CN113551920A - Comprehensive monitoring type aircraft engine output power stability detector - Google Patents
Comprehensive monitoring type aircraft engine output power stability detector Download PDFInfo
- Publication number
- CN113551920A CN113551920A CN202110841477.2A CN202110841477A CN113551920A CN 113551920 A CN113551920 A CN 113551920A CN 202110841477 A CN202110841477 A CN 202110841477A CN 113551920 A CN113551920 A CN 113551920A
- Authority
- CN
- China
- Prior art keywords
- sleeve
- groove
- bevel gear
- extends
- disc
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 238000012544 monitoring process Methods 0.000 title claims abstract description 63
- 239000007788 liquid Substances 0.000 claims description 43
- 230000005540 biological transmission Effects 0.000 claims description 27
- 238000010438 heat treatment Methods 0.000 claims description 20
- 238000001816 cooling Methods 0.000 claims description 17
- 239000004020 conductor Substances 0.000 claims description 11
- 239000004065 semiconductor Substances 0.000 claims description 11
- 238000005096 rolling process Methods 0.000 claims description 10
- 238000005057 refrigeration Methods 0.000 claims description 9
- 230000017525 heat dissipation Effects 0.000 claims description 7
- 230000005415 magnetization Effects 0.000 claims description 7
- 238000001514 detection method Methods 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims 2
- 238000000034 method Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L3/00—Measuring torque, work, mechanical power, or mechanical efficiency, in general
- G01L3/24—Devices for determining the value of power, e.g. by measuring and simultaneously multiplying the values of torque and revolutions per unit of time, by multiplying the values of tractive or propulsive force and velocity
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/42—Devices characterised by the use of electric or magnetic means
- G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
- G01P3/48—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
- G01P3/481—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals
- G01P3/487—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by rotating magnets
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/20—Control of temperature characterised by the use of electric means with sensing elements having variation of electric or magnetic properties with change of temperature
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Automation & Control Theory (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a comprehensive monitoring type aircraft engine output power stability detector, which relates to the technical field of aircraft engines and comprises an engine body, wherein an output shaft is arranged in the engine body, the comprehensive monitoring type aircraft engine output power stability detector is characterized in that a first sleeve, a second sleeve and a second limiting groove are arranged, an operator places the first sleeve on one side of the output shaft and then places the second sleeve on the other side of the output shaft, the first sleeve and the second sleeve are fixed through mounting screws, a first limiting block on one side of a first rotating disc is inserted into the first limiting groove, a second limiting block is inserted into the second limiting groove, the operator twists a jackscrew body, one end of the jackscrew body pushes a clamping sleeve to extrude towards the direction of the output shaft, so that the detector is mounted on the aircraft engine, and the detector is convenient to mount and dismount, therefore, the detector is convenient to use.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a comprehensive monitoring type aero-engine output power stability detector.
Background
The aircraft engine is a highly complex and precise thermal machine, is used as the heart of an aircraft, is not only the power of the aircraft flight, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine. Aircraft engines include various types of turbojet or turbofan engines, turboshaft/turboprop engines, ramjet engines, and piston engines. Along with the development of unmanned aerial vehicle model aeroplane and model ship technique, small-size aeroengine also uses in a large number, needs detect the output stability when current small-size aeroengine uses, but current detector is inconvenient to be installed, and the back of breaking down appears in the magnetization piece in the hall sense part simultaneously, is difficult for changing.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a comprehensive monitoring type aircraft engine output power stability detector, which solves the problems in the background technology.
In order to achieve the purpose, the invention is realized by the following technical scheme: a comprehensive monitoring type aircraft engine output power stability detector comprises an engine body, an output shaft is arranged inside the engine body, a first sleeve is arranged at the top of the engine body, a second sleeve is arranged at the top of the engine body and positioned on one side of the first sleeve, through grooves are formed in the bottoms and the tops of the first sleeve and the second sleeve, the top end of the output shaft penetrates through the through grooves and extends to the positions above the first sleeve and the second sleeve, a second rotating disc is arranged at the top of an inner cavity of the first sleeve, a first rotating disc is arranged at the top of an inner cavity of the second sleeve, jackscrew grooves are formed in the first rotating disc and the second rotating disc and positioned on two sides of the output shaft, jackscrew bodies are arranged in the jackscrew grooves, and one ends of the two jackscrew bodies respectively extend to one side of the first rotating disc and one side of the second rotating disc and are provided with clamping sleeves, the bottom of second rolling disc is provided with first transmission bevel gear subassembly, the bottom of first rolling disc is provided with second transmission bevel gear subassembly, first transmission bevel gear subassembly constitutes the transmission bevel gear structure with second transmission bevel gear subassembly, one side of first sleeve inner chamber is rotated and is connected with first axis of rotation, one side of second sleeve inner chamber is rotated and is connected with the second axis of rotation, first bevel gear has been cup jointed to the one end of first axis of rotation, the second bevel gear has been cup jointed to the one end of second axis of rotation, first bevel gear all is connected with transmission bevel gear structure meshing with the second bevel gear, one side of second sleeve is provided with the monitoring case, one side of first sleeve is provided with the fixed case.
