CN116833698A - Assembling method and structure of engine rotor for dynamic stress test - Google Patents
Assembling method and structure of engine rotor for dynamic stress test Download PDFInfo
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- CN116833698A CN116833698A CN202310796542.3A CN202310796542A CN116833698A CN 116833698 A CN116833698 A CN 116833698A CN 202310796542 A CN202310796542 A CN 202310796542A CN 116833698 A CN116833698 A CN 116833698A
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- 238000012360 testing method Methods 0.000 title claims abstract description 67
- 238000000034 method Methods 0.000 title claims abstract description 12
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 claims description 15
- 238000009662 stress testing Methods 0.000 claims description 8
- 238000006243 chemical reaction Methods 0.000 claims description 4
- 238000005452 bending Methods 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 10
- 230000005540 biological transmission Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an assembly method and an assembly structure of an engine rotor for dynamic stress test, which are based on the meshing connection of a compressor rotor and a turbine rotor, adopt a connecting anti-loosening device comprising a spring, a connecting sleeve tooth, an adjusting ring and a connecting screw to carry out connection assembly, and use a connecting screw wrench to carry out connection installation on the connecting anti-loosening device arranged in a cavity, so that the assembly of the engine rotor can be safely and reliably completed under the condition that the dynamic balance performance of the engine rotor is not changed, and the technical problem that the dynamic balance performance of the engine rotor is easy to change in the dynamic stress test assembly is solved.
Description
Technical Field
The invention relates to the field of turbine engine rotor assembly, in particular to an assembly method and an assembly structure of an engine rotor for dynamic stress test.
Background
The compressor blades are important parts of an aeroengine and are also parts prone to failure. In order to ensure the working safety of the engine, dynamic stress test analysis tests are usually carried out on the blade at the design stage of the engine so as to evaluate and determine the allowable stress level and durability of the blade under all working states. Because the combustion chamber is arranged between the compressor and the turbine, the turbine shaft is generally designed into a hollow long shaft, when the compressor blade adopts a back lead mode to carry out dynamic stress test analysis test, the problems of long signal transmission distance and complex structure exist, the lead and related parts need to be blindly assembled in a deep hole of the turbine shaft, and the dynamic balance performance of an engine rotor can be influenced.
In general, the compressor rotor and the turbine rotor of a single-rotor engine are combined together in a spline connection mode to realize torque transmission. For example, CN201210196589.8 discloses a power transmission mechanism of a compressor and a turbine, which is driven by a compressor impeller, a turbine back tooth driving mechanism, a compressor impeller with a straight trapezoid back tooth and a straight trapezoid end tooth, wherein the compressor impeller is meshed with each other, and a locking device of a conical nut at the end of the turbine shaft is formed by axially locking and meshing a gear ring in a matched manner with a shell. The assembly is a final link for guaranteeing the dynamic balance characteristic of the engine, the assembly of the engine at the present stage mostly depends on the experience of workers, and the dynamic balance performance of the engine rotor is easily influenced in the assembly process, so that the assembly of the engine rotor is safely and reliably realized under the condition that the dynamic balance performance of the engine rotor is not changed, and the assembly is a great difficulty faced by the current back lead mode.
Disclosure of Invention
The invention aims to solve the technical problem that the connection between an elastic shaft of an existing engine and a front journal of a compressor rotor is difficult to ensure accurate stability due to the large length-diameter ratio of the elastic shaft, and provides a turbine engine rotor assembly method for dynamic stress test.
The invention solves the technical problem of providing a turbine engine rotor assembly structure for dynamic stress test.
