CN114973902B - Aeroengine low-pressure turbine model for teaching and assembly method - Google Patents
Aeroengine low-pressure turbine model for teaching and assembly method Download PDFInfo
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- CN114973902B CN114973902B CN202210390805.6A CN202210390805A CN114973902B CN 114973902 B CN114973902 B CN 114973902B CN 202210390805 A CN202210390805 A CN 202210390805A CN 114973902 B CN114973902 B CN 114973902B
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- G09B25/00—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes
- G09B25/02—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes of industrial processes; of machinery
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention discloses a low-pressure turbine model of an aeroengine for teaching and an assembly method thereof, wherein the low-pressure turbine model comprises a rotating part, a static part and a standard deep groove ball bearing; the rotating component comprises a low-pressure turbine main shaft, a conical shaft, a front double-stage low-pressure turbine blade disc, a rear double-stage low-pressure turbine blade disc and low-pressure turbine rotor blades; the static component comprises a low-pressure turbine casing, a low-pressure turbine stator vane ring, a bearing support plate and a low-pressure turbine rear support. The invention is a novel rotatable and repeatable disassembly and assembly aeroengine low-pressure turbine teaching model, can embody the precise blade structure, supporting structure and technical characteristics of the low-pressure turbine, and can realize reasonable cost and reliable structure while the precision is enough to meet the teaching requirement; and the assembly process is innovated, a new non-tooling assembly mode is established, so that the assembly of the model can be completed under the condition of an external field, and the safety and the high efficiency of exhibition and popular science activities can be ensured.
Description
Technical Field
The invention belongs to the technical field of aeroengines, relates to a teaching aid, and particularly relates to a low-pressure turbine model of an aeroengine for teaching and an assembly method.
Background
The aircraft engine is used as the heart of an aircraft, the structural design of the aircraft engine needs extremely high technological level and technological level, is one of the symbolism of national strength, and has extremely high demonstration explanation value in the scenes of college teaching, aviation exhibition, science popularization lectures and the like.
The existing display means are as follows:
1. most exhibitions are displayed in modes of pictures, videos and the like, so that the characteristics of the aeroengine structure with a complex and exquisite structure are difficult to embody, and the problems of non-visual, invisible, non-specific and vivid display exist;
2. part of universities and units can use the retired aeroengines for displaying, quarter-cut is carried out on the retired engines, and entity displaying is more visual and vivid relative to pictures, but the problems of high price, multiple parts, extremely complex disassembly and assembly, incapability of enabling students to experience the assembly process and flow of the engines, heaviness, difficulty in transportation and the like exist;
3. the independent design model of part of the exhibition is manufactured, and the problems of difficult processing, high cost, rough structure and the like still exist.
Therefore, the existing aeroengine solid model has poor popularization and small application range.
The aeroengine consists of a gas compressor, a combustion chamber, a turbine and the like, wherein the turbine converts part of heat energy and pressure energy of high-temperature and high-pressure fuel gas into rotary mechanical work through impeller machinery, so that the gas compressor and other accessories are driven to work, and the structural design of the aeroengine has extremely high display value. However, the requirements of repeated disassembly and assembly, rotatable rotor blades and the like are required to be completed, the technical difficulty is high, the blades and the supporting structure are often greatly simplified in various aeroengine models, the technical characteristics and the precise structure of the aeroengine models are difficult to embody, and the propaganda effect is greatly influenced.
Therefore, the low-pressure turbine teaching model and the component assembly flow thereof, which can embody the precise blade structure, the supporting structure and the technical characteristics of the low-pressure turbine, can be repeatedly disassembled and assembled, are easy to put on hands, are convenient to publicize and popularize, and are low in price, have important popularization significance and application scenes.
