CN109655119A - Fuel mass flow sensor - Google Patents

Fuel mass flow sensor Download PDF

Info

Publication number
CN109655119A
CN109655119A CN201910145446.6A CN201910145446A CN109655119A CN 109655119 A CN109655119 A CN 109655119A CN 201910145446 A CN201910145446 A CN 201910145446A CN 109655119 A CN109655119 A CN 109655119A
Authority
CN
China
Prior art keywords
cyclone
tube
air deflector
mass flow
flow sensor
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.)
Granted
Application number
CN201910145446.6A
Other languages
Chinese (zh)
Other versions
CN109655119B (en
Inventor
江五贵
李源才
廖述梅
吕辉
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nanchang Hangkong University
Original Assignee
Nanchang Hangkong University
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Nanchang Hangkong University filed Critical Nanchang Hangkong University
Priority to CN201910145446.6A priority Critical patent/CN109655119B/en
Publication of CN109655119A publication Critical patent/CN109655119A/en
Application granted granted Critical
Publication of CN109655119B publication Critical patent/CN109655119B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01FMEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F1/00Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through the meter in a continuous flow
    • G01F1/76Devices for measuring mass flow of a fluid or a fluent solid material
    • G01F1/86Indirect mass flowmeters, e.g. measuring volume flow and density, temperature or pressure
    • G01F1/88Indirect mass flowmeters, e.g. measuring volume flow and density, temperature or pressure with differential pressure measurement to determine the volume flow

Abstract

The present invention provides a kind of fuel mass flow sensor, the fuel mass flow sensor includes: tube body, and the tube body includes: tube wall and the cavity that is surrounded by tube wall, and the cavity has arrival end and outlet end;The fuel mass flow sensor further include: air deflector, cyclone, turbine, rectifier and the measurement gear for being arranged in the cavity, and being sequentially arranged along the sequence of arrival end to outlet end;The fuel mass flow sensor further include: magnetoelectric induction device;The fuel mass flow sensor further include: rotary shaft, along being axially disposed between connecting shaft and outlet end for tube body;The turbine, the rectifier and measurement gear are set in the rotary shaft.The present invention has many advantages, such as that structure is simple, high reliablity, practical, measurement accuracy is high.

