CN104034465A - Force measurement mechanism in device for measuring blade rotating torque of single blade of controllable-pitch propeller - Google Patents
Force measurement mechanism in device for measuring blade rotating torque of single blade of controllable-pitch propeller Download PDFInfo
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- CN104034465A CN104034465A CN201410310769.3A CN201410310769A CN104034465A CN 104034465 A CN104034465 A CN 104034465A CN 201410310769 A CN201410310769 A CN 201410310769A CN 104034465 A CN104034465 A CN 104034465A
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Abstract
A force measurement mechanism in a device for measuring the blade rotating torque of a single blade of a controllable-pitch propeller comprises the controllable-pitch propeller, and the single measured blade on the controllable-pitch propeller is tightened to a conic section of the top of a force measurement sensor through a clamping ring and a pressing ring. The clamping ring is formed by two semi-rings in a butt joint mode, a conic through hole is formed in the middle of the clamping ring, the inner conic face of the conic through hole and the outer conic face of the conic section of the force measurement sensor have the same conicity, and the conic section of the force measurement sensor is embedded in the conic through hole. The bottom of the force measurement sensor is fastened in a propeller hub of the controllable-pitch propeller after penetrating through the pressing ring, the central axis of the force measurement sensor and the blade rotating axis of the measured blade coincide, and the measured blade is fixedly connected with the clamping ring and the pressing ring through screws. Strain gages, used for measuring the blade rotating torque of the measured blade, in the force measurement sensors are in full-bridge connection. The front end of the propeller hub is fixedly connected with a fairing cap, and the rear end of the propeller hub is connected with a main shaft of a dynamometer through a connection flange. The force measurement mechanism has good static calibration performance and anti-jamming capability and can guarantee measurement accuracy and reliability of the blade rotating torque of the blade of the controllable-pitch propeller.
Description
Technical field
The present invention relates to adjustable pitch propeller hydrodynamics experimental technique field, be specifically related to measure the test unit of adjustable pitch propeller one piece blade rotating vane moment in towing basin or pressure-variable water drum, relate in particular to the force measuring machine of measuring in one piece blade rotating vane torque test device.
Background technology
Adjustable pitch propeller, claim again tuning for Controllable Pitch Propeller, it is one of propulsion plant the most extensively adopting in current naval vessel, different from spacing oar, tuning for Controllable Pitch Propeller can be arranged at the motion in propeller hub by driving, angle with blade rotation and change blade is carried out propeller blades pitch, is realized the increase of main unit load or is reduced, to improve main frame propulsive efficiency, cut operating costs and to obtain good operating performance and maneuverability by the change of the blade angle of pitch.In the time of design real ship tuning for Controllable Pitch Propeller distance adjustor, hydraulic means and propeller hub, the rotating vane moment of (comprise stablely advance, stable retreat and handle rapidly) blade of tuning for Controllable Pitch Propeller is the important parameter of needs consideration in uniform-flow under different steady state conditions, especially for the tuning for Controllable Pitch Propeller of high rotating speed, platter surface ratio, the important parameter that must consider when rotating vane moment is design.Existing the measurement of tuning for Controllable Pitch Propeller rotating vane moment normally tested to carry out by the rotating vane moment of carrying out in pressure-variable water drum, conventionally realize the measurement of single blade rotating vane moment of tuning for Controllable Pitch Propeller with a cantilever strain beam keeping flat along propeller hub center, because its force measuring machine is not to be directly connected with tested blade, thereby force and moment suffered blade cannot be directly delivered on force measuring machine, the measuring accuracy of remote effect rotating vane moment, on the other hand, it directly measures the single component of rotating vane moment, may produce the force and moment disturbing to rotating vane moment and do not measure other, and from the antijamming capability of angle confirmatory measurement device to these interference volumes of test, therefore, cannot guarantee the reliability of rotating vane torgue measurement value.