Disclosure of Invention
Aiming at the defects existing in the prior art, the invention aims to provide an aeroengine low-pressure turbine model for teaching and an assembly method thereof, wherein the model is a novel rotatable and repeatedly detachable aeroengine low-pressure turbine teaching model, can embody precise blade structures, supporting structures and technical characteristics of a low-pressure turbine, and can realize reasonable cost and reliable structures while the precision is enough to meet the teaching requirements. And the assembly process is innovated, a new non-tooling assembly mode is established, so that the assembly of the model is completed under the condition of an external field, and the safety and the high efficiency of exhibition and popular science activities can be ensured.
In order to solve the technical problems, the invention adopts the following technical scheme:
a low-pressure turbine model of an aeroengine for teaching comprises a rotating part, a static part and a standard deep groove ball bearing;
the rotating component comprises a low-pressure turbine main shaft, a conical shaft, a front double-stage low-pressure turbine blade disc, a rear double-stage low-pressure turbine blade disc and low-pressure turbine rotor blades; the conical shaft is sleeved outside the low-pressure turbine main shaft and connected with the low-pressure turbine main shaft, a front double-stage low-pressure turbine blade disc and a rear double-stage low-pressure turbine blade disc are respectively arranged on the front side and the rear side of the annular mounting edge of the conical shaft, and the low-pressure turbine rotor blades are arranged on the front double-stage low-pressure turbine blade disc and the rear double-stage low-pressure turbine blade disc; the standard deep groove ball bearing is sleeved at the rear part of the low-pressure turbine main shaft;
the static component comprises a low-pressure turbine casing, a low-pressure turbine stator vane ring, a bearing support plate and a low-pressure turbine rear support; the low-pressure turbine casing is sleeved outside the rotating part, the low-pressure turbine stator vane rings are arranged on the inner wall of the low-pressure turbine casing and are sequentially and alternately distributed with the low-pressure turbine rotor blades along the axial direction, the rear end of the low-pressure turbine casing is connected with the outer annular mounting edge of the low-pressure turbine rear support, the front end of the bearing support plate is sleeved on the standard deep groove ball bearing, and the rear end of the bearing support plate is connected with the inner annular mounting edge of the low-pressure turbine rear support;
the conical shaft can transmit torque to the front double-stage low-pressure turbine blade disc, the rear double-stage low-pressure turbine blade disc and the low-pressure turbine rotor blade, and transmit radial loads generated when the front double-stage low-pressure turbine blade disc, the rear double-stage low-pressure turbine blade disc and the low-pressure turbine rotor blade rotate to the low-pressure turbine main shaft through the conical shaft, and the load bearing support plate and the low-pressure turbine rear support seat transmit loads of the rotating component to the low-pressure turbine casing so that the bearing is safe and reliable.
The invention also comprises the following technical characteristics:
specifically, the low-pressure turbine main shaft comprises a main shaft body, a conical part arranged on the outer wall of the middle part of the main shaft body, and a front bearing positioning boss arranged on the outer wall of the rear part of the main shaft body, which is used for axially limiting a standard deep groove ball bearing; the outer edge of the conical part is an annular mounting edge which is used for being connected with the conical shaft to transmit torque to the conical shaft;
the rear annular mounting edge of the inner diameter-reducing cone part of the conical shaft is coaxially opposite to the annular mounting edge of the low-pressure turbine main shaft and is connected with the annular mounting edge of the low-pressure turbine main shaft through bolts, and the rear annular mounting edge of the outer diameter-reducing cone part of the conical shaft can be connected with the two-stage low-pressure turbine blade disc and the rear two-stage low-pressure turbine blade disc.
Specifically, the front double-stage low-pressure turbine blade disc comprises a first-stage low-pressure turbine blade disc and a second-stage low-pressure turbine blade disc which are connected, and the rear double-stage low-pressure turbine blade disc comprises a third-stage low-pressure turbine blade disc and a fourth-stage low-pressure turbine blade disc which are connected; the first-stage low-pressure turbine blade disc, the second-stage low-pressure turbine blade disc, the third-stage low-pressure turbine blade disc and the fourth-stage low-pressure turbine blade disc are sequentially arranged along the axial direction from front to back; the front annular mounting edge of the front double-stage low-pressure turbine blade disc is mounted on the rear annular mounting edge front wall of the outer flaring cone part of the conical shaft through bolts;
the low-pressure turbine rotor blade comprises an annular rotor outer ring, an annular rotor inner ring and rotor blades arranged between the rotor inner ring and the rotor outer ring, and the rotor blades have the characteristics of bending and twisting; the low-pressure turbine rotor blades are respectively arranged on the first-stage low-pressure turbine blade disc, the second-stage low-pressure turbine blade disc, the third-stage low-pressure turbine blade disc and the fourth-stage low-pressure turbine blade disc.
