Combined propeller rotating blade multi-component exciting force test system and test method

Abstract

The invention provides a combined propeller rotating blade multi-component exciting force test system and method, and the system comprises a dynamometer assembly, an aircraft assembly, a propeller assembly, and a test sensor assembly, and the dynamometer assembly is an installation foundation of the aircraft assembly, the propeller assembly, and the test sensor assembly. The dynamometer assembly transmits power to the propeller assembly; the aircraft assembly is used for controlling the course and the moving posture of the propeller; the propeller assembly is used for providing power for the propeller; the test sensor assembly is used for measuring the multi-component excitation force of the rotating blade. The transmission shaft in the dynamometer assembly is a continuous shaft and is designed to be of a non-broken shaft structure, the complete rigidity of the transmission shaft can be ensured, the transverse rigidity and inherent frequency of the transmission shaft can be improved, and the problem that transverse and radial exciting force is difficult to measure due to the fact that the transverse rigidity of a broken shaft is reduced and the transverse inherent frequency is too low is solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of ship propeller, in particular to a combined propeller rotating blade multi-component excitation force test system, and more particularly to a three-component unsteady excitation force test system for a combined propeller rotating blade or a ship propeller. BACKGROUND

[0002] The propeller system occupies a core position in the ship power system, directly affects the navigation performance of the ship, and the combined propeller including a duct, a stator and a rotating blade has become one of the main propelling ways of the vehicle due to its high efficiency and low noise. During the operation of the combined propeller, the rotating blade is subjected to unsteady excitation force caused by a non-uniform flow field, and the amplitude of the unsteady excitation force of the rotating blade is relatively small, so that accurate testing and analysis of the frequency spectrum characteristics become a key technical problem for the optimization design of the propeller system.

[0003] The existing patent document with the publication number CN106996871A discloses a full-scale ship propeller shaft vibration transmission characteristic test device on land, which mainly comprises a foundation platform, a direct current motor, a high-elasticity coupling, a thrust bearing assembly, an intermediate shaft, a propeller shaft, a bow bearing, a amidship bearing, a stern bearing, a propeller simulation block, an axial static thrust loading device, a dynamic force loading device, a torque loading device, a sealing device, an axial system centering and adjusting device, a bearing base dynamic force test element, a complete set of base for each part, and a lubrication and cooling device. The complete set of base for each part is installed on the foundation platform, and the main components of the propeller shaft system and the auxiliary components are installed on the base. The patent provides a comprehensive propeller shaft test system, which can simulate static thrust, dynamic force and torque. However, the application mainly relates to the land bench test of the propeller shaft system, and cannot test the actual excitation force of the underwater propeller.

[0004] The existing patent document with the publication number CN116105910A discloses a propeller lateral excitation force measuring device, which comprises a lateral excitation force sensor assembly, a transmission shaft system, a water-cooled motor, a slip ring, a signal processing module, a shaft coupling, an encoder, a first O-ring and a second O-ring. The lateral excitation force sensor assembly is fixedly connected with the transmission shaft system, and a first O-ring is arranged therebetween. The transmission shaft system is fixedly connected with the water-cooled motor, and a second O-ring is arranged therebetween. The transmission shaft of the transmission shaft system is connected with the driving shaft of the water-cooled motor through the shaft coupling. The water-cooled motor is fixed with the boat model through first and second bearing seats. The propeller is fixedly connected with the lateral excitation force sensor assembly. Four two-component piezoelectric sensors are adopted in the lateral excitation force sensor assembly, so that the measurement of the lateral excitation force of the propeller can be realized. The patent describes a propeller lateral excitation force measuring device, and the transmission shaft and the propeller mainly adopt the structure form of "non-continuous shaft + hollow shaft" to complete the measurement. Actually, the lateral stiffness of the shaft system itself is not high, and the lateral stiffness of this structure form is lower, so there are difficulties in the calibration and measurement of the lateral excitation force.

