CN209802668U - Gear drive fan engine low pressure rotor system model test ware - Google Patents
Gear drive fan engine low pressure rotor system model test ware Download PDFInfo
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- CN209802668U CN209802668U CN201920504391.9U CN201920504391U CN209802668U CN 209802668 U CN209802668 U CN 209802668U CN 201920504391 U CN201920504391 U CN 201920504391U CN 209802668 U CN209802668 U CN 209802668U
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- 238000009434 installation Methods 0.000 claims abstract description 4
- 230000008878 coupling Effects 0.000 claims description 35
- 238000010168 coupling process Methods 0.000 claims description 35
- 238000005859 coupling reaction Methods 0.000 claims description 35
- 210000004907 gland Anatomy 0.000 claims description 27
- 241000555745 Sciuridae Species 0.000 claims description 13
- 238000006073 displacement reaction Methods 0.000 claims description 9
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- 238000013461 design Methods 0.000 description 5
- 238000004088 simulation Methods 0.000 description 3
- 241000722921 Tulipa gesneriana Species 0.000 description 2
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- 238000011160 research Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
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Abstract
A gear transmission fan engine low pressure rotor system model tester belongs to the mechanical field, and comprises a power part, a low pressure turbine rotor, a support, a fan rotor and a connecting part. The power part provides power for the low-pressure turbine rotor part; the low-pressure turbine rotor part comprises two fulcrums A, B, wherein A is located at a boss at the front end of the low-pressure rotor shaft, and B is located at a boss at the rear end of the low-pressure rotor shaft; the fan rotor part comprises a fulcrum C, and the fulcrum C is positioned on a boss at the rear end of the fan rotor shaft; the support portion includes three sets of bearing members, one at each of the three fulcrums A, B, C. The parts are connected through a connecting part. The axes of all rotating parts in the device are collinear, and torque is input by a motor and finally flows to a rotor part of the fan through a low-pressure rotor shaft, a low-pressure turbine counterweight disc, a low-pressure compressor counterweight disc and a gear box respectively. The utility model discloses simple structure, the installation of being convenient for satisfies the engineering needs, can study star type gear flexible rotor coupled system's inherent characteristic and unbalanced response through experimental mode.
Description
Technical Field
The utility model belongs to the field of machinery's experimental apparatus relates to a gear drive fan engine low pressure rotor system model test ware.
background
The gear transmission fan engine has great development potential and market application prospect in the field of aeronautical engines by virtue of the performance advantages of high fuel economy, less pollution emission and the like. The low-pressure rotor system is one of the core components of the gear transmission fan engine and is structurally in the form of a three-fulcrum rotor system with a star-shaped gear transmission structure. Due to the complex gear structure, the rotor span is large, the working rotating speed is high, the low-pressure compressor-turbine rotor is flexible, and the system has multi-stage resonance rotating speed, so that the structure and the dynamic design of the rotor system become more difficult. Meanwhile, the unbalanced vibration of the gear coupling rotor system is always a concern of people, and the self-excited vibration of the rotor system often happens in engineering, even accidents are caused. The vibration problem of the star-gear flexible rotor coupling system has become one of the issues to be studied urgently.
because the theoretical rotor model has limitations, and the experimental research directly based on the prototype machine needs a long period and has higher cost, the rotor model tester is developed based on the structural characteristics of the low-pressure rotor system of the prototype machine and follows the similarity principle, the inherent characteristics and the unbalanced response of the star-shaped gear flexible rotor coupling system are researched by adopting a simulation and simulation combined test mode, the rotor model tester has guiding significance for deeply researching the coupling vibration rule of the low-pressure rotor system of the gear transmission fan engine, and a foundation can be laid for the design and fault analysis of the rotor system of the aeroengine in China.
SUMMERY OF THE UTILITY MODEL
Problem to prior art existence, the utility model provides a gear drive fan engine low pressure rotor system model test ware realizes through the inherent characteristic and the unbalanced response of experimental mode research this star type gear flexible rotor coupled system.
the utility model discloses a following technical scheme realizes:
A gear transmission fan engine low pressure rotor system model tester can be divided into according to the function of each part: a power section, a low pressure turbine rotor section, a support section, a fan rotor section, and a coupling section.