Optionally, the second spacing groove has been seted up in the outside that the top of first sleeve inner chamber just was located logical groove, first spacing groove has been seted up in the outside that the top of second sleeve inner chamber just was located logical groove, first spacing inslot portion sliding connection has first spacing post, the bottom of first spacing post and the top fixed connection of first rotating disk, the spacing inslot portion sliding connection of second has the spacing post of second, the bottom of the spacing post of second is connected with the top of second rotating disk.
Optionally, second fixing parts are arranged on two sides of the second rotating disc, first fixing parts are arranged on two sides of the first rotating disc, fixing screws are connected to the insides of the second fixing parts in a threaded manner, one ends of the fixing screws extend into the insides of the first fixing parts and are connected with the insides of the first fixing parts in a threaded manner, second limiting grooves are formed in one sides, close to the second bevel gear, of the first bevel gear, second limiting blocks are arranged in the second limiting grooves, one ends of the second limiting blocks are connected with one sides of the second bevel gear, first limiting grooves are formed in one sides, close to the first rotating disc, of the second rotating disc, first limiting blocks are arranged in the first limiting grooves, and one ends of the first limiting blocks are connected with one sides of the first rotating disc.
Optionally, one end of the first rotating shaft extends into the fixed box and is provided with a conductor module, and an electromagnetic coil is arranged inside the fixed box and outside the conductor module.
Optionally, a monitoring cavity is formed inside the monitoring box, a liquid cavity is formed inside the monitoring box and outside the monitoring cavity, one end of the second rotating shaft extends into the monitoring cavity and is fixedly sleeved with a disc, a plurality of caulking grooves are formed outside the disc, magnetizing blocks are placed inside the caulking grooves, mounting grooves are formed in one sides of the caulking grooves inside the disc, connecting grooves are formed in two sides of the mounting grooves inside the disc, fixing keys are connected with the inner cavities of the connecting grooves in a sliding mode, mounting blocks are placed inside the mounting grooves, key grooves are formed in one ends, close to the fixing keys, of the outer sides of the mounting blocks, one ends of the fixing keys extend into the key grooves, unlocking grooves are formed in the outer sides of the disc, thread grooves are formed between the unlocking grooves and the connecting grooves inside the disc, fixing nails are arranged inside the unlocking grooves, the one end of staple extends to inside and with the inside threaded connection of thread groove, the one end of staple extends to inside the spread groove and offsets with one side of fixed key, the spread groove inner chamber just is located the equal sliding connection in the staple outside and has a coupling spring, one side of staple just is located inside the spread groove and all is provided with the connection rope, the one end of connecting the rope all is connected with one side of fixed key, the top of monitoring intracavity chamber is provided with hall detecting element.
Optionally, one side of monitoring case is provided with the cooler bin, one side of monitoring case and the bottom that is located the cooler bin are provided with the liquid pump, the one end of liquid pump extends to the liquid intracavity portion, the inside first spiral pipe that is provided with of cooler bin, the other end of liquid pump extends to the cooler bin inside and is connected with the one end of first spiral pipe, the other end of first spiral pipe extends to the outside of cooler bin and is provided with the second solenoid valve, the one end of second solenoid valve is provided with three way connection, three way connection's the other end is provided with the ooff valve, the one end of ooff valve extends to the liquid intracavity portion, one side of cooler bin is provided with the semiconductor refrigeration piece, one side of cooler bin and the outside that is located the semiconductor refrigeration piece are provided with the radiator bin.
Optionally, one side of monitoring box and the top that is located the cooler bin are provided with the heating cabinet, the inside second spiral pipe that is provided with of heating cabinet, the inside both sides that just are located the second spiral pipe of heating cabinet all are provided with the heater bar, the bottom of second spiral pipe extends to the below of heating cabinet and is provided with first solenoid valve, the one end of first solenoid valve is connected with three way connection's top, the top of second spiral pipe extends to the top of heating cabinet and extends to the liquid intracavity portion, one side that the top of monitoring intracavity chamber just is located hall detecting element is provided with temperature sensor.
Optionally, the first sleeve and the second sleeve are both mounted on the engine body through mounting screws.
The invention provides a comprehensive monitoring type aircraft engine output power stability detector which has the following beneficial effects:
1. the comprehensive monitoring type aircraft engine output power stability detector is provided with a first sleeve, a second sleeve and a second limiting groove, an operator places the first sleeve on one side of an output shaft, then the second sleeve is placed on the other side of the output shaft, the first sleeve and the second sleeve are fixed through the mounting screw, the first limiting block on one side of the first rotating disk is inserted into the first limiting groove, the second limiting block is inserted into the second limiting groove, then the operator screws the fixing screw to screw one end of the fixing screw into the first fixing piece, then an operator twists the jackscrew body to enable one end of the jackscrew body to push the jacket to extrude towards the direction of the output shaft, therefore, the detector is installed on the aero-engine, so that the detector can be conveniently installed and detached, and the detector is convenient to use.