Specifically, the low-pressure turbine casing is of a flaring cylindrical structure, the front annular mounting edge of the low-pressure turbine casing can be connected with the high-pressure turbine, the rear annular mounting edge of the low-pressure turbine casing can be connected with the rear support of the low-pressure turbine, and the inner wall of the low-pressure turbine casing is provided with a plurality of annular grooves for mounting low-pressure turbine stator vane rings; the low-pressure turbine casing is formed by splicing two semi-arc-shaped shells.
Specifically, the low-pressure turbine stator vane ring comprises a stator outer ring and a stator inner ring, and stator blades arranged between the stator inner ring and the stator outer ring, wherein the stator blades have the characteristics of bending and twisting; the front end and the rear end of the stator outer ring are respectively provided with an inverted L-shaped hook, and the structure can be matched with the annular groove of the inner wall of the low-pressure turbine casing to install the low-pressure turbine stator vane ring on the inner wall of the low-pressure turbine casing;
the three low-pressure turbine stator vane rings are respectively arranged in the three annular grooves, and are sequentially positioned among the first-stage low-pressure turbine vane disk, the second-stage low-pressure turbine vane disk, the third-stage low-pressure turbine vane disk and the fourth-stage low-pressure turbine vane disk so that the low-pressure turbine stator vane rings and the low-pressure turbine rotor blades are sequentially and alternately distributed along the axial direction;
the stator inner ring and the rotor inner ring of the stator vane ring of the low-pressure turbine jointly form the inner wall surface of the low-pressure turbine runner, and the stator outer ring and the rotor outer ring jointly form the outer wall surface of the low-pressure turbine runner.
Specifically, the bearing support plate is of a horn-shaped structure and comprises a front end cylinder part and a rear cone cylinder part, wherein the front end cylinder part is sleeved on the deep groove ball bearing, a bearing rear positioning boss is arranged at the rear part of the inner wall of the front end cylinder part and used for axially positioning the rear end of the deep groove ball bearing, and the rear end of the rear cone cylinder part is provided with a rear mounting edge of the bearing support plate and is connected with a rear support of the low-pressure turbine.
Specifically, the low-pressure turbine rear support comprises a low-pressure turbine rear support inner ring, a low-pressure turbine rear support outer ring and a plurality of circumferentially uniformly distributed support pieces connected between the low-pressure turbine rear support inner ring and the low-pressure turbine rear support outer ring;
the front end mounting ring of the inner ring of the low-pressure turbine rear support is used for being connected with the rear mounting edge of the bearing support plate, and the front end mounting ring of the outer ring of the low-pressure turbine rear support is used for being connected with the rear annular mounting edge of the low-pressure turbine casing.
An assembling method of a low-pressure turbine model of an aeroengine for teaching comprises the following steps:
step 1, positioning a low-pressure turbine main shaft, connecting a conical shaft with the low-pressure turbine main shaft, and then installing a front double-stage low-pressure turbine blade disc and a rear double-stage low-pressure turbine blade disc on the conical shaft to finish the installation of a rotating part;
step 2, loading a low-pressure turbine stator vane ring into a low-pressure turbine casing;
step 3: and assembling the low-pressure turbine casing together through the low-pressure turbine rear support, the bearing support plate, the deep groove ball bearing and the low-pressure turbine main shaft to complete the assembly of the rotating part and the static part.