Description

Fuel mass flow sensor
Technical field
The present invention relates to fields of measurement, and in particular to a kind of fuel mass flow sensor.
Background technique
In all mission phases of aircraft, fuel system, which all continuously should be able to be conveyed reliably to power device, fires Oil.In actual operation, it needs to carry out the fuel mass flow of engine precise measurement, accurate metering is to make engine Operating is effectively stablized, and is the important measures for improving aeroplane performance.In order to accurately carry out the measurement of fuel mass flow, The basis that precise translation is above-mentioned work is carried out to fuel mass flow signal.Because during its work in different engine Under, engine fuel supply is unstable, and degree of fluctuation is violent, and existing fuel mass flow measurement is inaccurate.
In conclusion following problems exist in the prior art: the fuel system of aircraft, fuel mass flow measurement be not smart Really.
Summary of the invention
The present invention provides a kind of fuel mass flow sensor, and to solve the fuel system of aircraft, fuel mass flow is surveyed Measure inaccurate problem.
For this purpose, the present invention proposes that a kind of fuel mass flow sensor, the fuel mass flow sensor include:
Tube body, the tube body include: tube wall and the cavity that is surrounded by tube wall, and the cavity has arrival end and outlet end;
The fuel mass flow sensor further include: setting arrives outlet end in the cavity, and along arrival end Air deflector, cyclone, turbine, rectifier and the measurement gear that sequence is sequentially arranged;
Air deflector is fixedly connected on the inner wall of tube wall;The air deflector is hemispherical, and the outer surface of the air deflector is Air deflector hemisphere face and the air deflector bottom surface for being connected to air deflector hemisphere face edge;The vertical air deflector bottom surface of the axis of air deflector, The axial direction of the axis parallel tubes of air deflector;The air deflector has multiple axial pass-through holes, the length side of each axial pass-through holes To axial parallel with tube body;Each axial pass-through holes run through air deflector hemisphere face and air deflector bottom surface;The axial pass-through holes will Become the axial direction of tube body by the directional velocity of the fluid of air deflector;
Cyclone is arranged between air deflector and outlet end;The outer surface of the cyclone includes: cyclone curved surface and company It connects in the cyclone bottom surface of cyclone curved edges, the axis of cyclone and the axis of air deflector are consistent;The axis of cyclone hangs down Straight cyclone bottom surface;The cyclone is the stereochemical structure formed by cyclone curved surface and cyclone bottom surface;On cyclone curved surface Equipped with a plurality of centrifugation runner, the speed for the fluid that each centrifugation runner will go on the curved surface of cyclone becomes eddy flow speed Degree, the swirl velocity direction can be decomposed into the tangential direction of tube body and the axial direction of tube body;
The fuel mass flow sensor further include: connecting shaft, through the axial direction of the air deflector and the axis of cyclone To;The air deflector and cyclone are all disposed in the connecting shaft;
Turbine, be arranged between cyclone and outlet end, turbine by from cyclone curved surface come out fluid impact and turn It is dynamic;
Rectifier is arranged between turbine and outlet end, and rectifier becomes the directional velocity of the fluid flowed out from turbine The axial direction of tube body;The rectifier includes: multiple blades being arranged radially along tube body, and the plane where each blade is parallel The axial direction of tube body;
Gear is measured, is arranged between rectifier and outlet end;
The fuel mass flow sensor further include: the magnetoelectric induction device of measurement gear revolution (revolving speed) is arranged in pipe On the inner wall of wall, for example, magnetoelectric induction device is wired to engine control system;
The fuel mass flow sensor further include: rotary shaft is axially disposed within connecting shaft and outlet end along tube body Between;The turbine, the rectifier and measurement gear are set in the rotary shaft;The turbine and measurement gear with it is described Rotary shaft is fixedly connected;The blade is fixed on the tube body and is connected in the rotary shaft by what bearing was able to rotate.
Further, the connecting shaft has both ends, the respectively rear end of the front end of connecting shaft and connecting shaft, connecting shaft Front end is close to arrival end, and far from arrival end, air deflector hemisphere face, and connecting shaft are stretched out in the front end of connecting shaft for the rear end of connecting shaft Front end be first pointed or the first taper or the first pencil point-shaped.
Further, the rotary shaft has both ends, the respectively rear end of the front end of rotary shaft and rotary shaft, rotary shaft Front end is close to the rear end of connecting shaft, and far from the rear end of connecting shaft, the front end of rotary shaft is second pointed or for the rear end of rotary shaft Two tapers or the second pencil point-shaped.
Further, the bore of the arrival end is less than the bore of outlet end.
Further, the cyclone be taper or hemisphere, the centrifugation runner be curve, each centrifugation runner or The extended line of each centrifugation runner can be met on the axis of tube body.
Further, the air deflector is threadedly attached on the inner wall of tube wall.
Further, the connecting shaft and the rotary shaft separate setting.
Further, cyclone bottom surface is 30-35mm at a distance from rectifier.
Further, each blade is fixedly connected on the inner wall of tube wall, and the measurement gear is spur gear.