[0005] The existing patent document with the publication number CN117589354A discloses a direct measurement method for the longitudinal bearing force of a real ship propeller, which comprises a propeller excitation force measuring device and installation interface design, a signal data transmission system and installation method design, a propeller longitudinal bearing force direct testing system calibration, and a propeller longitudinal bearing force testing during the real ship sailing process. The patent proposes a direct testing method for the longitudinal bearing force of a real ship propeller. In this scheme, the propeller and the shaft are connected by a flange, the shaft is in a broken state, and a data cable needs to be passed through a hole in the center of the shaft. This scheme can only measure the axial excitation force.

[0006] The present application aims at the limitations of the prior art and provides a continuous transmission shaft for a combined propeller rotating blade or a ship propeller, a multi-component excitation force testing system without the need to open a shaft hole, which directly measures through a sensor, externally arranges a current collector ring and strengthens the sealing design, realizes high-precision three-direction dynamic excitation force testing of the combined propeller rotating blade or the propeller, and provides reliable technical support for the optimization design and performance improvement of the propeller. SUMMARY

[0007] In view of the defects in the prior art, the purpose of the present application is to provide a combined propeller rotating blade multi-component excitation force testing system and testing method.

[0008] According to the combined propeller rotating blade multi-component excitation force testing system provided by the present application, a power instrument assembly, a vehicle assembly, a propeller assembly and a testing sensor assembly are provided. The power instrument assembly is the installation basis of the vehicle assembly, the propeller assembly and the testing sensor assembly, and transmits power to the propeller assembly.

[0009] The aircraft assembly is used for controlling the heading and motion posture of the propeller.

[0010] The propeller assembly is used for powering the propeller.

[0011] The test sensor assembly is used for measuring the multi-component excitation force of the rotating blade.

[0012] Preferably, the dynamometer assembly comprises a shaft end housing and a transmission shaft, one end of the transmission shaft extending out of the inner cavity of the shaft end housing and extending to the outside of the shaft end housing.

[0013] Preferably, the transmission shaft is a continuous shaft.

[0014] Preferably, the propeller assembly comprises a rotating blade hub and a rotating blade, the rotating blade being mounted on the rotating blade hub, and the rotating blade hub being mounted on one end of the transmission shaft extending to the outside of the shaft end housing.

[0015] Preferably, the test sensor assembly comprises a current collector ring, an amplifier and a force ring arranged in the axial direction of the transmission shaft, the current collector ring, the amplifier and the force ring being sequentially arranged on the transmission shaft in the direction of the rotating blade hub from one end of the shaft end housing.

[0016] The force ring is used for measuring the axial, lateral and radial excitation forces of the rotating blade when rotating, and the signal data of the force ring are sequentially transmitted outward through the amplifier and the current collector ring.

[0017] Preferably, one end of the force ring abuts against the rotating blade hub, and the other end of the force ring is connected to the amplifier.

[0018] Preferably, a sealing cover is arranged outside the force ring, and the sealing cover is mounted on the transmission shaft between the rotating blade hub and the current collector ring.

[0019] One end face of the sealing cover is connected to the rotating part of the current collector ring, and the other end face of the sealing cover is connected to the rotating blade hub.

[0020] Preferably, the amplifier is mounted on the transmission shaft through a fixing table, and the fixing table is arranged in the sealing cover.

[0021] The amplifier comprises three, and the three amplifiers are circumferentially symmetrically mounted on the fixing table.

[0022] Preferably, the current collector ring is connected to the shaft end housing.

[0023] The current collector ring is sleeved with a shaft seal.

[0024] The application also provides a test method of the combined propeller rotating blade multi-component excitation force test system, which is characterized in that the test method comprises the following steps based on the combined propeller rotating blade multi-component excitation force test system according to any one of claims 1 to 9.

[0025] Step S1: installing the dynamometer and the shaft end shell;

[0026] The dynamometer is placed on the fixed bracket, and the shaft end shell is installed on the outer surface of the dynamometer;

[0027] Step S2: installing the stationary part of the propeller assembly and the test sensor assembly;

[0028] The stator support sleeve is installed on the surface of the dynamometer;

[0029] The current collector ring is fixed on the shaft end shell, and the data cable of the stationary part of the current collector ring is led out of the stator support sleeve;

[0030] The stator hub is installed on the stator support sleeve, and the stationary part of the current collector ring is connected with the stator hub;

[0031] Step S3: installing the rotating part of the propeller assembly and the test sensor assembly;

[0032] The sealing cover is connected with the rotating part of the current collector ring;

[0033] The amplifier is assembled on the transmission shaft, and the fixed table is arranged in the sealing cover;

[0034] The force ring is installed on the transmission shaft and abuts against the fixed table;

[0035] The rotating blade hub is installed on the transmission shaft, and the end surface of the rotating blade hub presses the rear end surface of the force ring;

[0036] Step S4: calibration of the multi-component excitation force test system.