The power part comprises: motor 25, gear housing 20. The motor 25 is arranged on the bracket 17 of the truss structure and used for providing power for the rotor part of the low-pressure turbine, and the axis of the motor 25 is collinear with the central axis of the bracket 17. The gear case 20 is used for reducing the rotating speed of the fan counterweight plate 2 and improving the efficiency of the compressor and the turbine, and is mounted on the case support 16 through bolts, the case support 16 can move on the mounting surface of the support 17 through a sliding block, and is fixed through the bolts after reaching a specified mounting position.
The low pressure turbine rotor section includes: the low-pressure turbine balance weight disk comprises a low-pressure rotor shaft 12, a low-pressure turbine balance weight disk 13, a low-pressure compressor balance weight disk 8 and expansion sleeve pressing covers 1-2 and 1-3. The front end of the low-pressure rotor shaft 12 penetrates through a center hole of the low-pressure turbine counterweight plate 13 to be connected with a diaphragm coupling 24, the axial displacement of the low-pressure turbine counterweight plate 13 is limited through the expansion sleeve gland 1-3, and the diaphragm coupling 24 is connected with a motor 25. The rear end of the low-pressure rotor shaft 12 penetrates through a center hole of the low-pressure compressor counterweight disk 8 and then is connected with two quincuncial couplers 19-2 and 19-1 in sequence, a gear case 20 is arranged between the two quincuncial couplers 19-1 and 19-2, and the axial displacement of the low-pressure compressor counterweight disk 8 is limited through an expansion sleeve gland 1-2. The geometric parameters of the low-pressure turbine counterweight plate 13 and the low-pressure compressor counterweight plate 8 are obtained by the mechanical equivalent calculation of an actual turbine and an actual compressor. The low pressure turbine rotor portion includes two fulcrums A, B, where A is located at the forward lobe portion of low pressure rotor shaft 12 and B is located at the aft lobe portion of low pressure rotor shaft 12.
The fan rotor part comprises: expansion sleeve gland 1-1, fan counterweight disc 2 and fan rotor shaft 7. The front end of the fan rotor shaft 7 is connected with the plum coupling 19-1, the rear end of the fan rotor shaft is provided with the fan counterweight plate 2, and the axial displacement of the fan counterweight plate 2 is limited through the expansion sleeve gland 1-1. The fan rotor portion includes a fulcrum C located at the rear boss portion of the fan rotor shaft 7.
the support portion includes three sets of bearing members located at the three locations of the fulcrum A, B, C. The fulcrums A, C are all of a resilient support structure. At the fulcrum point a: the movable part at the rear part of the roller bearing seat 14 is connected to a hub of a supporting amplitude plate 15-3 through a bearing conical shell 5-2, the supporting amplitude plate 15-3 can move on the mounting surface of the bracket 17, and is fixed through bolts after reaching a specified mounting position; at the fulcrum C: the movable part at the rear part of the tapered roller bearing seat 3 is connected to a hub of a supporting amplitude plate 15-1 through a bearing conical shell 5-1, the supporting amplitude plate 15-1 can move on the mounting surface of a bracket 17, and is fixed through bolts after reaching a specified mounting position. Such support structures may alter the dynamic characteristics of the system structure to reduce vibration levels. The position of the pivot B is as follows: the rigidity of the tester is greatly influenced on the overall performance when the tester is positioned in the middle (the rear end boss part of the low-pressure rotor shaft 12), so that a rigid supporting structure is adopted, the deep groove ball bearing seat 11 is connected with a hub of a supporting web 15-2 through a supporting plate 10, the supporting web 15-2 can move on the mounting surface of a bracket 17, and the supporting web is fixed through bolts after reaching a specified mounting position. The three sets of bearing parts have the following specific structures:
the A fulcrum bearing part comprises: the device comprises a roller bearing 23, a lock nut 21-2, a roller bearing seat 14, a bearing gland 9-2, a supporting web 15-3, a bearing conical shell 5-2 and a bearing squirrel cage 6-2. The roller bearing 23 is arranged in the roller bearing seat 14, and the lock nut 21-2 is screwed on the low-pressure rotor shaft 12 through threads to limit the axial movement of the inner ring of the roller bearing 23. The small end face of the bearing gland 9-2 is contacted with the end face of the outer ring of the roller bearing 23 and is fixed on the roller bearing seat 14 by bolts so as to limit the axial movement of the outer ring of the roller bearing 23. The roller bearing seat 14 is provided with a small hole and fixed on the small end face of the bearing squirrel cage 6-2 through a bolt, and the large end face of the bearing squirrel cage 6-2 is provided with a small hole and fixed on the small end face of the bearing conical shell 5-2 through a bolt. The bearing conical shell 5-2 is arranged on a hub of the supporting web 15-3 through a bolt. This design can suppress bending deformation of the shaft and reduce vibration of the rotor. The support web 15-3 is movable on the mounting surface of the bracket 17 and is bolted after reaching a designated mounting location.