Summary of the invention
The applicant improves for above-mentioned shortcoming of the prior art, force measuring machine in a kind of tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device is provided, it has good quiet school performance and antijamming capability, can guarantee measuring accuracy and the reliability of tuning for Controllable Pitch Propeller blade rotating vane moment.
Technical scheme of the present invention is as follows:
Force measuring machine in tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device, comprise tuning for Controllable Pitch Propeller, list in tuning for Controllable Pitch Propeller only tested blade tightens up by distance adjustor in the cone section one that is assemblied in force cell top, described distance adjustor comprises clamping ring and compacting ring, clamping ring comprises two semi-rings, described two semi-rings are combined to form the clamping ring of middle part with conical through-hole one, conical through-hole one inner conical surface is consistent with the tapering of cone section one male cone (strobilus masculinus), compacting ring middle part is with the mounting hole connecting, the cone section one of force cell is entrenched in conical through-hole one, the bottom of force cell is fastened in the propeller hub of tuning for Controllable Pitch Propeller through after mounting hole, the rotating vane dead in line of the central axis of force cell and tested blade, tested blade is by two semi-rings of screw and clamping ring, compacting ring is fastenedly connected, on force cell, posting foil gauge, is that full-bridge connects for measuring the foil gauge of tested blade rotating vane moment, propeller hub front end is connected with fair water cone, the rear end of propeller hub and joint flange are fastening and be tightly connected, outside screw propeller pump dynamograph main shaft and joint flange are in transmission connection, propeller hub rear end is connected with watertight connector, and the signal wire of force cell is introduced into outside screw propeller pump dynamograph via watertight connector, joint flange.
Its further technical scheme is:
Cone section one below of described force cell is that xsect is the solid shell of column of octagon, four arcuate structures that limit is indent of the solid shell of column of octagon, and the arcuate structure interval of described indent is arranged, on other four limits of the solid shell of column of octagon, is posted foil gauge; The below of solid shell of column is base, and base and propeller hub are affixed.
Described base is provided with fairlead and logical wire casing, fairlead is positioned at the upper end of logical wire casing and the two communicates, and logical wire casing is communicated with seal groove diametrically, and the other end of seal groove is communicated with wire hole, wire hole is located on base and is through hole, is perfused with water-proof silica-gel in seal groove.
Described force cell is five component sensors, for measuring the rotating vane moment of tested blade, the force and moment that tested blade is subject in water (flow) direction, tested blade with all suffered force and moments in vertical direction of water (flow) direction and tested blade reference line direction, wherein, be that full-bridge connects for measure the foil gauge of the power being subject in water (flow) direction, for measure with water (flow) direction and tested blade reference line direction all in vertical direction the foil gauge of suffered power be that full-bridge is connected, be that half-bridge connects for measure the foil gauge of the moment being subject in water (flow) direction, for measure with water (flow) direction and tested blade reference line direction all in vertical direction the foil gauge of suffered moment be that half-bridge is connected.
Non-tested blade in described tuning for Controllable Pitch Propeller is fastened on propeller hub by roll adjustment circle, roll adjustment circle comprises two semi-rings, described two semi-rings are combined to form the roll adjustment circle of middle part with conical through-hole two, the blade root place of non-tested blade is with cone section two, conical through-hole two inner conical surfaces are consistent with the tapering of cone section two male cone (strobilus masculinus)s, the cone section two of non-tested blade is entrenched in conical through-hole two, and two semi-rings of roll adjustment circle are fastenedly connected by screw and propeller hub respectively.
Technique effect of the present invention:
The present invention, by tested blade directly being tightened up to the structural design of locking on force cell, can be directly delivered on force cell the suffered force and moment of tested blade, than traditional indirect transfer, has improved measuring accuracy; By be combined to form the structural design with clamping ring and the roll adjustment circle of taper mounting hole by two semi-rings, realizing on the adjustable basis of blade pitch, reduce the overall dimensions of tuning for Controllable Pitch Propeller model.