The aim of the invention is realized by the following technical scheme:
an assembling method of an engine rotor for dynamic stress test comprises the following steps:
s1, assembling a compressor rotor assembly and balancing;
the front lead tube assembly and the test lead in the test lead assembly are arranged on a rotor of the air compressor, and then dynamic balance is carried out;
s2, assembling a turbine rotor assembly and balancing;
mounting a rear lead tube assembly in the test lead assembly on the turbine rotor, and then performing dynamic balance;
s3, assembling an engine rotor;
s31, mounting a compressor rotor on an engine casing, mounting a turbine shaft on a rear shaft neck of the compressor rotor, leading out a test lead from an inner cavity of the turbine shaft, sleeving a spring, a connecting sleeve tooth, an adjusting ring and a connecting screw which are connected with a locking device on the test lead in sequence, and pushing the turbine shaft and the inner cavity of the rear shaft neck from the rear end of the turbine shaft;
s32, sleeving a jacking rod of a connecting screw wrench on the test lead, pushing the jacking rod into an inner cavity of the turbine shaft until the jacking rod contacts with the end surface of the connecting screw teeth, screwing an external thread at the end part of the screw sleeve into an internal thread of the connecting screw, meshing the tooth sleeve with the end tooth on the connecting screw, tightly pressing the sleeve wrench on the connecting screw, sleeving the pressing sleeve on the jacking rod, enabling the jacking rod to press the connecting screw teeth and compress the spring, forcing the connecting screw teeth to keep a certain distance away from the connecting screw, and screwing the connecting screw wrench to tighten the connecting screw, so that the turbine shaft is connected with a rear shaft neck of a rotor of the air compressor;
s33, after the pressing sleeve is disassembled, the connecting sleeve teeth are retracted into the connecting screw under the elastic reaction of the spring, small external splines of the connecting sleeve teeth are meshed with internal splines of the connecting screw, large external splines are meshed with internal splines of the rear axle journal, and the connecting screw is locked on the rear axle journal;
s34, after the connecting screw wrench is disassembled, the rear lead pipe assembly is sleeved on the test lead wire and is installed in the inner cavity of the turbine shaft, and then the turbine disk and the turbine blades are installed on the turbine shaft, so that the assembly of the engine rotor is completed.
Further, the specific steps of assembling the compressor rotor and balancing in S1 include:
s11, sequentially assembling all stages of compressor wheel discs, and simultaneously enabling a test lead to penetrate through all stages of compressor wheel discs and be fixed on the inner wall of each stage of compressor wheel discs;
s12, mounting the front lead tube assembly in a rear journal, and then assembling the front lead tube assembly and the rear journal together on the rear end face of the compressor wheel disc assembly, wherein a test lead penetrates through the center of the front lead tube assembly;
s13, mounting the compressor blade on a compressor wheel disc combination, and connecting a test lead with a strain gauge on the compressor blade;
s14, bending the flexible test lead wire extending out of the rear axle journal into a plurality of strands, and then installing the strands into a wire sleeve, wherein the wire sleeve is fastened at the rear end of the rear axle journal through external threads;
s15, placing the components on a dynamic balancing machine, completing dynamic balancing of a rotor of the compressor, and then removing the wire sleeve.
Further, the connecting screw spanner comprises a push rod, a pressing sleeve, a screw rod, a screw cap, a socket spanner and a toothed sleeve, wherein the push rod is a hollow round pipe, the screw rod is sleeved on the outer wall of the push rod, one end of the screw rod is provided with the detachable pressing sleeve, the other end of the screw rod is provided with an external thread capable of being screwed into the internal thread of the connecting screw, the outer wall of the screw rod is provided with the toothed sleeve, the end face of the toothed sleeve is provided with a tooth surface meshed with the end tooth of the connecting screw, and the toothed sleeve is provided with the socket spanner and a circular ring used for centering the connecting screw spanner in the inner cavity of the turbine shaft.
The utility model provides an assembly structure of engine rotor that dynamic stress test used, includes compressor rotor subassembly, turbine rotor subassembly, connects locking device and test lead wire subassembly, connect locking device and connect the back axle journal of compressor rotor subassembly and the turbine shaft of turbine rotor subassembly, the inner chamber of compressor rotor subassembly and turbine rotor subassembly is equipped with test lead wire subassembly.
Further, an inner spline and an inner thread are arranged in a cavity of a rear shaft neck of the compressor rotor, and an outer spline is arranged on the outer wall.