2. This comprehensive monitoring type aeroengine output power stability detector, through being provided with the magnetization piece, fixed key and staple, make when the magnetization piece breaks down, can be convenient change the magnetization piece, thereby make the use of this detector comparatively convenient, be convenient for change the magnetization piece, through being provided with first spiral pipe and second spiral pipe, make when monitoring intracavity inside temperature changes, can adjust the temperature of monitoring intracavity portion, make hall detecting element be in comparatively stable temperature environment, prevent that the work of the too big influence magnetization piece of temperature variation and hall detecting element.
Drawings
FIG. 1 is a schematic view of the internal structure of the present invention;
FIG. 2 is a schematic view of the internal structure of the monitoring box of the present invention;
FIG. 3 is a schematic view of the external structure of the present invention;
FIG. 4 is a schematic bottom view of the top of the inner chambers of the first and second sleeves of the present invention;
FIG. 5 is a schematic top view of the inner structure of the second rotary disk and the first rotary disk according to the present invention;
FIG. 6 is a side view of the inner structure of the disc according to the present invention;
FIG. 7 is a schematic bottom view of the internal structure of the first bevel gear and the second bevel gear of the present invention;
FIG. 8 is an enlarged view taken at A of FIG. 1 in accordance with the present invention;
FIG. 9 is an enlarged view taken at B of FIG. 5 in accordance with the present invention;
FIG. 10 is an enlarged view of FIG. 2 at C of the present invention;
fig. 11 is an enlarged view of fig. 2D according to the present invention.
In the figure: 1. an engine body; 2. a first sleeve; 3. a second sleeve; 4. an output shaft; 5. a first rotating shaft; 6. a second rotating shaft; 7. a first bevel gear; 8. a second bevel gear; 9. a first rotating disk; 10. a first limit groove; 11. a first limit post; 12. a second limit groove; 13. a second limit post; 14. a second rotating disk; 15. a first drive bevel gear assembly; 16. a second drive bevel gear assembly; 17. a first limiting groove; 18. a first limiting block; 19. a wire jacking groove; 20. a jackscrew body; 21. a jacket; 22. a fixed box; 23. an electromagnetic coil; 24. a conductor module; 25. a monitoring box; 26. a liquid chamber; 27. monitoring the cavity; 28. a Hall detection element; 29. a disc; 30. caulking grooves; 31. a magnetized block; 32. mounting grooves; 33. mounting blocks; 34. connecting grooves; 35. a connecting spring; 36. connecting ropes; 37. a fixed key; 38. a thread groove; 39. fixing nails; 40. unlocking the groove; 41. a keyway; 42. a heating box; 43. a cooling tank; 44. a liquid pump; 45. a first spiral pipe; 46. a semiconductor refrigeration sheet; 47. a second spiral pipe; 48. a heating rod; 49. a three-way joint; 50. a first solenoid valve; 51. a second solenoid valve; 52. an on-off valve; 53. a second limiting block; 54. a second limiting groove; 55. a first fixing member; 56. a second fixing member; 57. a set screw; 58. a heat dissipation box; 59. a through groove.
Detailed Description
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 only a part of the embodiments of the present invention, and not all of the embodiments.
Referring to fig. 1 to 11, the present invention provides a technical solution: a comprehensive monitoring type aircraft engine output power stability detector comprises an engine body 1, an output shaft 4 is arranged inside the engine body 1, a first sleeve 2 is arranged at the top of the engine body 1, a second sleeve 3 is arranged at the top of the engine body 1 and positioned on one side of the first sleeve 2, through grooves 59 are formed in the bottoms and the tops of the first sleeve 2 and the second sleeve 3, the top end of the output shaft 4 penetrates through the through grooves 59 to extend to the upper portions of the first sleeve 2 and the second sleeve 3, a second rotating disc 14 is arranged at the top of an inner cavity of the first sleeve 2, a first rotating disc 9 is arranged at the top of an inner cavity of the second sleeve 3, ejector screw grooves 19 are formed in the first rotating disc 9 and the second rotating disc 14 and positioned on two sides of the output shaft 4, ejector screw bodies 20 are arranged inside the ejector screw grooves 19, one ends of the two ejector screw bodies 20 extend to one sides of the first rotating disc 9 and the second rotating disc 14 respectively and are provided with jackets 21, the bottom of second rolling disc 14 is provided with first transmission bevel gear subassembly 15, the bottom of first rotary disc 9 is provided with second transmission bevel gear subassembly 16, first transmission bevel gear subassembly 15 constitutes the transmission bevel gear structure with second transmission bevel gear subassembly 16, one side of 2 inner chambers of first sleeve is rotated and is connected with first axis of rotation 5, one side of 3 inner chambers of second sleeve is rotated and is connected with second axis of rotation 6, first bevel gear 7 has been cup jointed to the one end of first axis of rotation 5, second bevel gear 8 has been cup jointed to the one end of second axis of rotation 6, first bevel gear 7 all is connected with the meshing of transmission bevel gear structure with second bevel gear 8, one side of second sleeve 3 is provided with monitoring box 25, one side of first sleeve 2 is provided with fixed box 22.