The present invention is by being designed to the construction section of foil gauge on force cell the solid post segment structure that xsect is octagon, and four limits of the solid shell of column of octagon are set to the arcuate structure of indent, the arcuate structure interval of described four indents is arranged, by the above-mentioned improvement to force cell physical construction, test and checking to the antijamming capability to other components by quiet school, explanation, load cell structure of the present invention is rationally symmetrical, bridge balance, stable output, and there is good antijamming capability, further illustrate, the rotating vane moment values that force cell of the present invention records is reliable.In addition, by the setting of seal groove on force cell base, can be to the signal wire of force cell be carried out to effective sealing, guarantee that force cell has good insulating property in process of the test.
Brief description of the drawings
Fig. 1 is force measuring machine one-piece construction schematic diagram of the present invention.
Fig. 2 is A-A cut-open view in Fig. 1.
Fig. 3 is the structural representation of clamping ring of the present invention.
Fig. 4 is B-B revolved sectional view in Fig. 3.
Fig. 5 is the structural representation of compacting ring of the present invention.
Fig. 6 is C-C revolved sectional view in Fig. 5.
Fig. 7 is the structural representation of force cell of the present invention.
Fig. 8 is D-D cut-open view in Fig. 7.
Fig. 9 is the sectional structure schematic diagram of base in force cell of the present invention, also shows the part-structure of solid shell of column in figure.
Figure 10 is the structural representation of looking up of Fig. 9.
Figure 11 is the structural representation of roll adjustment circle of the present invention.
Figure 12 is E-E revolved sectional view in Figure 11.
Figure 13 is the coordinate system schematic diagram of five-component force component that sensor is surveyed of the present invention on roll adjustment circle.
Figure 14 is five component sensor Qiao road principle schematic of the present invention.
Wherein: 1, tuning for Controllable Pitch Propeller; 101, tested blade; 102, propeller hub; 103, non-tested blade; 1031, cone section two; 2, force cell; 201, cone section one; 202, solid shell of column; 203, foil gauge; 204, base; 205, fairlead; 206, logical wire casing; 207, seal groove; 208, wire hole; 3, clamping ring; 301, conical through-hole one; 4, compacting ring; 401, mounting hole; 5, fair water cone; 6, joint flange; 7, watertight connector; 8, roll adjustment circle; 801, conical through-hole two; 9, O RunddichtringO; 10, set nut; 11, outer casing; 12, elasticity gear; 20, temperature compensation loop; 30, bridge balance loop.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described.
See Fig. 1, Fig. 2, Figure 13, force measuring machine of the present invention comprises tuning for Controllable Pitch Propeller 1, list in tuning for Controllable Pitch Propeller 1 only tested blade 101 tightens up by distance adjustor in the cone section 1 that is assemblied in force cell 2 tops, described distance adjustor comprises clamping ring 3 and compacting ring 4, see Fig. 3, Fig. 4, described clamping ring 3 comprises two semi-rings, described two semi-rings are combined to form the clamping ring 3 of middle part with conical through-hole 1, the inner conical surface of conical through-hole 1 is consistent with the tapering of the male cone (strobilus masculinus) of cone section 1, see Fig. 5, Fig. 6, described compacting ring 4 middle parts are with the mounting hole 401 connecting, the cone section 1 of force cell 2 is entrenched in conical through-hole 1, the bottom of force cell 2 is fastened in the propeller hub 102 of tuning for Controllable Pitch Propeller 1 through after mounting hole 401, propeller hub 102 is provided with the space for accommodating force cell 2 diametrically, and be provided with circlip 12 in the described accommodation space of propeller hub 102, clamping ring 3, compacting ring 4 is all assemblied in more than 12 space of circlip, the rotating vane dead in line of the central axis of force cell 2 and tested blade 101, tested blade 101 is fastenedly connected by two semi-rings, the compacting ring 4 of screw and clamping ring 3, and described two semi-rings of clamping ring 3 are all fastenedly connected by the tested blade 101 of screw and its top, the compacting ring 4 of its below, in order to realize the measurement of rotating vane moment, the design of Qiao road is upper, posts foil gauge 203 on force cell 2, is full-bridge connection for measuring the foil gauge 203 of tested blade 101 rotating vane moments, propeller hub 102 front ends are connected with fair water cone 5, the rear end of propeller hub 102 and joint flange 6 are fastenedly connected and are tightly connected by O RunddichtringO 9, outside screw propeller pump dynamograph main shaft and joint flange 6 are in transmission connection, particularly, the main shaft of external helicoid oar pump dynamograph is connected by key with joint flange 6, in order to prevent that pump dynamograph main shaft from rocking, the axle head of pump dynamograph main shaft is locked at by set nut 10 on the end face of joint flange 6, drives thus tuning for Controllable Pitch Propeller 1 to rotate and form required Test Cycle, propeller hub 102 rear ends are connected with watertight connector 7, and the signal wire of force cell 2 is introduced into outside screw propeller pump dynamograph via watertight connector 7, joint flange 6, outer casing 11 can be set up in the outside of joint flange.Wherein, screw propeller pump dynamograph belongs to ripe prior art.