[0037] The axial, transverse and radial excitation force transmission characteristics of the rotating blade hub are calibrated, and the test data of the force ring are recorded;

[0038] The transfer function value of the force ring output and the exciter input of the rotating blade is converted according to the test data, and the calibration coefficient is obtained;

[0039] The guide pipe connected with the stator blade is installed;

[0040] Step S5: water tunnel test of the test system and data analysis;

[0041] The whole test system is hoisted into the water tunnel, the inlet water velocity and the rotating blade rotating speed are adjusted to the test working condition step by step, the test data of the force measuring ring are recorded, and the three-component excitation force of the combined propeller rotating blade in the axial direction, the transverse direction and the radial direction is recorded according to the corresponding test data.

[0042] Compared with the prior art, the present application has the following beneficial effects:

[0043] 1、The present application sets the transmission shaft as a continuous shaft, a non-discontinuous shaft structure design, which can ensure the complete rigidity of the transmission shaft, improve the transverse rigidity and the natural frequency of the transmission shaft, and avoid the problems of difficult measurement of the transverse and radial excitation forces caused by the decrease of the transverse rigidity and the too low transverse natural frequency of the discontinuous shaft;

[0044] 2、The present application sets the force measuring ring directly abutting against the rotating blade hub of the combined propeller, so that the measured excitation force result is more direct and accurate, and the problem of inaccurate transverse and radial excitation forces caused by the force measuring ring spanning the bearing and not directly abutting against the rotating blade hub is avoided;

[0045] 3、The force measuring ring of the present application is connected to the transmission shaft through the locking cap pre-tightening, and the transverse and radial forces of the rotating blade are transmitted to the force measuring ring through friction, which completely conforms to the working principle of the force measuring ring, and avoids the problem of affecting the measurement accuracy caused by the bolt connection between the propeller mounting shaft and the transmission shaft in the discontinuous shaft scheme, the bolt transmission and the shunting of part of the transverse and radial dynamic forces;

[0046] 4、The present application has high sealing property and environmental adaptability, optimizes the sealing design, improves the stable operation ability of the test system in the complex underwater environment, and ensures the long-term test reliability;

[0047] 5、The present application can be widely applied to the excitation force test of the rotating blade of the combined propeller or the ship propeller, and provides support for the propeller performance evaluation, the vibration and noise reduction research, and the optimization of the propulsion system of the underwater vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0048] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0049] Figure 1 The main embodiment of the present application is the overall structure schematic diagram of the combined propeller rotating blade excitation test system;

[0050] Figure 2 The main embodiment of the present application is the structure schematic diagram of the dynamometer assembly;

[0051] Figure 3 The main embodiment of the present application is the structure schematic diagram of the vehicle assembly;

[0052] Figure 4 This mainly illustrates the structural diagram of the thruster assembly of the present invention;

[0053] Figure 5 This diagram mainly illustrates the structure of the test sensor assembly of the present invention.

[0054] As shown in the figure:

[0055] Power Instrument Component 1, Stator Hub 32, Test Sensor Component 4

[0056] Shaft end housing 11, stator blades 33, collector rings 41

[0057] Drive shaft 12, guide tube 34, shaft seal 42

[0058] Vehicle component 2 Rotary blade hub 35 Sealing cover 43

[0059] Stern section of the aircraft 21 Rotating blades 36 Amplifier 44

[0060] Aircraft rudder system 22 General's cap 37 Fixed platform 45

[0061] Thruster assembly 3, locking cap 38, force measuring ring 46

[0062] Stator support sleeve 31 Detailed Implementation

[0063] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0064] like Figure 1 As shown, a combined propeller rotating blade excitation test system according to the present invention includes a power instrument assembly, a vehicle assembly, a propeller assembly, and a test sensor assembly. The power instrument assembly serves as the mounting base for the vehicle assembly, the propeller assembly, and the test sensor assembly. The power instrument assembly transmits power to the propeller assembly. The vehicle assembly is used to control the heading and motion attitude of the propeller. The propeller assembly is used to provide power to the propeller. The test sensor assembly is used to measure the multi-component excitation force of the rotating blade.