Wherein, the top of the inner chamber of the first sleeve 2 and the outside that is located through groove 59 have seted up the second spacing groove 12, the top of the inner chamber of the second sleeve 3 and the outside that is located through groove 59 have seted up first spacing groove 10, the inside sliding connection of first spacing groove 10 has first spacing post 11, the bottom of first spacing post 11 and the top fixed connection of first rotating disk 9, the inside sliding connection of second spacing groove 12 has second spacing post 13, the bottom of second spacing post 13 is connected with the top of second rotating disk 14, conveniently spacing first transmission bevel gear subassembly 15 and second transmission bevel gear subassembly 16, make output shaft 4 drive first transmission bevel gear subassembly 15 and second transmission bevel gear subassembly 16 and rotate, thereby make first transmission bevel gear subassembly 15 and second transmission bevel gear subassembly 16 drive second bevel gear 8 and first bevel gear 7 and rotate.
Wherein, both sides of second rolling disc 14 all are provided with second mounting 56, the both sides of first rolling disc 9 all are provided with first mounting 55, the inside equal threaded connection of second mounting 56 has set screw 57, the one end of set screw 57 all extends to inside and with the inside threaded connection of first mounting 55, second restricted slot 54 has all been seted up to one side that first bevel gear 7 is close to second bevel gear 8, the inside second stopper 53 that all is provided with of second restricted slot 54, the one end of second stopper 53 all is connected with one side of second bevel gear 8, first restricted slot 17 has all been seted up to one side that second rolling disc 14 is close to first rolling disc 9, first stopper 18 all is provided with to the inside of first restricted slot 17, the one end of first stopper 18 all is connected with one side of first rolling disc 9, make second bevel gear 8 and first bevel gear 7 rotate in step.
Wherein, the one end of first axis of rotation 5 extends to inside fixed case 22 and is provided with conductor module 24, the outside that fixed case 22 is inside and is located conductor module 24 is provided with solenoid 23, one side of fixed case 22 is provided with power module, first axis of rotation 5 rotates and drives conductor module 24 and rotate in solenoid 23 is inside and cuts magnetic induction line motion for induced-current that produces in conductor module 24's the closed circuit, with current input to battery module storage, be used for supplying power to this detector.
Wherein, the monitoring chamber 27 is provided inside the monitoring box 25, the liquid chamber 26 is provided inside the monitoring box 25 and outside the monitoring chamber 27, one end of the second rotating shaft 6 extends to the inside of the monitoring chamber 27 and is fixedly sleeved with the disc 29, a plurality of caulking grooves 30 are provided outside the disc 29, the magnetizing blocks 31 are all placed inside the caulking grooves 30, the mounting grooves 32 are all provided inside the disc 29 and on one side of the caulking grooves 30, the connecting grooves 34 are both provided inside the disc 29 and on both sides of the mounting groove 32, the fixed keys 37 are all slidably connected inside the inner cavities of the connecting grooves 34, the mounting blocks 33 are all placed inside the mounting grooves 32, the key grooves 41 are all provided on one ends of the outer sides of the mounting blocks 33 close to the fixed keys 37, one ends of the fixed keys 37 all extend to the inside of the key grooves 41, the unlocking grooves 40 are provided on the outer sides of the disc 29, the threaded grooves 38 are all provided inside the disc 29 and between the unlocking grooves 40 and the connecting grooves 34, the inside staple 39 that is provided with of groove 40 that unlocks, the one end of staple 39 extend to inside and with the inside threaded connection of thread groove 38, the one end of staple 39 extends to inside and offset with one side of fixed key 37 of spread groove 34, the equal sliding connection in spread groove 34 inner chamber just is located the staple 39 outside has coupling spring 35, one side of staple 39 just is located spread groove 34 inside and all is provided with the connection rope 36, the one end of connecting rope 36 all is connected with one side of fixed key 37, the top of monitoring chamber 27 inner chamber is provided with hall detection element 28, be convenient for change magnetized block 31.