Further, see Fig. 7, Fig. 8, Fig. 9, Figure 10, cone section one 201 belows of described force cell 2 are that xsect is the solid shell of column 202 of octagon, four arcuate structures that limit is indent of the solid shell of column 202 of octagon, and the arcuate structure interval of described indent is arranged, on other four limits of the solid shell of column 202 of octagon, is posted foil gauge 203; The below of solid shell of column 202 is base 204, and base 204 is affixed with propeller hub 102.The solid shell of column 202 that posts foil gauge 203 is designed to symmetrical solid construction, can ensure that force cell 2 is in the time being subject to torsional interaction, strain output in symmetric position is strictly identical, improve measuring accuracy and the antijamming capability of force cell 2, simultaneously, the internal stress that the design of the arcuate structure of described indent can effectively be removed force cell 2 and made material, reduce stress and concentrate the impact that sensor measurement precision is caused, reduce the cumulative stress of other component outputs to the output of rotating vane moment components, further improve measuring accuracy and the antijamming capability of force cell 2.
The base 204 of force cell 2 is provided with fairlead 205 and logical wire casing 206, fairlead 205 is positioned at the upper end of logical wire casing 206 and the two communicates, logical wire casing 206 is communicated with seal groove 207 diametrically, the other end of seal groove 207 is communicated with wire hole 208, wire hole 208 is located on base 204 and is through hole, in seal groove 207, be perfused with water-proof silica-gel, wherein, four fairleads 205 are uniformly distributed along the circumference on base 204, and it is preferably the hole being in tilted layout, preferably the angle of its axis and surface level is 45 °, the central axis of logical wire casing 206 now overlaps with the central shaft of base 204, the signal wire of force cell 2 is first by fairlead 205, logical wire casing 206 enters seal groove 207, in seal groove 207, pour into water-proof silica-gel and complete the sealing to sensor signal lines, signal wire after sealing is unified oppositely from wire hole 208 outlets, watertightness performance through this force cell 2 after treatment is good, soak and pull out and measure its insulation values after one day, still more than reaching 100 megohms.
In order to verify the reliability of the force cell 2 rotating vane moment values of surveying, in order to detect the antijamming capability of force cell 2 to the force and moment in other directions, force cell 2 of the present invention is not the simple component sensor of only measuring rotating vane moment, but adopt five component sensors, for measuring the rotating vane moment of tested blade 101, the force and moment that tested blade 101 is subject in water (flow) direction, tested blade 101 with all suffered force and moments in vertical direction of water (flow) direction and tested blade 101 reference line directions, the Coordinate system definition of described five measurement components in tuning for Controllable Pitch Propeller 1 is shown in Figure 13, be x direction along water (flow) direction, the reference line direction of tested blade 101 is y direction, z direction meets right-hand rule, be and all vertical directions of x direction and y direction, My shown in figure is the rotating vane moment direction of tested blade 101, rotating vane moment direction is defined as and makes pitch augment direction for just, see Figure 14, in the design of Qiao road, be full-bridge connection for measuring the foil gauge 203 of tested blade 101 rotating vane moment My, be full-bridge connection for measure the foil gauge 203 of the power Fx being subject in water (flow) direction, for measure with water (flow) direction and tested blade 101 reference line directions all in vertical direction the foil gauge 203 of suffered power Mz be connected for full-bridge, be half-bridge connection for measure the foil gauge 203 of the moment Mx being subject in water (flow) direction, for measure with water (flow) direction and tested blade 101 reference line directions all in vertical direction the foil gauge 203 of suffered moment Mz be connected for half-bridge, in the design of Qiao road, consider the bridge balance between temperature compensation and each loop, temperature compensation loop 20 and bridge balance loop 30 have been designed, ensure the measuring accuracy of this five component sensor, and improve antijamming capability, temperature compensation and bridge balance are sensor technical field conventional design.