[0065] Specifically, such as Figure 2As shown, the dynamometer assembly includes a shaft end housing 11 and a transmission shaft 12, the shaft end housing 11 can be provided in multiple sections, when installed, the multiple sections of the shaft end housing 11 are installed on the dynamometer in sections, one end of the transmission shaft 12 extends out of the inner cavity of the shaft end housing 11 and extends to the outside of the shaft end housing 11, and the end of the transmission shaft 12 extending out of the shaft end housing 11 is used to install the vehicle assembly, the propeller assembly and the test sensor assembly. Further, in order to facilitate the installation of the vehicle assembly, the propeller assembly and the test sensor assembly, a plurality of steps with different diameters are provided on the transmission shaft 12, and a stepped shaft is formed at the end of the transmission shaft 12 extending out of the shaft end housing 11. Compared with the transmission shaft composed of multiple sections in the prior art, the transmission shaft 12 of the present application is a continuous shaft, which is designed as a non-discontinuous shaft structure and penetrates through the entire propeller system, which can ensure the complete stiffness of the transmission shaft 12, improve the lateral stiffness and natural frequency of the transmission shaft 12, and avoid the problems of difficult measurement of lateral and radial excitation forces caused by the decrease of lateral stiffness and the too low lateral natural frequency of the discontinuous shaft structure in the prior art.

[0066] Specifically, as shown in the figure, Figure 3 The vehicle assembly includes a vehicle stern 21 and a vehicle rudder wing system 22, the vehicle rudder wing system 22 is installed on the vehicle stern 21, the vehicle stern 21 is a basic platform and support skeleton, the vehicle rudder wing system 22 is physically installed and fixed on the vehicle stern 21 through bearings and mechanical interfaces, and the vehicle rudder wing system 22 is used to control the sailing direction of the propeller. The spacecraft assembly of the present application is a conventional arrangement of the propeller structure, which will not be described in detail here.

[0067] Specifically, as shown in the figure, Figure 4 The propeller assembly includes a stator support sleeve 31, a stator hub 32, a stator blade 33, a guide pipe 34, a rotating blade hub 35 and a rotating blade 36. The stator support sleeve 31 transmits the load of the stator hub 32 and the stator blade 33 to the guide pipe 34, the stator support sleeve 31 is a key load-bearing structure, and the guide pipe 34 provides flow control, pressure increase, noise reduction and protection. The stator hub 32 and the stator blade 33 are stationary components of the propeller assembly, the stator hub 32 installs and supports the inner end of the stator blade 33, and the stator blade 33 is a efficiency component that recovers rotational energy to convert into additional thrust and straightens the wake. The above stator support sleeve 31, stator hub 32, stator blade 33 and guide pipe 34 are conventional arrangements of the propeller structure, which will not be described in detail here.

[0068] The rotating blade hub 35 and the rotating blade 36 are rotating parts of the propeller assembly, the rotating blade 36 is installed on the rotating blade hub 35, the rotating blade hub 35 is installed on one end of the transmission shaft 12 extending out of the shaft end housing 11, and the rotating blade hub 35 is connected with the end of the transmission shaft 12 by a key. In order to prevent the rotating blade hub 35 from falling off from one end of the transmission shaft, a locking cap 38 is installed at the rear of the rotating blade hub 35, the locking cap 38 is installed on the threaded section of the shaft end of the transmission shaft 12, and is used to press the rotating blade hub and the test sensor assembly connected thereto against the step on the transmission shaft, and a top hat 37 is installed outside the locking cap 38, which is used for the shape retention of the entire propeller system stern.