Wherein, one side of the monitoring box 25 is provided with a cooling box 43, one side of the monitoring box 25 and the bottom of the cooling box 43 are provided with a liquid pump 44, one end of the liquid pump 44 extends to the inside of the liquid chamber 26, the inside of the cooling box 43 is provided with a first spiral pipe 45, the other end of the liquid pump 44 extends to the inside of the cooling box 43 and is connected with one end of the first spiral pipe 45, the other end of the first spiral pipe 45 extends to the outside of the cooling box 43 and is provided with a second electromagnetic valve 51, one end of the second electromagnetic valve 51 is provided with a three-way joint 49, the other end of the three-way joint 49 is provided with a switch valve 52, one end of the switch valve 52 extends to the inside of the liquid chamber 26, one side of the cooling box 43 is provided with a semiconductor refrigeration sheet 46, one side of the cooling box 43 and the outside of a heat dissipation hole of the semiconductor refrigeration sheet 46 are provided with a heat dissipation box 58, one side of the inner cavity of the heat dissipation box 58 is provided with a fan, the outside of the heat dissipation box 58 is provided with a plurality of heat dissipation holes, the fan dissipates heat from the semiconductor cooling fins 46, and facilitates control of the temperature of the operating environment of the hall sensing element 28 when the temperature inside the monitoring chamber 27 is high.
Wherein, one side of monitoring box 25 and the top that is located cooler bin 43 are provided with heating cabinet 42, the inside second spiral pipe 47 that is provided with of heating cabinet 42, the inside both sides that are located second spiral pipe 47 of heating cabinet 42 all are provided with heater bar 48, the bottom of second spiral pipe 47 extends to the below of heating cabinet 42 and is provided with first solenoid valve 50, the one end of first solenoid valve 50 is connected with three way connection 49's top, the top of second spiral pipe 47 extends to heating cabinet 42's top and extends to liquid chamber 26 inside, the top of monitoring chamber 27 inner chamber just is located one side of hall detecting element 28 and is provided with temperature sensor, conveniently when monitoring chamber 27 inside temperature is lower, control hall detecting element 28 operational environment temperature.
Wherein, first sleeve 2 and second sleeve 3 are all installed on engine body 1 through mounting screw, conveniently fix first sleeve 2 and second sleeve 3.
To sum up, when the comprehensive monitoring type aircraft engine output power stability detector is used, an operator places the first sleeve 2 on one side of the output shaft 4, then places the second sleeve 3 on the other side of the output shaft 4, fixes the first sleeve 2 and the second sleeve 3 through the mounting screws, at this time, the first limiting block 18 on one side of the first rotating disc 9 is inserted into the first limiting groove 17, the second limiting block 53 is inserted into the second limiting groove 54, then the operator twists the fixing screw 57 to enable one end of the fixing screw 57 to be screwed into the first fixing part 55, then the operator twists the jackscrew body 20 to enable one end of the jackscrew body 20 to push the jacket 21 to extrude towards the output shaft 4, so that in the rotating process of the output shaft 4, the first rotating disc 9 and the second rotating disc 14 are driven to rotate through the jacket 21 to enable the first limiting column 11 and the second limiting column 13 to move along the second limiting groove 12 and the inner cavity of the first limiting groove 10, the transmission bevel gear structure composed of the first transmission bevel gear assembly 15 and the second transmission bevel gear assembly 16 drives the first bevel gear 7 and the second bevel gear 8 to rotate, the second rotating shaft 6 and the first rotating shaft 5 rotate, the first rotating shaft 5 rotates to drive the conductor module 24 to rotate in the electromagnetic coil 23 to cut magnetic induction lines, induced current generated in a closed circuit of the conductor module 24 is input to the battery module to be stored for supplying power to the detector, the second rotating shaft 6 rotates to drive the disc 29 to rotate, the disc 29 drives the magnetized block 31 to rotate, when the magnetized block 31 passes through a corresponding end of the hall detection element 28, the hall detection element 28 senses the circuit to act and output the induced pulse, so that the rotating speed of the output shaft 4 is calculated, the output power of the aircraft engine is calculated, and the change of the output power of the aircraft engine within a period of time is detected, therefore, the stability of the output power of the aircraft engine is detected, when the temperature sensor detects that the temperature inside the monitoring cavity 27 is too high, the semiconductor refrigeration piece 46 and the liquid pump 44 are started, the semiconductor refrigeration piece 46 cools the conducting liquid inside the cooling box 43, at this time, one end of the liquid pump 44 pumps out the liquid inside the liquid cavity 26, then the other end of the liquid pump 44 discharges the liquid into the first spiral pipe 45, meanwhile, the first electromagnetic valve 50 is in a closed state, the switch valve 52 and the second electromagnetic valve 51 are in an open state, after the conducting liquid cools the liquid inside the first spiral pipe 45, the liquid is discharged into the liquid cavity 26 through the three-way joint 49 and the switch valve 52, the inside of the monitoring cavity 27 is cooled, when the temperature sensor detects that the temperature inside the monitoring cavity 27 is too low, at this time, the switch valve 52 and the semiconductor refrigeration piece 46 are closed, the second electromagnetic valve 51 and the first electromagnetic valve 50 are opened, when the heating rod 48 is started, one end of the liquid pump 44 pumps out the liquid in the liquid