (2-2), the bearing (2-7) and the bearing seat assembly (2-8) are coaxially arranged;
the grate ring (2-2) is used for preventing sand and dust;
the bearing (2-7) and the bearing seat assembly (2-8) are used for fixing the impeller shaft (2-1).
7. Electrically driven sand discharge device for an aircraft engine particle separator according to claim 4, characterised in that the drive mechanism comprises a junction box (4-1) and an electric motor (4-2);
the junction box (4-1) is arranged on the outer surface of the outer shell of the air outlet shell (3); the motor (4-2) is arranged in an inner shell annular inner cavity of the air outlet shell (3) and fixedly connected to the inner surface of an inner shell of the air outlet shell (3) through bolts or welding; the lead of the motor (4-2) is connected to the junction box (4-1) through the guide vane (3-1);
and a motor shaft of the motor (4-2) is connected with the impeller shaft (2-1) through a coupling (2-5).
8. Electrically driven sand discharge device for an aircraft engine particle separator according to claim 7, characterised in that the drive mechanism further comprises an end cover (4-3) and a cooling fan (4-4);
the end cover (4-3) is fixedly connected with the inner shell of the air outlet shell (3) through bolts or welding; a bearing is arranged at the center of the end cover (4-3); one end of a motor shaft of the motor (4-2) penetrates through the bearing and is fixedly connected with the cooling fan (4-4) through a bolt;
the cooling fan (4-4) is used for cooling the motor (4-2).
9. The electrically driven sand discharge device for an aircraft engine particle separator according to claim 8, wherein said drive mechanism further comprises a dust screen (4-5);
the dustproof mesh enclosure (4-5) is arranged on the side of the cooling fan (4-4) and fixedly installed at the tail end of the inner shell of the air outlet shell (3);
and the dustproof mesh enclosure (4-5) is used for preventing the discharged sand and dust from entering the motor (4-2).
10. Electrically driven sand discharge device for an aircraft engine particle separator according to claim 7, wherein said control means comprise a motor controller (5);
the motor controller (5) is arranged in the cockpit;
the motor controller (5) is electrically connected with the motor (4-2) through a junction box (4-1);
and the motor controller (5) is used for controlling the motor (4-2) to be started or closed.
CN202110972985.4A 2021-08-24 2021-08-24 Electric driving type sand discharging device for particle separator of aircraft engine Pending CN113530857A (en)

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CN202110972985.4A CN113530857A (en) 2021-08-24 2021-08-24 Electric driving type sand discharging device for particle separator of aircraft engine

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Application Number Priority Date Filing Date Title
CN202110972985.4A CN113530857A (en) 2021-08-24 2021-08-24 Electric driving type sand discharging device for particle separator of aircraft engine

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