the B fulcrum bearing part comprises: the deep groove ball bearing comprises a deep groove ball bearing seat 11, a bearing gland 9-1, a support plate 10, a support amplitude plate 15-2, a locking nut 21-1 and a deep groove ball bearing 22. The locking nut 21-1 is screwed on the low-pressure rotor shaft 12 through threads to limit axial movement of an inner ring of the deep groove ball bearing 22. The bearing gland 9-1 is contacted with the outer ring of the deep groove ball bearing 22 and is arranged on the deep groove ball bearing seat 11 through a bolt to limit the axial movement of the outer ring of the deep groove ball bearing 22 on the low-pressure rotor shaft. The deep groove ball bearing seat 11 is connected with the support plate 10 through bolts, and the bolts fix the support plate 10 on a hub of the support web 15-2. The support web 15-2 is movable on the mounting surface of the bracket 17 and is bolted after reaching a designated mounting location.
the C-fulcrum bearing member includes: the device comprises a tapered roller bearing 18, a tapered roller bearing seat 3, a bearing gland 9-3, a supporting amplitude plate 15-1, a bearing conical shell 5-1, a bearing squirrel cage 6-1 and a lining 4. The tapered roller bearing 18 is installed in the tapered roller bearing seat 3, and the small end face of the bearing gland 9-3 is in contact with the end face of the outer ring of the tapered roller bearing 18 and is fixed on the tapered roller bearing seat 3 by means of bolts so as to limit the axial movement of the outer ring of the tapered roller bearing seat 3. The tapered roller bearing seat 3 is provided with a small hole and fixed on the small end surface of the bearing squirrel cage 6-1 through a bolt, and the large end surface of the bearing squirrel cage 6-1 is provided with a small hole and fixed on the small end surface of the bearing tapered shell 5-1 through a bolt. The bearing conical shell 5-1 is arranged on a hub of the supporting web 15-1 through a bolt. The support web 15-1 is movable on the mounting surface of the bracket 17 and is bolted after reaching a designated mounting location. The bush 4 is a cylinder piece, and the outer wall of the bush is attached to the inner wall of the tapered roller bearing seat 3. The bush 4 serves to isolate the pair of tapered roller bearings 18 so that the pair of tapered roller bearings 18 are "reverse-mounted".
The support portion includes a casing support 16 in addition to A, B, C three bearing members, and the gear casing 20 is mounted on the casing support 16 by bolts, and the casing support 16 is movable on a mounting surface of the bracket 17 and fixed by bolts after reaching a specified mounting position.
The connecting portion includes: a tulip coupling 19 (two, 19-1,19-2), a diaphragm coupling 24, and respective bolts. The diaphragm coupling 24 connects the output end of the motor 25 with the input end of the low-pressure rotor shaft 12, the double-cone coupling 19-2 connects the output end of the low-pressure rotor shaft 12 with the input end of the gear case 20, and the double-cone coupling 19-1 connects the output end of the gear case 20 with the input end of the fan rotor shaft 7.
The utility model discloses all revolving part axis collineations, the moment of torsion is inputted by motor 25 and is respectively via low pressure rotor shaft 12, low pressure turbine counterweight plate 13, low pressure compressor counterweight plate 8 and gear case 20, finally flows to fan counterweight plate 2.
Compare with traditional rotor tester, the beneficial effects of the utility model are that:
to ensure the similarity of the drive train support structure, a force-bearing support plate structure of a hanging point is adopted for the gear case 20, and the gear case 20 is bolted to the case support 16. The upper surface of the whole machine support 17 is a mounting base surface of each component of the tester rotor system, so that the mounting error is reasonably controlled, and the problem that the input and output shafts of the gear case 20 and the low-pressure rotor shaft 12 are not aligned is avoided to a certain extent. The utility model discloses a similar design's of model test ware thought, fulcrum (being fulcrum A) have designed elastic support structure (bearing component A, C) and true supporting structure degree of agreeing with height behind fan rotor shaft 7 fulcrum (being fulcrum C) and low-pressure rotor shaft 12 before fulcrum (being fulcrum A), also satisfy the engineering needs in simple structure is convenient for install.