Propeller hub 102 sizes of considering tuning for Controllable Pitch Propeller 1 model are less, be subject to the restriction in propeller hub 102 interior spaces, if use the pitch adjusting structure of existing tuning for Controllable Pitch Propeller, it is hydraulic mechanism, push rod, slide, conventional pitch adjusting structure in the prior aries such as eccentric pin, conventionally can exceed the design conditions of tuning for Controllable Pitch Propeller 1 model, therefore, for model test, for the non-tested blade 10 in tuning for Controllable Pitch Propeller 1 has designed special pitch adjusting structure, be that non-tested blade 103 in tuning for Controllable Pitch Propeller 1 is fastened on propeller hub 102 by roll adjustment circle 8, see Figure 11, Figure 12, described roll adjustment circle 8 comprises two semi-rings, described two semi-rings are combined to form the roll adjustment circle 8 of middle part with conical through-hole 2 801, the blade root place of non-tested blade 103 is with cone section 2 1031, conical through-hole 2 801 inner conical surfaces are consistent with the tapering of cone section 2 1031 male cone (strobilus masculinus)s, the cone section 2 1031 of non-tested blade 103 is entrenched in conical through-hole 2 801, described two semi-rings of roll adjustment circle 8 are fastenedly connected by screw and propeller hub 102 respectively, after roll adjustment circle 8 is assemblied on propeller hub 102, it is circular structure that the assembly of propeller hub 102 and multiple roll adjustment circles 8 forms an xsect.
The torgue measurement of 1 single blade rotating vane of tuning for Controllable Pitch Propeller is carried out equally in pressure-variable water drum, the rear end of joint flange 6 is connected with hollow shafting, force measuring machine of the present invention and hollow shafting entirety are placed in pressure-variable water drum, and entirety is fixed on pressure-variable water drum cylindrical shell, driving voltage and strain output are by signal wire, wire transmits through the slip ring assembly of hollow shafting, the setting of hollow shafting and slip ring assembly is prior art, signal filtering, signal amplifies and data acquisition all completes in the outside of pressure-variable water drum, concrete adjusting and measuring process are as follows:
The pitch regulated of tested blade 101: by unclamping tested blade 101, clamping ring 3, the screw that compacting ring 4 is affixed, two semi-rings that originally tighten up the clamping ring 3 in the cone section 1 of force cell 2 are thrown off with cone section 1, thus can 360 ° rotate tested blades 101, thereby realize the pitch regulated of tested blade 101, be adjusted to after constant pitch, by described two semi-rings of clamping ring 3 to being combined in the periphery of cone section 1, and by screw by tested blade 101, clamping ring 3, compacting ring is fastenedly connected, thus, by the conical through-hole 1 of clamping ring 3 and the locking of the cone section 1 of force cell 2.Completing tested blade 101 is connected with tightening up of force cell 2;
The pitch regulated of non-tested blade 103: by unclamping the screw that two semi-rings of roll adjustment circle 8 and propeller hub 102 are fastenedly connected, two semi-rings that originally tighten up the roll adjustment circle 8 in the cone section 2 1031 of non-tested blade 103 are thrown off with cone section 2 1031, thus can 360 ° rotate non-tested blades 103, thereby realize the pitch regulated of non-tested blade 103, be adjusted to after constant pitch, by described two semi-rings of roll adjustment circle 8 to being combined in the periphery of cone section 2 1031 of non-tested blade 103, and by screw, two semi-rings of roll adjustment circle 8 and propeller hub 102 are fastenedly connected, thus, by the conical through-hole 2 801 and the locking of the cone section 2 1031 of non-tested blade 103 and being fastenedly connected of roll adjustment circle 8 and propeller hub 102 of roll adjustment circle 8, completing non-tested blade 103 is connected with tightening up of roll adjustment circle 8.