Further, outside diameter of gear 15-20cm, turbine outer diameter 24-30cm are measured
Sensor of the invention is installed on the left of engine fan case, the top of Transfer Gearbox, with aircraft fuel oil system System is connected.The traffic transformation of fuel oil is tach signal and then passes through the derivation of equation and be converted into electric signal and be transmitted to display by the present invention In instrument or signal pickup assembly.
Fuel oil enters cyclone 3, the eddy flow by the axial pass-through holes 21 on air deflector from the arrival end 11 of tube body Device makes fuel oil that speed be become tangential direction by runner thereon, and fuel oil flow direction is become jet stream, the fuel oil of tangential velocity Small power turbine will be driven quickly to rotate, if tangential velocity increases, power turbine angular speed is also increased with it;Conversely, also So, therefore, even if fuel delivery is unstable, degree of fluctuation is violent, and measurement gear all can be in fuel supply volume realization ratio Variation, the problem of failure will not occurs because becoming larger by fuel supply volume.The fuel oil gone out from power turbine flow is eddy flow, rectifier The fuel oil speed flowed out from turbine is turned round directly, is tangentially done work with reducing to the greatest extent to measurement gear.It measures gear and is equipped with arteries and veins Generator is rushed, measurement gear rotation using measurement gear (impulse generator) tachometric survey in rotary shaft and then is converted into combustion The mass flow of oil.
For example, can issue electric pulse because of magnetic flux change with the rotation of measurement gear and generate an initial pulse Signal generates a terminate pulse signal when second tooth passes through coil.The time interval of initial pulse and terminate pulse is big Small directly proportional to fuel mass flow, time interval signal is converted into fuel mass flow signal and is transmitted to sustainer calculating Machine system, by conversion, to indicate fuel mass flow.Traditional measurement method is that the flow of fuel oil is converted to pressure, It is calculated using law article, clockwork spring is the material of elasticity, there is certain memory capability, when thus there is error, and designing , there are also a highest limit, fuel flow is excessive for it, it is possible to and it is more than that this highest limits, thus, fuel flow measurement is possible to lose Spirit.But the present invention, there will be no so more problems, is limited using revolving speed without highest, and sensitiveer.
Detailed description of the invention
Fig. 1 is the schematic view of the front view of fuel mass flow sensor of the invention;
Fig. 2 is the schematic perspective view of the inside of fuel mass flow sensor of the invention, wherein eliminating part Tube wall;
Fig. 3 is the schematic view of the front view of the inside of fuel mass flow sensor of the invention;Wherein eliminate part Tube wall;
Fig. 4 is the schematic perspective view of first angle of air deflector of the invention;
Fig. 5 is the schematic perspective view of second angle of air deflector of the invention;
Fig. 6 is the overlooking structure diagram of Fig. 4;
Fig. 7 is the schematic perspective view of cyclone of the invention;
Fig. 8 is the schematic view of the front view of cyclone of the invention;
Fig. 9 is the left view structural representation of cyclone of the invention;
Figure 10 is the right side structural representation of cyclone of the invention;
Figure 11 is the schematic perspective view of turbine of the invention;
Figure 12 is the side structure schematic view of turbine of the invention;
Figure 13 is the overlooking structure diagram of turbine of the invention;
Figure 14 is the schematic perspective view that the blade of rectifier of the invention is connect with tube wall;
Figure 15 is the side structure schematic view that the blade of rectifier of the invention is connect with tube wall;
Figure 16 is the schematic perspective view that rotary shaft of the invention is connect with measurement gear;
Figure 17 is the schematic view of the front view that rotary shaft of the invention is connect with measurement gear;
Figure 18 is the schematic perspective view of electromagnetic inductor of the invention.
Drawing reference numeral explanation:
1, tube body;2, air deflector;3, cyclone;4, rectifier;5, gear is measured;6, magnetoelectric induction device;7, connecting shaft;8, Rotary shaft;9, turbine;
11, arrival end;12, outlet end;21, axial pass-through holes;23, air deflector hemisphere face;25, air deflector bottom surface;31, from Heart runner;33, cyclone curved surface;35, cyclone bottom surface;41, blade;71, the front end of connecting shaft;81, the front end of rotary shaft.
Specific embodiment
For a clearer understanding of the technical characteristics, objects and effects of the present invention, this hair of Detailed description of the invention is now compareed It is bright.
As shown in Figure 1, Figure 2 and Figure 3, the present invention proposes a kind of fuel mass flow sensor, the fuel mass flow Sensor includes:
Tube body 1, the tube body 1 are circumferentially closed, comprising: tube wall and the cavity surrounded by tube wall, the cavity have Arrival end 11 and outlet end 12;Arrival end 11 can be equipped with the external screw thread for connection;
The fuel mass flow sensor further include: setting arrives outlet end in the cavity, and along arrival end Air deflector 2, cyclone 3, turbine 9, rectifier 4 and the measurement gear 5 that sequence is sequentially arranged;