Drawings
FIG. 1 is a three-dimensional block diagram of the present invention;
FIG. 2 is a front view of the present invention;
Fig. 3 is a top view of the present invention;
Fig. 4 is a side view of the present invention;
FIG. 5 is a gear case support scheme;
in the figure: 1 expansion sleeve gland (three, 1-1, 1-2, 1-3); 2, a fan counterweight plate; 3, a tapered roller bearing seat; 4, lining the sleeve; 5 bearing conical shells (two, 5-1, 5-2); 6 bearing squirrel cages (two, 6-1, 6-2); 7 a fan rotor shaft; 8, a counterweight plate of the low-pressure compressor; 9 bearing glands (three, 9-1, 9-2, 9-3); 10 a support plate; 11, a deep groove ball bearing seat; 12 a low pressure rotor shaft; 13 low pressure turbine balance weight disc; 14 stick bearing seats; 15 supporting webs (three, 15-1, 15-2, 15-3); 16 supporting the casing; 17 a support; 18 tapered roller bearings; 19 quincunx couplings (two, 19-1, 19-2); 20 gear case; 21 lock nuts (two, 21-1, 21-2); 22 deep groove ball bearings; 23 roller bearings; 24 diaphragm coupling; 25 motor.
Detailed Description
The embodiments of the present invention will be further explained with reference to the accompanying drawings.
A gear transmission fan engine low pressure rotor system model tester can be divided into according to the function of each part: a power section, a low pressure turbine rotor section, a support section, a fan rotor section, and a coupling section.
The power part comprises: motor 25, gear housing 20. The motor 25 is arranged on the bracket 17 of the truss structure and used for providing power for the rotor part of the low-pressure turbine, and the axis of the motor 25 is collinear with the central axis of the bracket 17. The gear case 20 is used for reducing the rotating speed of the fan counterweight plate 2 and improving the efficiency of the compressor and the turbine, and is mounted on the case support 16 through bolts, the case support 16 can move on the mounting surface of the support 17 through a sliding block, and is fixed through the bolts after reaching a specified mounting position.
The low pressure turbine rotor section includes: the low-pressure turbine balance weight disk comprises a low-pressure rotor shaft 12, a low-pressure turbine balance weight disk 13, a low-pressure compressor balance weight disk 8 and expansion sleeve pressing covers 1-2 and 1-3. The front end of the low-pressure rotor shaft 12 penetrates through a center hole of the low-pressure turbine counterweight plate 13 to be connected with a diaphragm coupling 24, the axial displacement of the low-pressure turbine counterweight plate 13 is limited through the expansion sleeve gland 1-3, and the diaphragm coupling 24 is connected with a motor 25. The rear end of the low-pressure rotor shaft 12 penetrates through a center hole of the low-pressure compressor counterweight disk 8 and then is connected with two quincuncial couplers 19-2 and 19-1 in sequence, a gear case 20 is arranged between the two quincuncial couplers 19-1 and 19-2, and the axial displacement of the low-pressure compressor counterweight disk 8 is limited through an expansion sleeve gland 1-2. The geometric parameters of the low-pressure turbine counterweight plate 13 and the low-pressure compressor counterweight plate 8 are obtained by the mechanical equivalent calculation of an actual turbine and an actual compressor. The low pressure turbine rotor portion includes two fulcrums A, B, where A is located at the forward lobe portion of low pressure rotor shaft 12 and B is located at the aft lobe portion of low pressure rotor shaft 12.
The fan rotor part comprises: expansion sleeve gland 1-1, fan counterweight disc 2 and fan rotor shaft 7. The front end of the fan rotor shaft 7 is connected with the plum coupling 19-1, the rear end of the fan rotor shaft is provided with the fan counterweight plate 2, and the axial displacement of the fan counterweight plate 2 is limited through the expansion sleeve gland 1-1. The fan rotor portion includes a fulcrum C located at the rear boss portion of the fan rotor shaft 7.