Further, one end of the turbine shaft is provided with an internal spline matched with an external spline on the outer wall of the rear journal of the compressor rotor.
Further, the connecting anti-loose device comprises a spring, connecting sleeve teeth, an adjusting ring and connecting screws, wherein the connecting sleeve teeth are connected with the rear shaft neck of the compressor rotor, one side of each connecting sleeve tooth is provided with a compression spring, the other side of each connecting sleeve tooth is connected with one side of each connecting screw, the other side of each connecting screw is pressed with the turbine shaft on the end face of the rear shaft neck, and the adjusting ring is arranged at the pressed part of each connecting screw and the rear shaft neck.
Further, the pipe diameters of the two ends of the connecting sleeve teeth are different, one end with a large pipe diameter is provided with a large external spline to be meshed with the internal spline of the rear axle journal, and one end with a small pipe diameter is provided with a small external spline to be meshed with the internal spline of the connecting screw.
Further, the outer wall of the connecting screw is provided with an external thread meshed with the internal thread of the rear axle journal, one end in the cavity of the connecting screw is provided with an internal spline, the cavity is provided with an internal thread, the other end of the connecting screw is provided with an external flanging, and the end face of the external flanging is provided with end teeth.
Further, the test lead wire assembly comprises a front lead wire tube assembly, a rear lead wire tube assembly and a test lead wire, wherein the front lead wire tube assembly and the rear lead wire tube assembly are connected at the end parts, and the test lead wire is arranged in the cavities of the front lead wire tube assembly and the rear lead wire tube assembly.
Compared with the prior art, the beneficial effects are that:
in the assembly of the engine rotor, a connecting screw wrench is used for extending into the inner cavity of the turbine shaft, a top rod is contacted with the end face of a connecting screw sleeve, the external thread at the end part of the screw sleeve is screwed into the internal thread of the connecting screw, the tooth sleeve is meshed with the end tooth on the connecting screw, the socket wrench is tightly pressed on the connecting screw, the top rod presses the connecting screw tooth and compresses a spring, the connecting screw tooth is forced to keep a certain distance away from the connecting screw, and the connecting screw wrench is pulled to screw the connecting screw, so that the turbine shaft and the rear journal of the compressor rotor are connected together. After the pressing sleeve is disassembled, the connecting sleeve teeth are retracted into the connecting screw under the elastic reaction of the spring, the small external spline of the connecting sleeve teeth is meshed with the internal spline of the connecting screw, the large external spline is meshed with the internal spline of the rear shaft neck, and the connecting screw is locked on the rear shaft neck.
Drawings
FIG. 1 is a schematic diagram of an engine rotor assembly for dynamic stress testing;
FIG. 2 is a turbine shaft block diagram;
FIG. 3 is a rear journal structure;
FIG. 4 is a block diagram of the connection locking device;
FIG. 5 is a diagram of a tooth structure of a connecting sleeve;
FIG. 6 is a block diagram of a connecting screw;
FIG. 7 is a diagram of a test lead assembly;
FIG. 8 is a diagram of a connecting screw wrench;
FIG. 9 is a diagram of a connecting screw wrench;
FIG. 10 is a diagram of a compressor rotor dynamic balancing assembly;
FIG. 11 is a diagram of a turbine rotor dynamic balancing assembly.