As shown in Fig. 2, Fig. 3, Fig. 4, Fig. 5 and Fig. 6, air deflector 2 is fixedly connected on the inner wall of tube wall;The air deflector 2 For hemispherical, the outer surface of the air deflector is air deflector hemisphere face 23 and the air deflector bottom for being connected to air deflector hemisphere face edge Face 25;25 closed stream lending device hemisphere face of air deflector bottom surface, 23 edge, the vertical air deflector bottom surface 25 of the axis of air deflector, air deflector The axial direction of axis parallel tubes;The air deflector 2 have multiple axial pass-through holes 21, the length direction of each axial pass-through holes 21 with The axial direction of tube body is parallel;Each axial pass-through holes 21 run through air deflector hemisphere face 23 and air deflector bottom surface 25;The axial pass-through holes 21 will become the axial direction of tube body by the directional velocity of the fluid (fuel oil) of air deflector;
As shown in Fig. 7, Fig. 8, Fig. 9 and Figure 10, cyclone 3 is arranged between air deflector and outlet end, that is, is arranged in water conservancy diversion The downstream of device 2;Cyclone is not connect with tube wall, there is slight clearance therewith;The outer surface of the cyclone includes: cyclone song Face 33 and the cyclone bottom surface 35 for being connected to cyclone curved edges, the axis of cyclone and the axis of air deflector are consistent;Eddy flow The vertical cyclone bottom surface of the axis of device;The edge of cyclone curved surface 33 is closed in cyclone bottom surface 35, and the cyclone is by eddy flow The stereochemical structure that device curved surface and cyclone bottom surface are formed;Cyclone curved surface 33 is equipped with a plurality of centrifugation runner 31, each centrifugation The speed for the fluid (fuel oil) that runner 31 will go on the curved surface of cyclone becomes swirl velocity, swirl velocity direction energy Enough it is decomposed into the tangential direction of tube body and the axial direction of tube body;I.e. cyclone 3 makes the speed of fuel oil become having along tube body The speed of the speed of tangential direction and the axial direction along tube body, so as to which impulse turbine, applies tangential direction to turbine Power, and do work;
As shown in Fig. 2, Fig. 3, Fig. 4, Fig. 5, the fuel mass flow sensor further include: connecting shaft 7 is led through described Flow the axial direction of device 2 and the axial direction of cyclone 3;The air deflector 2 and cyclone 3 are all disposed in the connecting shaft 7;Connecting shaft 7 Play support and connection function;
As shown in Figure 11,12 and Figure 13, turbine 9 (also referred to as small power turbine) is arranged between cyclone and outlet end, The downstream of cyclone 3 is set, and the blade of turbine 9 is curved surface, and the axis of the curved surface and turbine is not parallel, and turbine 9 is by from rotation It flows the impact for the fluid that device curved surface 33 comes out and rotates;Cyclone 3 becomes the speed of fuel oil with the tangential direction along tube body Speed and the axial direction along tube body speed, along tube body tangential direction speed to turbine 9 do work, thus make turbine turn It is dynamic;
Rectifier 4 is arranged between turbine and outlet end, that is, the downstream of turbine 9 is arranged in, the rectifier includes: more A blade 41 being arranged radially along tube body, the axial direction of the plane parallel tubes where each blade 41;Rectifier 4 or blade 41 will The directional velocity of the fluid flowed out from turbine 9 becomes the axial direction of tube body, eliminates the speed of tube body tangential direction;Blade 41 is pacified On axis hole, blade 41 is set in rotary shaft by axis hole;
Gear 5 is measured, is arranged between rectifier 4 and outlet end, that is, the downstream of rectifier 4 is set, is measured on gear 5 Equipped with impulse generator;Rotary shaft can be integrated manufacture with measurement gear, be an entirety;
As shown in Figure 1, the fuel mass flow sensor further include: the magnetoelectric induction device 6 of measurement gear revolution;Magnetoelectricity Inductor 6, which is arranged in face measurement gear 5 or magnetoelectric induction device 6 on the inner wall of tube wall and measure gear 5, is located at tube wall On same radial section, accurately to inductively measure the rotation of gear 5, in the rotation process of measurement gear 5, the gear teeth and tooth Convex-concave conversion between slot causes the variation of magnetic flux in magnetoelectric induction device magnetic induction loop, then generates induced field current, then It is wired to engine control system, i.e. the rotation of measurement gear is equivalent to impulse generator.Flight control system is electric by this Signal is converted into fuel mass flow signal, and tube wall is equipped with mounting hole, and magnetoelectric induction device 6 runs through tube wall, and conducting wire is connected to magnetic Electric inductor 6 is located at the part except the outer wall of tube wall, is connected to engine control system;Magnetoelectric induction device by pole piece (forever Long magnet) and the composition such as coil, utilize the measurement gear (rotation of measurement gear is equivalent to impulse generator) in rotary shaft to turn Speed measures and then is converted into the mass flow of fuel oil;Magnetoelectric induction device of the invention, so that magnetic flux changes periodically, thus The electromotive force signal of approximate sine wave is induced in coil, frequency and the relationship of tested revolving speed are f=n*z/60;