The support portion includes three sets of bearing members located at the three locations of the fulcrum A, B, C. The fulcrums A, C are all of a resilient support structure. At the fulcrum point a: the movable part at the rear part of the roller bearing seat 14 is connected to a hub of a supporting amplitude plate 15-3 through a bearing conical shell 5-2, the supporting amplitude plate 15-3 can move on the mounting surface of the bracket 17, and is fixed through bolts after reaching a specified mounting position; at the fulcrum C: the movable part at the rear part of the tapered roller bearing seat 3 is connected to a hub of a supporting amplitude plate 15-1 through a bearing conical shell 5-1, the supporting amplitude plate 15-1 can move on the mounting surface of a bracket 17, and is fixed through bolts after reaching a specified mounting position. Such support structures may alter the dynamic characteristics of the system structure to reduce vibration levels. The position of the pivot B is as follows: the rigidity of the tester is greatly influenced on the overall performance when the tester is positioned in the middle (the rear end boss part of the low-pressure rotor shaft 12), so that a rigid supporting structure is adopted, the deep groove ball bearing seat 11 is connected with a hub of a supporting web 15-2 through a supporting plate 10, the supporting web 15-2 can move on the mounting surface of a bracket 17, and the supporting web is fixed through bolts after reaching a specified mounting position. The support portion includes a casing support 16 in addition to A, B, C three bearing members, and the gear casing 20 is mounted on the casing support 16 by bolts, and the casing support 16 is movable on a mounting surface of the bracket 17 and fixed by bolts after reaching a specified mounting position.
The connecting portion includes: a tulip coupling 19 (two, 19-1,19-2), a diaphragm coupling 24, and respective bolts. The diaphragm coupling 24 connects the output end of the motor 25 with the input end of the low-pressure rotor shaft 12, the double-cone coupling 19-2 connects the output end of the low-pressure rotor shaft 12 with the input end of the gear case 20, and the double-cone coupling 19-1 connects the output end of the gear case 20 with the input end of the fan rotor shaft 7.
The utility model discloses all revolving part axis collineations, the moment of torsion is inputted by motor 25 and is respectively via low pressure rotor shaft 12, low pressure turbine counterweight plate 13, low pressure compressor counterweight plate 8 and gear case 20, finally flows to fan counterweight plate 2.
Before the test, the motor 25 is fixed on the support 17 by using a bolt, and the bolt hole on the support can meet the requirement of shape and position during processing, so that the axis of the motor 25 is collinear with the central axis of the support 17. Bearing member A, B, C and casing support 16 are arranged in sequence without being bolted in order to horizontally adjust the position of bearing member A, B, C and casing support 16 during installation of the coupling. Then a low-pressure rotor shaft 12, a low-pressure turbine counterweight plate 13, a low-pressure compressor counterweight plate 8, a gear case 20, a fan rotor shaft 7 and a fan counterweight plate 2 are sequentially placed. The various components are then coupled together by couplings from the output shaft of the motor 25, and the bearing member A, B, C and the support housing 14 can be moved horizontally on the carriage rails if necessary and then bolted together. Finally, the motor 25 is connected with the circuit of the ABB frequency converter, and the sensor is arranged to be tested.
And (3) static characteristic test:
Before the model tester of the low-pressure rotor system of the gear transmission fan engine is started, a hammering test is carried out, and the three-way static inherent characteristics of objects to be researched (such as a low-pressure turbine counterweight plate 13, a fan counterweight plate 2, a low-pressure compressor counterweight plate 8 and the like) are measured by an acceleration sensor.
dynamic characteristic test
turning on a power supply to test, controlling the rotating speed of the motor 25 by the ABB frequency converter, and testing the vibration response of the rotor system in the acceleration and deceleration process, particularly near the critical rotating speed; the vibration response at constant rotational speed can also be tested.
And testing the dynamic response of the low-pressure rotor system under the meshing action of the gears in the running process, comparing the dynamic response with a theoretical model, and verifying the correctness of the model.
The dynamic response of the bearing component is tested by applying single-point sinusoidal excitation and single-point random excitation on the supporting web 15 and the bearing (deep groove ball bearing 22, rolling rod bearing 23), and the damping performance of the bearing component is evaluated by comparing with the design parameters.
fault simulation:
a. Misalignment faults: misalignment can be simulated by shimming the supporting web 15 at the contact point with the bracket 17.
b. Unbalance failure: by adding unbalance weights to the fan balance weight disc 2 and the low-pressure turbine balance weight disc 13, various unbalance conditions can be simulated.