chamber 26, the other end of the liquid pump 44 discharges the liquid into the first spiral pipe 45 and then into the second spiral pipe 47, at this time, the heating rod 48 heats the conduction liquid in the heating box 42, the conduction liquid heats the liquid in the second spiral pipe 47 and then discharges the liquid into the liquid chamber 26, when the magnetized block 31 is in failure, an operator twists the thread groove 38 to make the thread groove 38 drive the fixed key 37 to move towards the inside of the connecting groove 34 through the connecting rope 36, so that one end of the fixed key 37 moves out of the inside of the key slot 41, then the magnetized block 31 can be taken out, then in the process of inserting the mounting block 33 arranged at one side of the new magnetized block 31 into the inside of the mounting groove 32, the arc end of the mounting block 33 pushes the fixed key 37 to move towards the inside of the connecting groove 34, when the key slot 41 moves to the position corresponding to the fixed key 37, the connecting spring 35 pushes one end of the fixing key 37 to be inserted into the key groove 41, and then the operator screws the unlocking groove 40 so that one end of the fixing nail 39 abuts against the fixing key 37.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (8)
1. The utility model provides a comprehensive monitoring type aeroengine output power stability detector, includes engine body (1), its characterized in that: an output shaft (4) is arranged inside the engine body (1), a first sleeve (2) is arranged at the top of the engine body (1), a second sleeve (3) is arranged at the top of the engine body (1) and located on one side of the first sleeve (2), through grooves (59) are formed in the bottoms and the tops of the first sleeve (2) and the second sleeve (3), the top end of the output shaft (4) penetrates through the through grooves (59) to extend to the positions above the first sleeve (2) and the second sleeve (3), a second rotating disc (14) is arranged at the top of an inner cavity of the first sleeve (2), a first rotating disc (9) is arranged at the top of an inner cavity of the second sleeve (3), screw jacking grooves (19) are formed in the first rotating disc (9) and the second rotating disc (14) and located on two sides of the output shaft (4), screw jacking bodies (20) are arranged inside the screw jacking grooves (19), one end of each of the two jackscrew bodies (20) extends to one side of the first rotating disc (9) and the second rotating disc (14) respectively and is provided with a jacket (21), the bottom end of the second rotating disc (14) is provided with a first transmission bevel gear assembly (15), the bottom end of the first rotating disc (9) is provided with a second transmission bevel gear assembly (16), the first transmission bevel gear assembly (15) and the second transmission bevel gear assembly (16) form a transmission bevel gear structure, one side of the inner cavity of the first sleeve (2) is rotatably connected with a first rotating shaft (5), one side of the inner cavity of the second sleeve (3) is rotatably connected with a second rotating shaft (6), one end of the first rotating shaft (5) is sleeved with a first bevel gear (7), one end of the second rotating shaft (6) is sleeved with a second bevel gear (8), and the first bevel gear (7) and the second bevel gear (8) are both meshed with the transmission bevel gear structure, one side of the second sleeve (3) is provided with a monitoring box (25), and one side of the first sleeve (2) is provided with a fixing box (22).
2. The comprehensive monitoring type aircraft engine output power stability detector of claim 1, characterized in that: the utility model discloses a spacing post of first spacing post (11), including first sleeve (2), first spacing post (13), second spacing post (13), first sleeve (2) inner chamber, first sleeve (3) inner chamber, first spacing post (11) and second sleeve (13), first sleeve (2) inner chamber, first sleeve (59) inner chamber, first spacing groove (10) have been seted up to the outside that just is located logical groove (59), first spacing groove (10) inside sliding connection has first spacing post (11), the bottom of first spacing post (11) and the top fixed connection of first rolling disc (9), second spacing groove (12) inside sliding connection has second spacing post (13), the bottom of second spacing post (13) is connected with the top of second rolling disc (14).
3. The comprehensive monitoring type aircraft engine output power stability detector of claim 1, characterized in that: the two sides of the second rotating disc (14) are respectively provided with a second fixing piece (56), the two sides of the first rotating disc (9) are respectively provided with a first fixing piece (55), the inside of the second fixing piece (56) is in threaded connection with a fixing screw (57), one end of the fixing screw (57) extends into the first fixing piece (55) and is in threaded connection with the inside of the first fixing piece (55), one side of the first bevel gear (7) close to the second bevel gear (8) is respectively provided with a second limiting groove (54), the inside of the second limiting groove (54) is respectively provided with a second limiting block (53), one end of the second limiting block (53) is respectively connected with one side of the second bevel gear (8), one side of the second rotating disc (14) close to the first rotating disc (9) is respectively provided with a first limiting groove (17), and the inside of the first limiting groove (17) is respectively provided with a first limiting block (18), one end of each first limiting block (18) is connected with one side of the first rotating disc (9).
4. The comprehensive monitoring type aircraft engine output power stability detector of claim 1, characterized in that: one end of the first rotating shaft (5) extends into the fixed box (22) and is provided with a conductor module (24), and an electromagnetic coil (23) is arranged inside the fixed box (22) and on the outer side of the conductor module (24).