As shown in Figure 1, Figure 2, shown in Figure 16 and Figure 17, the fuel mass flow sensor further include: rotary shaft 8, along tube body Be axially disposed between connecting shaft and outlet end;That is the downstream that connecting shaft 7 is set of rotary shaft 8, do not contacted with connecting shaft 7 or Interval setting, the turbine 9 and measurement gear 5 are set in the rotary shaft 8;The turbine 9 and measurement gear 5 and the rotation Shaft 8 is fixedly connected, and is rotated synchronously with rotary shaft 8;The blade 41, which is fixed on, to be able to rotate on the tube body and by bearing It is connected in the rotary shaft, bearing is miniature taper roller bearing, and the changing of the relative positions does not occur for inner ring and rotary shaft cooperation, and outer ring is matched with blade The changing of the relative positions does not also occur for conjunction.Forward, i.e., entire rotary shaft will not play backward for cone ball cone in taper roller bearing.
Fuel oil enters cyclone 3, the eddy flow by the axial pass-through holes 21 on air deflector from the arrival end 11 of tube body Device makes fuel oil that speed be become tangential direction by runner thereon, and fuel oil flow direction is become jet stream, the fuel oil of tangential velocity Small power turbine will be driven quickly to rotate, if tangential velocity increases, power turbine angular speed is also increased with it;Conversely, also So, therefore, even if fuel delivery is unstable, degree of fluctuation is violent, and measurement gear all can be in fuel supply volume realization ratio Variation, the problem of failure will not occurs because becoming larger by fuel supply volume.The fuel oil gone out from power turbine flow is eddy flow, rectifier The fuel oil speed flowed out from turbine is turned round directly, is tangentially done work with reducing to the greatest extent to measurement gear.It measures gear and is equipped with arteries and veins Generator is rushed, measurement gear rotation using measurement gear (the being equivalent to impulse generator) tachometric survey in rotary shaft and then turns Turn to the mass flow of fuel oil.
For example, can issue electric pulse because of magnetic flux change with the rotation of measurement gear and generate an initial pulse Signal generates a terminate pulse signal when second tooth passes through coil.The time interval of initial pulse and terminate pulse is big Small directly proportional to fuel mass flow, time interval signal is converted into fuel mass flow signal and is transmitted to sustainer calculating Machine system, by conversion, to indicate fuel mass flow.Traditional measurement method is that the flow of fuel oil is converted to pressure, It is calculated using law article, clockwork spring is the material of elasticity, there is certain memory capability, when thus there is error, and designing , there are also a highest limit, fuel flow is excessive for it, it is possible to and it is more than that this highest limits, thus, fuel flow measurement is possible to lose Spirit.But the present invention, there will be no so more problems, is limited using revolving speed without highest, and sensitiveer.
In turn, when fuel oil is to after the acting of small power turbine by measurement gear, measurement gear mesh its do it is certain (few Amount) function, and the kinetic energy that gear work done is less than turbine is measured, certain resistance can integrally be generated to fuel oil, so that rotation Spindle speed is unlikely to excessive.So whole system maintains dynamic equilibrium, enables the feelings fluctuated in fuel flow Under condition, be still able to maintain higher sensitivity, and measure the acting of gear mesh fuel oil, improve its temperature, be conducive to fuel oil into Enter combustion chamber preferably to burn.
Further, as shown in Figure 4 and Figure 5, the connecting shaft 7 has both ends, the respectively front end 71 of connecting shaft and company The rear end of spindle, the front end 71 of connecting shaft is close to arrival end, and far from arrival end, the front end 71 of connecting shaft is stretched out for the rear end of connecting shaft Air deflector hemisphere face, and the front end 71 of connecting shaft is first pointed or the first taper or the first pencil point-shaped, to reduce to fuel oil Resistance.
Further, as shown in Figure 16 and Figure 17, the rotary shaft 8 has both ends, respectively 81 He of front end of rotary shaft The rear end of rotary shaft, the front end 81 of rotary shaft is close to the rear end of connecting shaft, and the rear end of rotary shaft is far from the rear end of connecting shaft, rotation The front end of axis is second pointed or the second taper or the second pencil point-shaped.Not so cyclone and turbine, which must not be too far away, cannot form fluid Kinetics relation, there are human factor when guaranteeing assembly again, it is preferred plan that the front end 81 of rotary shaft is arranged, which is top, is prevented Front and back section interferes with each other.Since rotary shaft 8 is arranged close to connecting shaft 7, the front end 81 of rotary shaft is designed as taper or pointed, to keep away When exempting from rotary shaft 8 close to connecting shaft 7, the two contact surface is larger and generates friction work.Preferably, the front end 81 of rotary shaft is cone Pointed, the vertex of cone is located on the axis of rotary shaft 8 or connecting shaft 7, to further decrease friction work.
Further, as shown in Figure 1, Figure 2 and Figure 3, the bore of the arrival end 11 is less than the bore of outlet end 12.According to Continuity equation PVA=constant knows that wherein P is fluid density, and V is fluid velocity, and A is tube body sectional area, in order to enable fluid Enter sensor with larger speed, by reducing tube body sectional area, so that fluid enters the fast speed of sensor, so as to real-time Rapid survey.
Further, such as Fig. 7, Fig. 8, Fig. 9 and Figure 10, the cyclone 3 is taper or hemisphere, the centrifugation runner 31 For curve, for example, involute or parabola, with the effect that realization is preferably centrifuged, the top or each of each centrifugation runner The extended line at the top of the centrifugation runner can be met on the axis of tube body.Be centrifuged runner 31 bottom with cyclone bottom surface 35 Intersection.