Wherein, 1 rear journal; 101 rear journal external splines; 102 rear journal internal spline; 103 rear journal internal threads; 2, a turbine shaft; 201 turbine shaft internal splines; 3, a spring; 4 connecting sleeve teeth; 401 large external splines; 402 small external splines; 5, adjusting the ring; 6, connecting a screw; 601 connecting the internal spline of the screw; 602 connecting screw external threads; 603 connecting screw internal threads; 604 end teeth; 7, testing the lead assembly; 701 a front-mounted lead-in tube assembly; 702 a post-lead tube assembly; 703 testing the leads; 8, a push rod; 9 screw rods, 901 screw rod external threads; 10 tooth sleeves; 11 socket wrenches; 12, pressing the sleeve; 13 circular rings; 14 nuts.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that, if directional indications (such as up, down, left, right, front, and rear) are involved in the embodiment of the present invention, the directional indications are merely used to explain the relative positional relationship, movement conditions, etc. between the components in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indications are correspondingly changed. If there is a description of "first", "second", etc. in an embodiment of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "provided," "connected," and the like are to be construed broadly, and may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Example 1
As shown in fig. 1, the present embodiment provides a structure of an engine rotor, which comprises a compressor rotor assembly, a turbine rotor assembly, a connection anti-loosening device and a test lead 703 assembly 7, wherein the connection anti-loosening device is connected with a rear journal 1 of the compressor rotor assembly and a turbine shaft 2 of the turbine rotor assembly, and the test lead 703 assembly 7 is arranged in the cavities of the rear journal 1 and the turbine shaft 2.
As shown in fig. 2, the cavity of the rear journal 1 of the compressor rotor is provided with a rear journal internal spline 102 and a rear journal internal thread 103, and the outer wall is provided with a rear journal external spline 101.
As shown in fig. 3, one end of the turbine shaft 2 is provided with a turbine shaft internal spline 201 which mates with the rear journal external spline 101 of the compressor rotor.
As shown in fig. 4, the connection anti-loosening device comprises a spring 3, a connecting sleeve tooth 4, an adjusting ring 5 and a connecting screw 6, wherein the connecting sleeve tooth 4 is connected with a rear shaft neck 1 of the compressor rotor, one side of the connecting sleeve tooth 4 is provided with a compression spring 3, the other side of the connecting sleeve tooth 4 is connected with one side of the connecting screw 6, the other side of the connecting screw 6 is pressed with a turbine shaft 2 on the end face of the rear shaft neck 1, and the pressing part of the connecting screw 6 and the rear shaft neck 1 is provided with the adjusting ring 5.
As shown in fig. 5, the two ends of the connecting sleeve teeth 4 have different pipe diameters, one end with a large external spline 401 is meshed with the rear journal internal spline 102, and the other end with a small external spline 402 is meshed with the connecting screw internal spline 601.
As shown in fig. 6, the outer wall of the connecting screw 6 is provided with a connecting screw external thread 602 meshed with the rear axle neck internal thread 103, one end of the connecting screw 6 cavity is provided with a connecting screw internal spline 601, the cavity is provided with a connecting screw internal thread 603, the other end of the connecting screw 6 is provided with an external flanging, and the end face of the external flanging is provided with an end tooth 604.
As shown in fig. 7, the test lead 703 assembly 7 includes a front lead tube assembly 701, a rear lead tube assembly 702, and a test lead 703, the front lead tube assembly 701 and the rear lead tube assembly 702 are connected at their ends, and the test lead 703 is disposed in the cavity of the front lead tube assembly 701 and the rear lead tube assembly 702.
Example 2
This embodiment provides an installation tool for a connecting screw wrench according to embodiment 1, which includes a top rod 8, a press sleeve 12, a screw 9, a nut 14, a socket wrench 11, and a socket 10, as shown in fig. 8 to 9.
The ejector rod 8 is a hollow round tube, and the middle part of the ejector rod can be used for penetrating the test lead 703 assembly 7.
The pressing sleeve 12 comprises a sleeve and a cylindrical pin, the sleeve is a hollow multi-section cylinder, the inner cavity of the sleeve is four sections of sequentially-enlarged cylindrical surfaces, the diameter of the first section of cylindrical surface is the same as that of the inner hole of the ejector rod 8 and is used for threading a test wire, the second section of cylindrical surface is in clearance fit with the outer cylindrical surface of the ejector rod 8, and the third section of cylindrical surface and the fourth section of cylindrical surface are in clearance fit with the screw rod 9. The external surface of the sleeve is two sections of cylindrical surfaces, cylindrical pins are arranged on the cylindrical surfaces, and the cylindrical pins are flush with the external cylindrical surfaces of the sleeve and are used for hooking the screw 9.