Independent static demarcating to five components: before systematic survey, force cell 2 is demarcated carrying out.Table 1, for rotating vane moment My is carried out to the experimental data that independent static demarcating obtains, repeatedly loads and measures along with the increase of moment and through six times, and the experimental data obtaining is as following table 1, and wherein, amplifier magnification ratio is 1000, and bridge is pressed as 10V:
Table 1 carries out to rotating vane moment My the experimental data that independent static demarcating obtains
According to table 1 obtained experimental data, utilize mathematical method to calculate the repeatability of experimental data described in table 1, hysteresis, the linearity, explicit coefficient, export and quiet school coefficient zero point, and and then to calculate the comprehensive quiet school of rotating vane moment My precision be 0.236%, it is less than 1%, under same verification condition, utilize identical method, can obtain respectively other four component F x, Fz, the experimental data of Mx and Mz, and calculate respectively the comprehensive quiet school precision of these four components, by the independent static demarcating of each component, the comprehensive quiet school precision that can obtain five components is all less than 1%, thus, illustrate that force cell 2 structural symmetry of the present invention are reasonable, bridge balance, stable output, there is good quiet school performance.
The interference free performance of force cell 2 to other four component F x, Fz, Mx and Mz: by increase progressively the mode of loading and decrement load in Mx direction, read corresponding strain output in Mx and My direction, obtain as following table 2 experimental datas:
Table 2 to Mx increase progressively with decrement load after obtain the experimental data in Mx and My direction
By above-mentioned experimental data, in order to converse Mx interference volume to My output under corresponding heap(ed) capacity, due to the complicacy of non-linear matrix computations, based on experimental data in table 2, the present invention can converse interference volume T by simple linear computing method, according to the Linearity Formula of following interference volume T, calculate the interference volume to My output under corresponding Mx heap(ed) capacity:
T＝(V-V
0)*B
In above formula, T is interference volume, and V represents the output in My direction, V
0represent that amplifier exports mean value zero point, B is the quiet school coefficient 3.6674N.m/V of My, it obtains by the independent quiet school to My, in the time that Mx direction loads the moment of 3.92N.m, according to the computing formula of interference volume, can calculate the interference volume T value to My under this loading moment and this interference volume and account for the number percent C of the full scale 20N.m of My direction:
T＝(0.04945V-0.4787V)*3.6674N.m/V＝0.058N.m
V
0＝(0.4789V+0.4785V)/2＝0.4787V
C＝T/20N.m＝0.058/20*100％＝0.29％
By the above-mentioned computing method to interference volume, can calculate the interference volume to My under corresponding Mx direction heap(ed) capacity and this interference volume and account for the number percent of My direction full scale, the data obtained is shown in as following table 3:
The interference volume of table 3 Mx to My and this interference volume account for the number percent of My direction full scale
From table 3 data, Mx component exists and disturbs the measurement of rotating vane moment My component, and when Mx direction loads full scale, its interference volume to rotating vane moment My direction of measurement is about 1%.Can obtain other three component F x, Fz and Mz is all less than 1% to the interference volume of rotating vane moment My direction of measurement according to same method, the interference by a small amount of to the measurement of rotating vane moment My of Fx, Fz, Mx and tetra-components of Mz is described, but the component of maximum interference is Mx, its maximum interference amount is about 1%, and the interference volume of other measurements of three components to rotating vane moment My is all less than 1%, thus, the interference volume that Fx, Fz, Mx and the measurement of tetra-components of Mz to rotating vane moment My are described is little, illustrates that the antijamming capability of whole force cell 2 is fine.