Further, the air deflector 2 is threadedly attached on the inner wall of tube wall.The air deflector bottom surface 25 of air deflector 2 It can thicken setting, form rotary table, the edge of rotary table is equipped with external screw thread, and tube wall is equipped with internal screw thread, in this way, air deflector 2 can be with It is conveniently installed in tube body 1.
Further, cyclone bottom surface 35 and turbine 9 minimum distance (in such as Fig. 3, cyclone bottom surface 35 and turbine 9 The lower edge of blade) it is 6-10mm.Cyclone must not be too far away with turbine, not so cannot form fluid dynamics relationship, guarantee again There are human factors when assembly.The minimum distance of cyclone bottom surface and rectifier is 30-35mm, so that cyclone, turbine, rectification There is reasonable matching to the eddy flow of speed, rectification between device.Applicant passes through FEM calculation (such as the finite element for passing through liquid Calculate) and test, obtain above-mentioned data.
Further, each blade 41 is fixedly connected on the inner wall of tube wall, to provide support for rotary shaft 8.The measurement Gear 5 is spur gear, so that fuel oil after the rectification of blade 41, does work to measurement gear 5 less.
Further, tube length 200-240cm, inlet radius 10-15cm, exit radius 24-30cm measure gear Outer diameter 15-20cm, turbine outer diameter 24-30cm.The ratio of the outer diameter and turbine that measure gear is 0.625-0.67.These numerical value It is (such as by fluid FEM calculation, to be learnt, such as can be calculated by software ANSYS Fluent by FEM calculation Learn) and test, obtained preferable space configuration.
Mounting technology scheme of the invention:
Tube body is divided into front half section and second half section,
Step 01: first by air deflector precession front half section, and installation locking nut, bestow certain torque;
Step 02: installation cyclone simultaneously matches upper locking nut, bestows certain torque, front half section completes assembly;
Step 03: to after certain temperature at the axis hole of the connection blade of heating second half section tube body, miniature taper roller bearing is taken out, It is installed on corresponding position;
Step 04: to after certain temperature, taking out rotary shaft from the second half section at the miniature taper roller bearing of 03 assembly parts of heating stepses Rear is inserted into bearing inner race, is locked after cooling with locking nut, and bestow certain torque;
Step 05: miniature integral power turbine is taken out, heats at its axis hole to after certain temperature, is loaded on rotary shaft front end, It is locked after cooling with locking nut, and bestows certain torque;
Step 06: installation magnetoelectric induction device, and bestow certain torque, i.e. completion second half section assembly;
Step 07: finally carrying out general assembly, together by front and back section assembly parts connection (such as welding), and finally bestow certain Torque.
Fuel mass flow calculation formula of the invention are as follows:(this formula is that this product uses Empirical equation, such as can by experiment obtain), Δ P=λ f, f=n*z/60, f be measure gear rotate frequency, unit For secondary/second, wherein QmFor fuel mass flow, using international unit kg/m3.μ is discharge coefficient, this parameter is provided by producer, (value range 1-5, this occurrence are come out by experimental data linear fit).A is the circulation area of tube body outlet end, Unit is square metre.ρ is fuel density, unit (kg/m3) this parameter is tabled look-up to obtain.Δ P is pressure difference before and after sensor, that is, is entered The pressure difference at mouth end and outlet end, unit are International System of Units Pa, this parameter can be acquired by experiment measurement, such as can be used Setting pressure gauge in the tube body or both ends of tube body measures.Proportionality coefficient of the λ between pressure difference and interpulse period be Characteristic, this parameter are provided by producer.N is turbine or the revolving speed for measuring gear, and unit is the International System of Units, turn/per second, this Parameter is measured by magnetoelectric induction device.Z is the number of teeth for measuring gear, and the number of teeth will determine according to TT&C system logical program, such as this Embodiment uses the number of teeth for 15, to guarantee certain precision.
Present invention employs the mass flows of measurement gear rotational speed measurement fuel oil, solve previous sensor in small flow Shi Jingdu is very high, and when having arrived big flow the problem of accuracy decline;And it does not need external power, either stability of flow Or when flowed fluctuation, it can be accurately converted to corresponding gear rotational speed, to be identified by magnetoelectric induction device, and pass through conversion Flow parameter is converted to show.
All parts of the invention can be manufactured by 3D printing, and simple process, the time cycle is short, and performance is secure, Middle air deflector, single shaft and measurement gear are integrated, and rectifier frame is integrated with pipe fitting, and structure is simple, easy to assembly.
The present invention has many advantages, such as that structure is simple, high reliablity, practical, measurement accuracy is high.
The foregoing is merely the schematical specific embodiment of the present invention, the range being not intended to limit the invention.For this Each component part of invention can be combined with each other under conditions of not conflicting, any those skilled in the art, not depart from this Made equivalent changes and modifications, should belong to the scope of protection of the invention under the premise of the conceptions and principles of invention.