The screw rod 9 is sleeved on the outer wall of the ejector rod 8, and a gap exists between the screw rod and the ejector rod, so that the assembly and the disassembly are convenient. One end of the screw rod 9 is uniformly provided with L-shaped holes along the circumferential direction for installing the cylindrical pin on the pressing sleeve 12, and the other end is provided with a screw rod external thread 901 which can be screwed into the connecting screw internal thread 603.
The tooth sleeve 10 is arranged on the outer wall of the screw rod 9, and one end face of the tooth sleeve 10 is provided with a tooth surface meshed with the end tooth 604 of the connecting screw 6.
The socket wrench 11 is provided on the socket 10, and is fixed and restrained from axial displacement by the nut 14.
The inner surface of the circular ring 13 is attached to the outer cylindrical surface of the tooth sleeve 10, the outer surface of the circular ring is attached to the inner cavity of the rear end of the turbine shaft 2, the circular ring 13 is used as a supporting block to be installed at the air hole of the rear end of the turbine shaft 2, and the connecting screw wrench is supported and placed in the inner cavity of the turbine shaft 2 to play a centering role.
Example 3
The embodiment provides an assembling method of an engine rotor for dynamic stress test according to the engine rotor assembling structure of embodiment 1 and the connecting screw wrench tool of embodiment 2, as shown in fig. 10-11, comprising the steps of:
s1, assembling a compressor rotor and balancing;
s11, sequentially assembling all stages of compressor wheel discs, and simultaneously enabling a test lead 703 to penetrate through each stage of compressor wheel discs and be fixed on the inner wall of each stage of compressor wheel discs;
s12, installing the front lead tube assembly 701 in the rear journal 1, and then assembling the front lead tube assembly 701 and the rear journal together on the rear end face of the compressor wheel disc assembly, wherein a test lead 703 passes through the center of the front lead tube assembly 701;
s13, mounting the compressor blade on a compressor wheel disc combination, and connecting a test lead 703 with a strain gauge on the compressor blade;
s14, bending the flexible test lead 703 extending out of the rear journal 1 into a plurality of strands, and then installing the strands into a wire sleeve, wherein the wire sleeve is screwed and fixed at the rear end of the rear journal 1 through external threads;
s15, placing the components on a dynamic balancing machine, completing dynamic balancing of a rotor of the compressor, and then removing the wire sleeve.
S2, assembling the turbine rotor and balancing;
s21. the post-lead tube assembly 702 is installed in the turbine shaft 2 and then assembled with the turbine disk and turbine blades.
S22, placing the assembly on a dynamic balancing machine, completing dynamic balancing of the turbine rotor, and then respectively detaching the turbine shaft 2 and the rear lead tube assembly 702. The method comprises the steps of carrying out a first treatment on the surface of the
S3, assembling an engine rotor;
s31, mounting a compressor rotor on an engine casing, mounting a turbine shaft 2 on a rear journal 1 of the compressor rotor, leading a test lead 703 out of an inner cavity of the turbine shaft 2, sleeving a spring 3, a connecting sleeve tooth 4, an adjusting ring 5 and a connecting screw 6 which are connected with a locking device on the test lead 703 in sequence, and pushing the turbine shaft 2 and the inner cavity of the rear journal 1 from the rear end of the turbine shaft 2;
s32, sleeving a push rod 8 of a connecting screw spanner on a test lead 703, pushing the push rod 8 into an inner cavity of a turbine shaft 2 until the push rod 8 contacts the end face of a connecting screw tooth 4, screwing a screw external thread 901 at the end part of a screw 9 into a connecting screw internal thread 603, meshing a tooth sleeve 10 with an end tooth 604 on a connecting screw 6, tightly pressing a socket spanner 11 on the connecting screw 6, sleeving a pressing sleeve 12 on the push rod 8, enabling the push rod 8 to press the connecting screw tooth 4 and compress a spring 3, forcing the connecting screw tooth 4 to keep a certain distance away from the connecting screw 6, and connecting the turbine shaft 2 with a rear journal 1 of a compressor rotor by pulling the connecting screw spanner to screw the connecting screw 6;
s33, after the pressing sleeve 12 is detached, under the elastic reaction of the spring 3, the connecting sleeve teeth 4 are retracted into the connecting screw 6, the small external spline 402 of the connecting sleeve teeth 4 is meshed with the connecting screw internal spline 601, the large external spline 401 is meshed with the rear journal internal spline 102, and the connecting screw 6 is locked on the rear journal 1;
s34, after the connecting screw wrench is detached, the post lead tube assembly 702 is sleeved on the test lead 703 and is installed in the inner cavity of the turbine shaft 2, and then the turbine disc and the turbine blades are installed on the turbine shaft 2, so that the assembly of the engine rotor is completed.