[0069] Specifically, as shown in Figure 5 The test sensor assembly includes a current collector ring 41, a shaft seal 42, a sealing cover 43, an amplifier 44, a fixed platform 45, and a force ring 46, the current collector ring 41, the amplifier 44, and the force ring 46 are sequentially arranged on the transmission shaft 12 along one end of the shaft end housing 11 towards the direction close to the rotating blade hub 35. The rotating blade hub 35 is installed on the end of the transmission shaft 12, the rotating blade hub 35 is set as the downstream end of the transmission shaft 12, one end of the shaft end housing 11 is set as the upstream end, the current collector ring 41, the amplifier 44, and the force ring 46 are sequentially installed on the transmission shaft 12 from the upstream end to the downstream end, the current collector ring 41 is located upstream of the rotating blade hub 35, the current collector ring 41 is connected with the shaft end housing 11, and its main function is the dynamic and static conversion of data transmission, the amplifier 44 and the force ring 46 are installed close to the rotating blade 36 for dynamic force test, the amplifier 44 is located downstream of the current collector ring 41 for amplifying the test data of the force ring 46 and transmitting it to the current collector ring 41, and the force ring 46 is used to measure the axial, lateral, and radial excitation forces when the rotating blade 36 rotates, and the signal data of the force ring 46 is transmitted outward in sequence through the amplifier 44 and the current collector ring 41.

[0070] More specifically, the slip ring 41 is connected with the shaft end housing 11, and the slip ring 41 is sleeved with the shaft seal 42, which is preferably a mechanical shaft seal, and is sleeved outside the slip ring 41 for waterproof sealing between the stationary part and the rotating part of the slip ring 41, and can also prevent water from penetrating into the inside of the slip ring 41 and the end of the transmission shaft 12, thereby ensuring the tightness and signal stability of the propeller system. The slip ring 41 and the shaft seal 42 are connected by a pin outside before being installed on the transmission shaft 12, so as to reduce the installation time. The amplifier 44 is installed on the transmission shaft 12 through the fixing table 45, and the fixing table 45 is arranged in the sealing cover 43. A step is arranged on the transmission shaft 12 at the fixing table 45, which is used for pre-tightening the force ring 46. The amplifier 44 can be arranged in three, and the three amplifiers correspond to the three-way force ring in the transverse direction, the axial direction and the radial direction, respectively. Preferably, the three amplifiers 44 are symmetrically arranged in the circumferential direction on the fixing table 45. The force ring 46 is installed behind the fixing table 45. The three-way excitation force data of the force ring 46 is transmitted to the three amplifiers 44 through three data lines, respectively. The end surface of the rotating blade hub 35 presses the rear end surface of the force ring 46, and the locking cap 38 is used to press the rotating blade hub 35 and the force ring 46 closely. The pre-tightening of the force ring 46 is according to the specified state of the locking cap 38 being tightened.

[0071] The sealing cover 43 for water or air tightness and rotation transmission is further arranged outside the force ring 46. The sealing cover 43 is installed on the transmission shaft between the rotating blade hub 35 and the slip ring 41. The upstream end surface of the sealing cover 43 is connected with the rotating part of the slip ring 41, and the downstream end surface of the sealing cover 43 is connected with the front end surface of the rotating blade hub 35. O-rings are arranged at both ends for preventing water or harmful gas from entering the position where the force ring 46 and the amplifier 44 are arranged, and protecting the force ring 46. An embodiment for installing the sealing cover 43 is that the sealing cover 43 is designed to have a flange structure connected with the rotating blade hub 35, and grooves are arranged on the flange structure for installing sealing O-rings. O-rings are also designed on the locking cap 38 for preventing water or gas from entering the inside of the sealing cover 43 from the shaft hole of the rotating blade hub 35 along the transmission shaft 12.

[0072] The force ring 46 is pre-tightened and connected to the transmission shaft 12 through the locking cap 38 and the general cap 37. The transverse and radial forces of the rotating blade 35 are conducted to the force ring 46 through the friction between the rotating blade hub 35 and the force ring 46, which conforms to the working principle of the force ring 46. The transmission shaft 12 of the present application adopts a continuous shaft, and the data line passes outside the transmission shaft 12, so that the transmission shaft 12 does not need to be processed by cutting and opening a center hole on the shaft, thereby avoiding the problem that in the cutting shaft scheme, the bolts are used to connect the propeller mounting shaft and the transmission shaft, and the bolts conduct and shunt part of the transverse and radial dynamic forces, thereby affecting the measurement accuracy.