Claims (10)

1. a kind of fuel mass flow sensor, which is characterized in that the fuel mass flow sensor includes:
Tube body, the tube body include: tube wall and the cavity that is surrounded by tube wall, and the cavity has arrival end and outlet end;
The fuel mass flow sensor further include: be arranged in the cavity, and along the sequence of arrival end to outlet end Air deflector, cyclone, turbine, rectifier and the measurement gear being sequentially arranged;
Air deflector is fixedly connected on the inner wall of tube wall;The air deflector is hemispherical, and the outer surface of the air deflector is water conservancy diversion Device hemisphere face and the air deflector bottom surface for being connected to air deflector hemisphere face edge;The vertical air deflector bottom surface of the axis of air deflector, water conservancy diversion The axial direction of the axis parallel tubes of device;The air deflector have multiple axial pass-through holes, the length direction of each axial pass-through holes with The axial direction of tube body is parallel;Each axial pass-through holes run through air deflector hemisphere face and air deflector bottom surface;The axial pass-through holes will pass through The directional velocity of the fluid of air deflector becomes the axial direction of tube body;
Cyclone is arranged between air deflector and outlet end;The outer surface of the cyclone includes: cyclone curved surface and is connected to The cyclone bottom surface of cyclone curved edges, the axis of cyclone and the axis of air deflector are consistent;The axis of cyclone vertically revolves Flow device bottom surface;The cyclone is the stereochemical structure formed by cyclone curved surface and cyclone bottom surface;Cyclone curved surface is equipped with The speed of a plurality of centrifugation runner, the fluid that each centrifugation runner will go on the curved surface of cyclone becomes swirl velocity, institute The tangential direction of tube body and the axial direction of tube body can be decomposed by stating swirl velocity direction;
The fuel mass flow sensor further include: connecting shaft, through the axial direction of the air deflector and the axial direction of cyclone;Institute It states air deflector and cyclone is all disposed in the connecting shaft;
Turbine, be arranged between cyclone and outlet end, turbine by from cyclone curved surface come out fluid impact and rotate;
Rectifier is arranged between turbine and outlet end, and the directional velocity of the fluid flowed out from turbine is become tube body by rectifier Axial direction;The rectifier includes: multiple blades being arranged radially along tube body, the plane parallel tubes where each blade Axial direction;
Gear is measured, is arranged between rectifier and outlet end;
The fuel mass flow sensor further include: the magnetoelectric induction device of measurement gear revolution is arranged on the inner wall of tube wall;
The fuel mass flow sensor further include: rotary shaft, along being axially disposed between connecting shaft and outlet end for tube body; The turbine, the rectifier and measurement gear are set in the rotary shaft;The turbine and measurement gear and the rotation Axis is fixedly connected;The blade is fixed on the tube body and is connected in the rotary shaft by what bearing was able to rotate.
2. fuel mass flow sensor as described in claim 1, which is characterized in that the connecting shaft has both ends, respectively For the front end of connecting shaft and the rear end of connecting shaft, the front end of connecting shaft is close to arrival end, and the rear end of connecting shaft is far from arrival end, even Air deflector hemisphere face is stretched out in the front end of spindle, and the front end of connecting shaft is the first taper.
3. fuel mass flow sensor as claimed in claim 2, which is characterized in that the rotary shaft has both ends, respectively For the front end of rotary shaft and the rear end of rotary shaft, the front end of rotary shaft is close to the rear end of connecting shaft, and the rear end of rotary shaft is far from even The rear end of spindle, the front end of rotary shaft are the second taper.
4. fuel mass flow sensor as described in claim 1, which is characterized in that the bore of the arrival end is less than outlet The bore at end.
5. fuel mass flow sensor as described in claim 1, which is characterized in that the cyclone is taper or hemisphere Body, the centrifugation runner are smooth curve, and the extended line of each centrifugation runner or each centrifugation runner can meet at tube body On axis.
6. fuel mass flow sensor as described in claim 1, which is characterized in that the air deflector is threadedly attached in On the inner wall of tube wall.
7. fuel mass flow sensor as described in claim 1, which is characterized in that the connecting shaft and the rotary shaft point Every setting.
8. fuel mass flow sensor as described in claim 1, which is characterized in that cyclone bottom surface is at a distance from rectifier For 30-35cm.
9. fuel mass flow sensor as described in claim 1, which is characterized in that each blade is fixedly connected on the interior of tube wall On wall, the measurement gear is spur gear.
10. fuel mass flow sensor as described in claim 1, which is characterized in that measurement outside diameter of gear 15-20cm, whirlpool Take turns outer diameter 24-30cm.
CN201910145446.6A 2019-02-27 2019-02-27 Fuel mass flow sensor Active CN109655119B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910145446.6A CN109655119B (en) 2019-02-27 2019-02-27 Fuel mass flow sensor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910145446.6A CN109655119B (en) 2019-02-27 2019-02-27 Fuel mass flow sensor