5. The comprehensive monitoring type aircraft engine output power stability detector of claim 1, characterized in that: monitoring chamber (27) has been seted up to monitoring case (25) inside, monitoring case (25) inside just is located the outside of monitoring chamber (27) and has seted up sap cavity (26), the one end of second axis of rotation (6) extends to monitoring chamber (27) inside and fixed cup joints disc (29), a plurality of caulking groove (30) have been seted up to the outside of disc (29), magnetization piece (31) have all been placed to caulking groove (30) inside, disc (29) inside just is located one side of caulking groove (30) and has all seted up mounting groove (32), the both sides that disc (29) inside just is located mounting groove (32) have all seted up spread groove (34), the equal sliding connection of spread groove (34) inner chamber has fixed key (37), installation piece (33) have all been placed to mounting groove (32) inside, the one end that the installation piece (33) outside is close to fixed key (37) has all seted up keyway (41), the one end of fixed key (37) all extends to inside keyway (41), the outside of disc (29) has all been seted up and has been unlocked groove (40), inside just being located of disc (29) between unlocking groove (40) and spread groove (34) all has been seted up thread groove (38), inside being provided with staple (39) of unlocking groove (40), the one end of staple (39) extends to inside and with thread groove (38) inside threaded connection, the one end of staple (39) extends to inside and offsets with one side of fixed key (37) of spread groove (34), the equal sliding connection has connecting spring (35) in spread groove (34) inner chamber just being located the staple (39) outside, one side of staple (39) just is located inside all being provided with of spread groove (34) and connects rope (36), the one end of connecting rope (36) all is connected with one side of fixed key (37), and a Hall detection element (28) is arranged at the top of the inner cavity of the monitoring cavity (27).
6. The comprehensive monitoring type aircraft engine output power stability detector of claim 1, characterized in that: a cooling box (43) is arranged on one side of the monitoring box (25), a liquid pump (44) is arranged on one side of the monitoring box (25) and is positioned at the bottom of the cooling box (43), one end of the liquid pump (44) extends into the liquid cavity (26), a first spiral pipe (45) is arranged inside the cooling box (43), the other end of the liquid pump (44) extends into the cooling box (43) and is connected with one end of the first spiral pipe (45), the other end of the first spiral pipe (45) extends to the outer side of the cooling box (43) and is provided with a second electromagnetic valve (51), a three-way joint (49) is arranged at one end of the second electromagnetic valve (51), a switch valve (52) is arranged at the other end of the three-way joint (49), one end of the switch valve (52) extends into the liquid cavity (26), and a semiconductor refrigerating sheet (46) is arranged on one side of the cooling box (43), and a heat dissipation box (58) is arranged on one side of the cooling box (43) and positioned on the outer side of the semiconductor refrigeration sheet (46).
7. The comprehensive monitoring type aircraft engine output power stability detector of claim 5, characterized in that: one side of monitoring box (25) and the top that is located cooler bin (43) are provided with heating cabinet (42), inside second spiral pipe (47) that is provided with of heating cabinet (42), the inside both sides that just are located second spiral pipe (47) of heating cabinet (42) all are provided with heater bar (48), the bottom of second spiral pipe (47) extends to the below of heating cabinet (42) and is provided with first solenoid valve (50), the one end of first solenoid valve (50) is connected with the top of three way connection (49), the top of second spiral pipe (47) extends to the top of heating cabinet (42) and extends to liquid chamber (26) inside, the top of monitoring chamber (27) inner chamber and the one side that is located hall detecting element (28) are provided with temperature sensor.
8. The comprehensive monitoring type aircraft engine output power stability detector of claim 1, characterized in that: the first sleeve (2) and the second sleeve (3) are both mounted on the engine body (1) through mounting screws.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110841477.2A CN113551920A (en) | 2021-07-26 | 2021-07-26 | Comprehensive monitoring type aircraft engine output power stability detector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110841477.2A CN113551920A (en) | 2021-07-26 | 2021-07-26 | Comprehensive monitoring type aircraft engine output power stability detector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113551920A true CN113551920A (en) | 2021-10-26 |
Family
ID=78104431
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110841477.2A Withdrawn CN113551920A (en) | 2021-07-26 | 2021-07-26 | Comprehensive monitoring type aircraft engine output power stability detector |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113551920A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0417984A1 (en) * | 1989-09-15 | 1991-03-20 | General Motors Corporation | Method and apparatus for determining engine exhaust backpressure |