It is to be understood that the above examples of the present invention are provided by way of illustration only and not by way of limitation of the embodiments of the present invention. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. Any modification, equivalent replacement, improvement, etc. which come within the spirit and principles of the invention are desired to be protected by the following claims.
Claims (10)
1. An assembling method of an engine rotor for dynamic stress test is characterized by comprising the following steps:
s1, assembling a compressor rotor assembly and balancing;
the front lead tube assembly and the test lead in the test lead assembly are arranged on a rotor of the air compressor, and then dynamic balance is carried out;
s2, assembling a turbine rotor assembly and balancing;
mounting a rear lead tube assembly in the test lead assembly on the turbine rotor, and then performing dynamic balance;
s3, assembling an engine rotor;
s31, mounting a compressor rotor on an engine casing, mounting a turbine shaft on a rear shaft neck of the compressor rotor, leading out a test lead from an inner cavity of the turbine shaft, sleeving a spring, a connecting sleeve tooth, an adjusting ring and a connecting screw which are connected with a locking device on the test lead in sequence, and pushing the turbine shaft and the inner cavity of the rear shaft neck from the rear end of the turbine shaft;
s32, sleeving a jacking rod of a connecting screw wrench on the test lead, pushing the jacking rod into an inner cavity of the turbine shaft until the jacking rod contacts with the end surface of the connecting screw teeth, screwing an external thread at the end part of the screw sleeve into an internal thread of the connecting screw, meshing the tooth sleeve with the end tooth on the connecting screw, tightly pressing the sleeve wrench on the connecting screw, sleeving the pressing sleeve on the jacking rod, enabling the jacking rod to press the connecting screw teeth and compress the spring, forcing the connecting screw teeth to keep a certain distance away from the connecting screw, and screwing the connecting screw wrench to tighten the connecting screw, so that the turbine shaft is connected with a rear shaft neck of a rotor of the air compressor;
s33, after the pressing sleeve is disassembled, the connecting sleeve teeth are retracted into the connecting screw under the elastic reaction of the spring, small external splines of the connecting sleeve teeth are meshed with internal splines of the connecting screw, large external splines are meshed with internal splines of the rear axle journal, and the connecting screw is locked on the rear axle journal;
s34, after the connecting screw wrench is disassembled, the rear lead pipe assembly is sleeved on the test lead wire and is installed in the inner cavity of the turbine shaft, and then the turbine disk and the turbine blades are installed on the turbine shaft, so that the assembly of the engine rotor is completed.
2. The method of assembling an engine rotor for dynamic stress testing according to claim 1, wherein the step of assembling the compressor rotor and balancing in S1 comprises:
s11, sequentially assembling all stages of compressor wheel discs, and simultaneously enabling a test lead to penetrate through all stages of compressor wheel discs and be fixed on the inner wall of each stage of compressor wheel discs;
s12, mounting the front lead tube assembly in a rear journal, and then assembling the front lead tube assembly and the rear journal together on the rear end face of the compressor wheel disc assembly, wherein a test lead penetrates through the center of the front lead tube assembly;
s13, mounting the compressor blade on a compressor wheel disc combination, and connecting a test lead with a strain gauge on the compressor blade;
s14, bending the flexible test lead wire extending out of the rear axle journal into a plurality of strands, and then installing the strands into a wire sleeve, wherein the wire sleeve is fastened at the rear end of the rear axle journal through external threads;
s15, placing the components on a dynamic balancing machine, completing dynamic balancing of a rotor of the compressor, and then removing the wire sleeve.