Publications (2)

Publication Number Publication Date
CN109655119A true CN109655119A (en) 2019-04-19
CN109655119B CN109655119B (en) 2020-06-05

Family

ID=66123782

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910145446.6A Active CN109655119B (en) 2019-02-27 2019-02-27 Fuel mass flow sensor

Country Status (1)

Country Link
CN (1) CN109655119B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110595549A (en) * 2019-10-12 2019-12-20 中国石油集团渤海钻探工程有限公司 Intelligent turbine type liquid flow measuring tool

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5005426A (en) * 1988-06-20 1991-04-09 Lew Hyok S Mass-volume vortex flowmeter
CN2599531Y (en) * 2003-01-28 2004-01-14 陈宝荣 Gas turbo-flowmeter
CN102506945A (en) * 2011-10-18 2012-06-20 潘兆铿 Axial flow impedance type water flow sensor
CN103674555A (en) * 2012-09-14 2014-03-26 通用电气公司 Methods and systems for substance profile measurements in gas turbine exhaust
CN104848904A (en) * 2015-06-05 2015-08-19 中国航天空气动力技术研究院 Air duct flow measuring system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5005426A (en) * 1988-06-20 1991-04-09 Lew Hyok S Mass-volume vortex flowmeter
CN2599531Y (en) * 2003-01-28 2004-01-14 陈宝荣 Gas turbo-flowmeter
CN102506945A (en) * 2011-10-18 2012-06-20 潘兆铿 Axial flow impedance type water flow sensor
CN103674555A (en) * 2012-09-14 2014-03-26 通用电气公司 Methods and systems for substance profile measurements in gas turbine exhaust
CN104848904A (en) * 2015-06-05 2015-08-19 中国航天空气动力技术研究院 Air duct flow measuring system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
徐虹艳等: "涡轮叶片尾缘内冷通道旋流冷却特性", 《航空动力学报》 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110595549A (en) * 2019-10-12 2019-12-20 中国石油集团渤海钻探工程有限公司 Intelligent turbine type liquid flow measuring tool

Also Published As

Publication number Publication date
CN109655119B (en) 2020-06-05

Similar Documents

Publication Publication Date Title
CN105716779B (en) Dynamic pressure blade profile probe
Iungo et al. Linear stability analysis of wind turbine wakes performed on wind tunnel measurements
Friehe et al. Deviations from the cosine law for yawed cylindrical anemometer sensors
CN109655119A (en) Fuel mass flow sensor
CN109798945A (en) Fuel mass flow measurement method
US4056976A (en) Mass rate of flow meter
CN106092538B (en) It is a kind of for axial rotation hole discharge coefficient measure device and do not rotate method
US3604265A (en) Fluid-driven mass flowmeter
Fuentes Motion of a helical vortex
CN207556596U (en) A kind of turbine consumption sensor
US3880003A (en) Fluid flowmeter
Joslyn et al. Unsteady three-dimensional turbine aerodynamics
CN206177376U (en) Vane -wheel type flowmeter does not have magnetism signal pickup assembly
Tabakoff et al. Three-dimensional flow measurements in a turbine scroll
CN101672668B (en) Dual-rotor mechanical flow sensor and operating method thereof
CN102589621A (en) Impeller of high-precision rotor type flow transducer and working method of impeller
CN110068439A (en) Rotor blade multiple modal vibrations exciting bank and its motivational techniques
CN1212519C (en) Separated axle needle type prepeller wind gauge for measuring cylinder vortex
CN102393236B (en) Meter coefficient self-correcting method of gas turbine flowmeter
CN109282861A (en) A kind of shaftless gas turbine meter and measurement method
CN107843296A (en) A kind of turbine consumption sensor
CN106153980A (en) A kind of measuring method of low speed wind direction and wind velocity direct reading measurement instrument
US3043139A (en) Mass flow meter
CN209432191U (en) A kind of cold medium flux measuring device in unit laboratory
CN205785352U (en) A kind of turbine flow transducer of wide range ratio

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
GR01 Patent grant
GR01 Patent grant