[0073] During the test, the transmission shaft 12 drives the rotating blade 36 (or propeller) to rotate, and then drives the sealing cover 43, and then drives the rotating part of the ring 41, and the signal data of the force ring 46 is transmitted from the rotating part of the ring 41 to the stationary part of the ring 41, and the signal data line of the force ring 46 is transmitted through the force ring 46→amplifier 44→ring 41→external acquisition card and the like. The force ring 46 forms a dynamic conduction path with the transmission shaft 12 through the fixed table 45.

[0074] The application provides a combined propeller rotating blade excitation test system, which is used for high-precision test of dynamic excitation force of the rotating blade 35 under different working conditions.

[0075] Compared with the prior art, the application has the following obvious advantages:

[0076] (1) The transmission shaft 12 is a continuous shaft, and the non-discontinuous shaft structure design can ensure the complete stiffness of the shaft, improve the lateral stiffness and natural frequency of the transmission shaft 12, and avoid the problems that the lateral stiffness of the shaft is reduced and the lateral and radial excitation forces are difficult to measure due to the excessively low lateral natural frequency.

[0077] (2) The force ring 46 is directly in close contact with the rotating blade hub 35 of the combined propeller, and the measured excitation force result is more direct and accurate, and the problems of inaccurate lateral and radial excitation forces caused by the non-direct contact of the force ring 46 with the rotating blade hub 35 are avoided.

[0078] (3) High sealing property and environmental adaptability, optimized sealing design, improved stable operation ability of the system in a complex underwater or gaseous environment, and ensured long-term test reliability.

[0079] The application provides a high-efficiency, stable and reliable combined propeller rotating blade excitation force test system, which can test the dynamic load on the shaft in real time and accurately under different working conditions, and provides important technical support for the optimized design and performance improvement of the propelling system.

[0080] The innovation of the present application is mainly to invent a scheme of multi-component excitation force measurement without breaking the shaft and close to the excitation source. The scheme especially adopts the external wiring mode of the dynamometer to solve the problem of low transverse natural frequency in the existing breaking shaft scheme, which makes it difficult to carry out the measurement of transverse and radial excitation force.

[0081] The test method of the combined propeller rotating blade multi-component excitation force test system of the present application comprises the following steps:

[0082] Step 1: Install the dynamometer and the shaft end shell 11

[0083] Place the dynamometer on the fixed bracket, then install the segmented shaft end shell 11 on the outer surface of the dynamometer. Preferably, after completing this step, the data cable can be arranged on the bracket and the cable length for the subsequent steps is left.

[0084] Step 2: Install the propeller assembly and the stationary parts in the test sensor assembly.

[0085] Install the stator support sleeve 31 on the special step on the surface of the dynamometer, then fix the current collector ring 41 and the shaft seal 42 to the shaft end shell 11, and lead the data cable of the stationary part of the current collector ring 41 out of the stator support sleeve 31; then install the stator hub 32 to the stator support sleeve 31 by bolts, and finally connect the stationary parts of the current collector ring 41 and the shaft seal 42 to the stator hub 32 by bolts, to complete the installation of the main stationary parts. Preferably, after completing this step, the data cables on the stationary parts and rotating parts of the current collector ring 41 can be arranged to facilitate subsequent installation. The wire outlet hole on the stator support sleeve 31 is configured with a waterproof joint to prevent water or gas from entering the stator support sleeve 31 through the wire outlet hole. An O-ring is designed on the end flange of the stator support sleeve 31 to prevent water or gas from entering the interior of the stator support sleeve 31 and the interior of the stator hub 32 from the connection between the fixed sleeve and the stator end face.

[0086] Step 3: Install the rotating parts in the propeller assembly and the test sensor.

[0087] The sealing cover 43 is connected to the rotating part of the current collector ring 41 by bolts; then the fixed table 45 of the assembled three amplifiers is assembled on the transmission shaft 12 and pressed on the specially designed step of the transmission shaft 12, at this time the fixed table 45 has been placed in the designated position in the sealing cover 43; then the force ring 46 is installed on the transmission shaft 12 and abuts against the fixed table 45; finally, the rotating blade hub 35 is installed on the transmission shaft 12, and the rear end surface of the force ring 46 is pressed by the end surface of the rotating blade hub 35, and the rotating blade hub 35 and the force ring 46 abutting thereto are pressed by the locking cap 38. Preferably, before the rotating blade hub 35 and the force ring 46 are pressed, it can be simply checked whether the data of the force ring 46 is normal, and if not, whether the installation steps are wrong.