Claims (4)
1. A gear transmission fan engine low pressure rotor system model tester is characterized in that the tester can be divided into the following according to the functions of each part: a power section, a low pressure turbine rotor section, a support section, a fan rotor section, and a coupling section;
The power part comprises: a motor (25) and a gear case (20); the motor (25) is arranged on a bracket (17) of the truss structure and used for providing power for a rotor part of the low-pressure turbine, and the axis of the motor (25) is collinear with the central axis of the bracket (17); the gear case (20) is installed on a case support (16), the case support (16) can move on the installation surface of the bracket (17), and the gear case is fixed through bolts after reaching a specified installation position;
The low pressure turbine rotor section includes: the low-pressure turbine balance weight disk comprises a low-pressure rotor shaft (12), a low-pressure turbine balance weight disk (13), a low-pressure compressor balance weight disk (8), expansion sleeve gland covers (1-2) and (1-3); the front end of the low-pressure rotor shaft (12) penetrates through a center hole of the low-pressure turbine counterweight plate (13) to be connected with a diaphragm coupling (24), the axial displacement of the low-pressure turbine counterweight plate (13) is limited through an expansion sleeve gland (1-3), and the diaphragm coupling (24) is connected with a motor (25); the rear end of the low-pressure rotor shaft (12) penetrates through a center hole of the low-pressure compressor counterweight disc (8) and then is connected with two quincuncial couplers (19-2) and (19-1) in sequence, a gear case (20) is arranged between the two quincuncial couplers (19-1) and (19-2), and the axial displacement of the low-pressure compressor counterweight disc (8) is limited through a swelling sleeve gland (1-2); the low-pressure turbine rotor part comprises two supporting points A, B, wherein A is located at the front boss part of the low-pressure rotor shaft (12), and B is located at the rear boss part of the low-pressure rotor shaft (12);
The fan rotor part comprises: the expansion sleeve gland (1-1), the fan counterweight plate (2) and the fan rotor shaft (7); the front end of the fan rotor shaft (7) is connected with the plum coupling (19-1), the rear end of the fan rotor shaft is provided with the fan counterweight plate (2), and the axial displacement of the fan counterweight plate (2) is limited by the expansion sleeve gland (1-1); the fan rotor part comprises a fulcrum C, and the fulcrum C is positioned at the rear end boss part of the fan rotor shaft (7);
The supporting part comprises three sets of bearing parts which are respectively positioned at the positions of the three supporting points A, B, C; the fulcrums A, C are all elastic supporting structures, and a rigid supporting structure is adopted at the fulcrum B; at the fulcrum point a: the movable part at the rear part of the roller bearing seat (14) is connected to a hub of a supporting amplitude plate (15-3) through a bearing conical shell (5-2), the supporting amplitude plate (15-3) can move on the mounting surface of a bracket (17), and is fixed through bolts after reaching a specified mounting position; at the fulcrum C: the movable part at the rear part of the tapered roller bearing seat (3) is connected to a hub of a supporting amplitude plate (15-1) through a bearing conical shell (5-1), the supporting amplitude plate (15-1) can move on the mounting surface of a bracket (17), and is fixed through a bolt after reaching a specified mounting position; the position of the pivot B is as follows: the deep groove ball bearing seat (11) is connected with a hub of a supporting amplitude plate (15-2) through a supporting plate (10) and is positioned at the middle part of the tester and the rear end boss part of a low-pressure rotor shaft (12), the supporting amplitude plate (15-2) can move on the mounting surface of a bracket (17), and the supporting amplitude plate is fixed through a bolt after reaching a specified mounting position; the supporting part comprises a casing support (16) besides A, B, C three bearing components;
The connecting portion includes: two plum couplings (19-1) and (19-2) and a diaphragm coupling (24); the output end of the motor (25) is connected with the input end of the low-pressure rotor shaft (12) through a diaphragm coupling (24), the output end of the low-pressure rotor shaft (12) is connected with the input end of the gear case (20) through a plum coupling (19-2), and the output end of the gear case (20) is connected with the input end of the fan rotor shaft (7) through the plum coupling (19-1);
The axes of all rotating parts in the device are collinear, and torque is input by a motor (25) and finally flows to a fan counterweight disc (2) through a low-pressure rotor shaft (12), a low-pressure turbine counterweight disc (13), a low-pressure compressor counterweight disc (8) and a gear case (20).