By tested blade 101 is directly connected with force cell 2, and by passing the improvement of force cell 2 structures, evidence, force measuring machine of the present invention has good quiet school performance and antijamming capability, can guarantee measuring accuracy and the reliability of tuning for Controllable Pitch Propeller blade rotating vane moment.
More than describing is explanation of the invention, is not the restriction to invention, and limited range of the present invention, referring to claim, within protection scope of the present invention, can be done any type of amendment.
Claims (5)
1. the force measuring machine in tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device, comprise tuning for Controllable Pitch Propeller (1), it is characterized in that: the list in tuning for Controllable Pitch Propeller (1) only tested blade (101) tightens up by distance adjustor in the cone section one (201) that is assemblied in force cell (2) top, described distance adjustor comprises clamping ring (3) and compacting ring (4), clamping ring (3) comprises two semi-rings, described two semi-rings are combined to form the clamping ring (3) of middle part with conical through-hole one (301), conical through-hole one (301) inner conical surface is consistent with the tapering of cone section one (201) male cone (strobilus masculinus), compacting ring (4) middle part is with the mounting hole (401) connecting, the cone section one (201) of force cell (2) is entrenched in conical through-hole one (301), the bottom of force cell (2) is fastened in the propeller hub (102) of tuning for Controllable Pitch Propeller (1) through after mounting hole (401), the rotating vane dead in line of the central axis of force cell (2) and tested blade (101), tested blade (101) is by two semi-rings of screw and clamping ring (3), compacting ring (4) is fastenedly connected, on force cell (2), posting foil gauge (203), is full-bridge connection for measuring the foil gauge (203) of tested blade (101) rotating vane moment, propeller hub (102) front end is connected with fair water cone (5), the rear end of propeller hub (102) and joint flange (6) are fastening and be tightly connected, outside screw propeller pump dynamograph main shaft and joint flange (6) are in transmission connection, propeller hub (102) rear end is connected with watertight connector (7), and the signal wire of force cell (2) is introduced into outside screw propeller pump dynamograph via watertight connector (7), joint flange (6).
2. by the force measuring machine in tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device claimed in claim 1, it is characterized in that: the solid shell of column (202) that cone section one (201) below of described force cell (2) is octagon for xsect, four arcuate structures that limit is indent of the solid shell of column (202) of octagon, and the arcuate structure interval of described indent is arranged, on other four limits of the solid shell of column (202) of octagon, is posted foil gauge (203); The below of solid shell of column (202) is base (204), and base (204) is affixed with propeller hub (102).
3. by the force measuring machine in tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device claimed in claim 2, it is characterized in that: described base (204) is provided with fairlead (205) and logical wire casing (206), fairlead (205) is positioned at the upper end of logical wire casing (206) and the two communicates, logical wire casing (206) is communicated with seal groove (207) diametrically, the other end of seal groove (207) is communicated with wire hole (208), wire hole (208) is located at base (204) above and is through hole, seal groove is perfused with water-proof silica-gel in (207).
4. by the force measuring machine in tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device claimed in claim 1, it is characterized in that: described force cell (2) is five component sensors, be used for measuring the rotating vane moment of tested blade (101), the force and moment that tested blade (101) is subject in water (flow) direction, tested blade (101) with all suffered force and moments in vertical direction of water (flow) direction and tested blade (101) reference line direction, wherein, be full-bridge connection for measure the foil gauge (203) of the power being subject in water (flow) direction, for measurement and water (flow) direction and tested blade (101) reference line direction all in vertical direction the foil gauge (203) of suffered power be connected for full-bridge, be half-bridge connection for measure the foil gauge (203) of the moment being subject in water (flow) direction, for measurement and water (flow) direction and tested blade (101) reference line direction all in vertical direction the foil gauge (203) of suffered moment be connected for half-bridge.