[0088] Step 4: Calibration of the multi-component excitation force test system.

[0089] After the installation of the test system is basically completed, the axial and radial excitation force transmission characteristics (including transverse and radial) of the rotating blade hub 35 are calibrated under specified working conditions by a specially designed tool. During calibration, the force ring 46 is used to excite the rotating blade hub 35 at a specified frequency and amplitude, and the test data of the force ring 46 in front of the rotating blade hub 35 are recorded. According to the test data, the transfer function values of the force ring output and the exciter input of the rotating blade 36 are converted, so as to obtain the calibration coefficient. After calibration is completed, the general cap 37 behind the rotating blade hub 35 and the guide pipe 34 connected to the stator blade 33 can be installed.

[0090] After the above step 4 is completed, the test system can be placed in the water tank for 72 hours of water tightness test to verify the water tightness of the entire test system.

[0091] Step 5: Water tunnel test of the test system and data analysis.

[0092] The entire test system is hoisted into the water tunnel, the inlet flow velocity and the rotating blade speed are gradually adjusted to the test working condition, the data of the force ring are recorded, and the three-component excitation force of the combined propeller rotating blade is analyzed according to the corresponding test data.

[0093] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0094] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be combined with each other at will without conflict.

Claims

1. A combined propeller rotating blade multi-component excitation force test system, characterized in that, The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system.

2. The combined propeller-rotating blade multi-component excitation force test system according to claim 1, characterized in that, The application relates to a combined propeller rotating blade multi-component excitation force test system.

3. The combined propeller-rotating blade multi-component excitation force test system of claim 2, wherein, The application relates to a combined propeller rotating blade multi-component excitation force test system.

4. The combined propeller-rotating blade multi-component excitation force test system of claim 2, wherein, The application relates to a combined propeller rotating blade multi-component excitation force test system.

5. The combined propeller-rotating blade multi-component excitation force test system of claim 4, wherein, The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system.

6. The combined propeller-rotating blade multi-component excitation force test system of claim 5, wherein, The application relates to a combined propeller rotating blade multi-component excitation force test system.

7. The combined propeller-rotating blade multi-component excitation force test system of claim 5, wherein, The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system.

8. The combined propeller-rotating blade multi-component excitation force test system of claim 7, wherein, The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system.

9. The combined propeller-rotating blade multi-component excitation force test system of claim 5, wherein, The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system.

10. A test method for a combined propeller-rotating blade multi-component excitation force test system, characterized in that, The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation force test system. The application relates to a combined propeller rotating blade multi-component excitation Fix the ring (41) on the shaft end housing (11) and lead the data cable of the stationary part of the ring (41) out of the stator support sleeve (31); Install the stator hub (32) on the stator support sleeve (31) and connect the stationary part of the ring (41) with the stator hub (32); Step S3: Install the propeller assembly and test the rotating part of the sensor assembly; Connect the seal cover (43) with the rotating part of the ring (41); Assemble the amplifier (44) on the transmission shaft (12) and fix the platform in the seal cover (43); Install the force ring (46) on the transmission shaft (12) and abut the fixed platform (45); Install the rotating blade hub (35) on the transmission shaft (12) and press the rear end face of the force ring (46) with the end face of the rotating blade hub (35); Step S4: Calibration of the multi-component excitation force test system. Calibrate the axial, lateral and radial excitation force transmission characteristics of the rotating blade hub (35) and record the test data of the force ring (46); According to the test data, convert the transfer function value of the rotating blade force ring (46) output and the exciter input to obtain the calibration coefficient; Install the guide pipe (34) connected with the stator blade (33); Step S5: Water tunnel test of the test system and data analysis; Hoist the entire test system into the water tunnel, gradually adjust the inflow water speed and the rotating blade (36) speed to the test working condition, record the test data of the force ring (46), and analyze the three-component excitation force of the combined propeller rotating blade (36) according to the corresponding test data.

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