2. A geared fan engine low pressure spool system model tester as claimed in claim 1 wherein said support portion center a pivot bearing assembly comprises: the device comprises a roller bearing (23), a locking nut (21-2), a roller bearing seat (14), a bearing gland (9-2), a supporting web (15-3), a bearing conical shell (5-2) and a bearing squirrel cage (6-2); the roller bearing (23) is arranged in the roller bearing seat (14), and the locking nut (21-2) is screwed on the low-pressure rotor shaft (12); the small end face of the bearing gland (9-2) is in contact with the end face of the outer ring of the roller bearing (23) and is fixed on the roller bearing seat (14); the roller bearing seat (14) is fixed on the small end face of the bearing squirrel cage (6-2) through bolts, and the large end face of the bearing squirrel cage (6-2) is fixed on the small end face of the bearing conical shell (5-2) through bolts; the bearing conical shell (5-2) is arranged on the hub of the supporting amplitude plate (15-3).
3. a geared fan engine low pressure spool system model tester as claimed in claim 1 wherein said B fulcrum bearing assembly in the bearing section comprises: the deep groove ball bearing comprises a deep groove ball bearing seat (11), a bearing gland (9-1), a support plate (10), a support amplitude plate (15-2), a locking nut (21-1) and a deep groove ball bearing (22); the locking nut (21-1) is screwed on the low-pressure rotor shaft (12) and used for limiting the axial movement of the inner ring of the deep groove ball bearing (22); the bearing gland (9-1) is in contact with the outer ring of the deep groove ball bearing (22), is arranged on the deep groove ball bearing seat (11) and is used for limiting the axial movement of the outer ring of the deep groove ball bearing (22) on the low-pressure rotor shaft; the deep groove ball bearing seat (11) is connected with a bearing plate (10), and the bearing plate (10) is fixed on a hub of a supporting amplitude plate (15-2).
4. A geared fan engine low pressure spool system model tester as claimed in claim 1 wherein said support portion C-pivot bearing assembly comprises: the device comprises a tapered roller bearing (18), a tapered roller bearing seat (3), a bearing gland (9-3), a supporting web plate (15-1), a bearing conical shell (5-1) and a bearing squirrel cage (6-1); the tapered roller bearing (18) is arranged in the tapered roller bearing seat (3), and the small end surface of the bearing gland (9-3) is in contact with the end surface of the outer ring of the tapered roller bearing (18) and is fixed on the tapered roller bearing seat (3) so as to limit the axial movement of the outer ring of the tapered roller bearing seat (3); the tapered roller bearing seat (3) is fixed on the small end face of the bearing squirrel cage (6-1) through bolts, and the large end face of the bearing squirrel cage (6-1) is fixed on the small end face of the bearing conical shell (5-1) through bolts; the bearing conical shell (5-1) is arranged on the hub of the supporting amplitude plate (15-1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920504391.9U CN209802668U (en) | 2019-04-15 | 2019-04-15 | Gear drive fan engine low pressure rotor system model test ware |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920504391.9U CN209802668U (en) | 2019-04-15 | 2019-04-15 | Gear drive fan engine low pressure rotor system model test ware |
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| Publication Number | Publication Date |
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| CN209802668U true CN209802668U (en) | 2019-12-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920504391.9U Withdrawn - After Issue CN209802668U (en) | 2019-04-15 | 2019-04-15 | Gear drive fan engine low pressure rotor system model test ware |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110006659A (en) * | 2019-04-15 | 2019-07-12 | 大连理工大学 | A kind of gear drive Duct-Burning Turbofan low pressure rotor system model exerciser |
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2019
- 2019-04-15 CN CN201920504391.9U patent/CN209802668U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110006659A (en) * | 2019-04-15 | 2019-07-12 | 大连理工大学 | A kind of gear drive Duct-Burning Turbofan low pressure rotor system model exerciser |
| CN110006659B (en) * | 2019-04-15 | 2023-12-29 | 大连理工大学 | Gear drive fan engine low pressure rotor system model test ware |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20191217 Effective date of abandoning: 20231229 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20191217 Effective date of abandoning: 20231229 |