3. The method for assembling the engine rotor for dynamic stress testing according to claim 1, wherein the connecting screw wrench comprises a push rod, a pressing sleeve, a screw rod, a nut, a socket wrench and a tooth sleeve, the push rod is a hollow round tube, the screw rod is sleeved on the outer wall of the push rod, one end of the screw rod is provided with the detachable pressing sleeve, the other end of the screw rod is provided with an external thread capable of being screwed into the internal thread of the connecting screw, the outer wall of the screw rod is provided with the tooth sleeve, the end face of the tooth sleeve is provided with a tooth face meshed with the end tooth of the connecting screw, and the tooth sleeve is provided with the socket wrench and a circular ring for centering the connecting screw wrench in the inner cavity of the turbine shaft.
4. The assembly structure of the engine rotor for dynamic stress test is characterized by comprising a compressor rotor assembly, a turbine rotor assembly, a connecting anti-loosening device and a test lead assembly, wherein the connecting anti-loosening device is connected with a rear shaft neck of the compressor rotor assembly and a turbine shaft of the turbine rotor assembly, and the inner cavities of the compressor rotor assembly and the turbine rotor assembly are provided with the test lead assembly.
5. The assembly structure of an engine rotor for dynamic stress testing according to claim 4, wherein the rear journal of the compressor rotor is provided with internal splines and internal threads in a cavity, and the outer wall is provided with external splines.
6. The assembly structure of an engine rotor for dynamic stress testing according to claim 4, wherein one end of the turbine shaft is provided with an internal spline which is matched with an external spline on the outer wall of the rear journal of the compressor rotor.
7. The assembly structure of an engine rotor for dynamic stress testing according to claim 4, wherein the connecting anti-loose device comprises a spring, a connecting sleeve tooth, an adjusting ring and a connecting screw, the connecting sleeve tooth is connected with a rear journal of the compressor rotor, one side of the connecting sleeve tooth is provided with a compression spring, the other side of the connecting sleeve tooth is connected with one side of the connecting screw, the other side of the connecting screw is pressed with a turbine shaft on the end face of the rear journal, and the pressing part of the connecting screw and the rear journal is provided with the adjusting ring.
8. The assembly structure of the engine rotor for dynamic stress test according to claim 4, wherein the pipe diameters of the two ends of the connecting sleeve teeth are different, a large external spline is arranged at one end with a large pipe diameter and is meshed with the internal spline of the rear journal, and a small external spline is arranged at one end with a small pipe diameter and is meshed with the internal spline of the connecting screw.
9. The assembly structure of an engine rotor for dynamic stress testing according to claim 4, wherein the outer wall of the connecting screw is provided with an external thread meshed with the internal thread of the rear axle journal, one end in the cavity of the connecting screw is provided with an internal spline, the cavity is provided with an internal thread, the other end of the connecting screw is provided with an external flanging, and the end face of the external flanging is provided with end teeth.
10. The assembly structure of an engine rotor for dynamic stress testing according to claim 4, wherein the test lead assembly comprises a front lead tube assembly, a rear lead tube assembly and a test lead, the front lead tube assembly and the rear lead tube assembly being end-connected, the test lead being disposed in a cavity of the front lead tube assembly and the rear lead tube assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310796542.3A CN116833698A (en) | 2023-06-30 | 2023-06-30 | Assembling method and structure of engine rotor for dynamic stress test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310796542.3A CN116833698A (en) | 2023-06-30 | 2023-06-30 | Assembling method and structure of engine rotor for dynamic stress test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116833698A true CN116833698A (en) | 2023-10-03 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310796542.3A Pending CN116833698A (en) | 2023-06-30 | 2023-06-30 | Assembling method and structure of engine rotor for dynamic stress test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116833698A (en) |
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2023
- 2023-06-30 CN CN202310796542.3A patent/CN116833698A/en active Pending
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