| AU1058695A (en) * | 1993-11-23 | 1995-06-13 | Wilcom Tufting Pty. Ltd. | A mechanical tufting head |
| CN103293003A (en) * | 2013-06-25 | 2013-09-11 | 中国航空动力机械研究所 | Turboshaft engine super-twist testing device and method |
| CN104913934A (en) * | 2015-05-07 | 2015-09-16 | 潍柴动力股份有限公司 | Engine test bench and crankshaft front-end output test device |
| CN107132049A (en) * | 2017-06-24 | 2017-09-05 | 东北大学 | Aero-engine blisk rotating vibration test platform and application based on laser vibration measurer |
| CN109932187A (en) * | 2019-03-22 | 2019-06-25 | 中国航发湖南动力机械研究所 | Utilize the method and system for the power that Aerial weapon equipment test run generates |
| CN110057591A (en) * | 2019-04-15 | 2019-07-26 | 中国航发湖南动力机械研究所 | Turboaxle motor air inlet heating system |
| CN110296845A (en) * | 2019-08-02 | 2019-10-01 | 灵翼飞航（天津）科技有限公司 | A kind of coaxial double-oar unmanned plane dynamic test device |
| CN111693864A (en) * | 2020-06-15 | 2020-09-22 | 中国科学院电工研究所 | Propeller characteristic simulation experiment device based on permanent magnet synchronous motor |
| CN111912619A (en) * | 2020-06-01 | 2020-11-10 | 浙江海骆航空科技有限公司 | Axial containment test device and method for turbine engine exhaust casing |
-
2021
- 2021-07-26 CN CN202110841477.2A patent/CN113551920A/en not_active Withdrawn
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0417984A1 (en) * | 1989-09-15 | 1991-03-20 | General Motors Corporation | Method and apparatus for determining engine exhaust backpressure |
| US5051909A (en) * | 1989-09-15 | 1991-09-24 | General Motors Corporation | Method and means for determining exhaust backpressure in a crankcase scavenged two-stoke engine |
| AU1058695A (en) * | 1993-11-23 | 1995-06-13 | Wilcom Tufting Pty. Ltd. | A mechanical tufting head |
| CN103293003A (en) * | 2013-06-25 | 2013-09-11 | 中国航空动力机械研究所 | Turboshaft engine super-twist testing device and method |
| CN104913934A (en) * | 2015-05-07 | 2015-09-16 | 潍柴动力股份有限公司 | Engine test bench and crankshaft front-end output test device |
| CN107132049A (en) * | 2017-06-24 | 2017-09-05 | 东北大学 | Aero-engine blisk rotating vibration test platform and application based on laser vibration measurer |
| CN109932187A (en) * | 2019-03-22 | 2019-06-25 | 中国航发湖南动力机械研究所 | Utilize the method and system for the power that Aerial weapon equipment test run generates |
| CN110057591A (en) * | 2019-04-15 | 2019-07-26 | 中国航发湖南动力机械研究所 | Turboaxle motor air inlet heating system |
| CN110296845A (en) * | 2019-08-02 | 2019-10-01 | 灵翼飞航（天津）科技有限公司 | A kind of coaxial double-oar unmanned plane dynamic test device |
| CN111912619A (en) * | 2020-06-01 | 2020-11-10 | 浙江海骆航空科技有限公司 | Axial containment test device and method for turbine engine exhaust casing |
| CN111693864A (en) * | 2020-06-15 | 2020-09-22 | 中国科学院电工研究所 | Propeller characteristic simulation experiment device based on permanent magnet synchronous motor |
Non-Patent Citations (1)
| Title |
|---|
| 花家寿等: "轿车自动无级变速器的试验研究及其试验装置的开发", 《传动技术》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3618263A1 (en) | Engine with a permanent magnet electric machine | |
| CN113551920A (en) | Comprehensive monitoring type aircraft engine output power stability detector | |
| CN215216805U (en) | Automatic door opening and closing device and refrigerator having the same | |
| KR100474329B1 (en) | Compressor driving control method of refrigerator | |
| BRPI0803661B1 (en) | double flow turbocharger | |
| US3538759A (en) | Test stand for vehicle engines | |
| CN202651983U (en) | Isolated transmission device | |
| CN205610430U (en) | Novel radiating vibrating motor of automatically regulated | |
| CN101907368A (en) | Refrigerated constant temperature pot | |
| CN117559059A (en) | New energy battery protection device and use method thereof | |
| CN215835740U (en) | Insulation detector controller | |
| CN217819346U (en) | Cooling device for low-temperature test of automobile engine | |
| US4932325A (en) | Safety device for an aerodynamic body fuse | |
| CN212718281U (en) | Integrated electric bypass valve structure | |
| CN223513830U (en) | Explosion-proof control box with interlocking mechanism | |
| CN113944518B (en) | A Turbine Blade Dynamic Test System Based on Circulating Micropipe | |
| CN222805345U (en) | A low temperature centrifugal separation device | |
| CN114215819A (en) | Overheating-prevention hydraulic oil cylinder | |
| CN216133906U (en) | Lithium cell BMS fast-assembling heat dissipation casing | |
| US20240141926A1 (en) | Axial pump with adjustable impeller | |
| US20250276430A1 (en) | Power tool with impulse assembly | |
| CN215724269U (en) | Temperature control device convenient to overhaul of semiconductor refrigerator | |
| CN117766349B (en) | Intelligent circuit breaker with angular displacement sensor | |
| CN218212279U (en) | Fluid monitoring devices with rapid cooling function | |
| CN112763940B (en) | Testing device for oil extractor of gas turbine starter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20211026 |
|
| WW01 | Invention patent application withdrawn after publication |