5. by the force measuring machine in the tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device described in the arbitrary claim of claim 1 to 4, it is characterized in that: the non-tested blade (103) in described tuning for Controllable Pitch Propeller (1) is fastened on propeller hub (102) by roll adjustment circle (8), roll adjustment circle (8) comprises two semi-rings, described two semi-rings are combined to form the roll adjustment circle (8) of middle part with conical through-hole two (801), the blade root place of non-tested blade (103) is with cone section two (1031), conical through-hole two (801) inner conical surfaces are consistent with the tapering of cone section two (1031) male cone (strobilus masculinus)s, the cone section two (1031) of non-tested blade (103) is entrenched in conical through-hole two (801), two semi-rings of roll adjustment circle (8) are fastenedly connected by screw and propeller hub (102) respectively.
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| CN201410310769.3A CN104034465B (en) | 2014-07-01 | 2014-07-01 | Force measuring machine in tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device |
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| CN201410310769.3A CN104034465B (en) | 2014-07-01 | 2014-07-01 | Force measuring machine in tuning for Controllable Pitch Propeller one piece blade rotating vane torque measuring device |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105021337A (en) * | 2015-07-30 | 2015-11-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Propeller driving rotation force measuring apparatus and force measuring method |
| CN107941404A (en) * | 2017-11-01 | 2018-04-20 | 武汉理工大学 | A kind of pump dynamograph of the propeller near-end test of small and exquisite exquisiteness |
| CN109000909A (en) * | 2018-06-22 | 2018-12-14 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | One kind being used for polar region ship model propeller ice water combined load measuring device |
| CN109932123A (en) * | 2019-03-22 | 2019-06-25 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Propeller single-blade leaf determination of six components of foree device |
| CN111547201A (en) * | 2020-05-13 | 2020-08-18 | 中国船舶工业集团公司第七0八研究所 | Ship model heeling locking device and moment measuring method |
| CN114264404A (en) * | 2021-12-28 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Zero setting method of force transducer for structural strength test |
| CN116513393A (en) * | 2023-02-09 | 2023-08-01 | 合肥倍豪海洋装备技术有限公司 | Method for determining initial zero position of keyless taper assembly of propeller |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105021337A (en) * | 2015-07-30 | 2015-11-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Propeller driving rotation force measuring apparatus and force measuring method |
| CN107941404A (en) * | 2017-11-01 | 2018-04-20 | 武汉理工大学 | A kind of pump dynamograph of the propeller near-end test of small and exquisite exquisiteness |
| CN107941404B (en) * | 2017-11-01 | 2019-10-25 | 武汉理工大学 | A kind of pump dynamograph of the propeller proximal end test of small and exquisite exquisiteness |
| CN109000909A (en) * | 2018-06-22 | 2018-12-14 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | One kind being used for polar region ship model propeller ice water combined load measuring device |
| CN109000909B (en) * | 2018-06-22 | 2020-04-28 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Be used for polar region ship propeller model ice-water mixed load measuring device |
| CN109932123A (en) * | 2019-03-22 | 2019-06-25 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Propeller single-blade leaf determination of six components of foree device |
| CN111547201A (en) * | 2020-05-13 | 2020-08-18 | 中国船舶工业集团公司第七0八研究所 | Ship model heeling locking device and moment measuring method |
| CN111547201B (en) * | 2020-05-13 | 2021-03-12 | 中国船舶工业集团公司第七0八研究所 | Ship model heeling locking device and moment measuring method |
| CN114264404A (en) * | 2021-12-28 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Zero setting method of force transducer for structural strength test |
| CN114264404B (en) * | 2021-12-28 | 2024-02-23 | 中国航空工业集团公司西安飞机设计研究所 | Zeroing method of force transducer for structural strength test |
| CN116513393A (en) * | 2023-02-09 | 2023-08-01 | 合肥倍豪海洋装备技术有限公司 | Method for determining initial zero position of keyless taper assembly of propeller |
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