Compared with the prior art, the invention has the following beneficial technical effects:
(1) Compared with various existing engine models with too rough structures, the model provided by the invention can show the internal structure, the structural characteristics of parts, the mounting structure and the assembly mode of the engine, can show the precise blade structure, the supporting structure and the technical characteristics of the low-pressure turbine, and solves the problems that the details of the traditional engine model are too small to meet the teaching requirements and the size is too small to show.
(2) The size ratio of the model of the invention to various currently used commercial turbofan engines with real large bypass ratio is kept at about 1: and 3, the parts which can be mainly taught in teaching of the universities are mainly displayed, the problems that the structure is too complex and difficult to disassemble when a real engine is adopted as a teaching model are solved, and the structure has enough volume and internal space to carry out assembly teaching.
(3) The invention innovates an assembly method, the whole model can be repeatedly assembled and disassembled, the assembly and disassembly complexity and difficulty are moderate, and the requirements of the whole process display of engine assembly and the practical operation training of students in teaching can be met.
(4) The rotor of the model of the invention can rotate, adopts lower rotating speed, has low strength requirement on each part, reduces material and processing cost, and avoids the problem of high cost caused by using a mature commercial aeroengine in teaching.
Drawings
FIG. 1 is a cross-sectional view of the overall structure of the present invention;
FIG. 2 is a schematic diagram of the overall structure of the present invention;
FIG. 3 is a schematic view of a low pressure turbine spindle of the present invention;
FIG. 4 is a schematic view of a tapered shaft according to the present invention;
FIG. 5 is a schematic illustration of a forward dual stage low pressure turbine blade disk and low pressure turbine rotor blade according to the present invention;
FIG. 6 is a schematic illustration of a aft dual stage low pressure turbine blade disk and low pressure turbine rotor blade of the present invention;
FIG. 7 is a schematic view of a low pressure turbine case of the present invention;
FIG. 8 is a schematic view of a low pressure turbine stator vane ring according to the present invention;
FIG. 9 is a schematic view of a force bearing support plate according to the present invention;
FIG. 10 is a schematic view of the aft support of the low pressure turbine of the present invention.
The meaning of each reference numeral in the figures is:
11. a low pressure turbine main shaft, 12, a conical shaft, 13, a front double-stage low pressure turbine blade disc, 14, a rear double-stage low pressure turbine blade disc, 15, low pressure turbine rotor blades; 11-1, a main shaft body, 11-2, a conical part; 12-1, 12-2, 21, 22, 23, 24, and a low-pressure turbine rear support; 21-1 ring grooves; 23-1, a front end cylinder part, 23-2, a rear cone cylinder part; 24-1, 24-2, 24-3, of a support piece; 3. standard deep groove ball bearings.
Detailed Description
The following specific embodiments of the present invention are provided, and it should be noted that the present invention is not limited to the following specific embodiments, and all equivalent changes made on the basis of the technical solutions of the present application fall within the protection scope of the present invention.
Example 1:
the embodiment is an aeroengine low-pressure turbine model for teaching, and achieves the teaching display function of a typical structure and an assembly process of a modern large-bypass-ratio turbofan engine low-pressure turbine. The parts according to the embodiment can be processed and have sufficient strength under the condition of applying the photo-curing 3D printing processing technology. The low-pressure turbine model of the aero-engine for teaching of the embodiment can be combined with other part models, including a fan model, a high-pressure compressor model, an annular combustion chamber model and a high-pressure turbine model.
As shown in fig. 1 to 10, the present embodiment provides a low-pressure turbine model of an aero-engine for teaching, which includes a rotating part, a stationary part, and a standard deep groove ball bearing 3.
The rotating components include a low pressure turbine main shaft 11, a conical shaft 12, a front dual stage low pressure turbine disk 13, a rear dual stage low pressure turbine disk 14 and low pressure turbine rotor blades 15; the conical shaft 12 is sleeved outside the low-pressure turbine main shaft 11 and connected with the low-pressure turbine main shaft 11, a front double-stage low-pressure turbine blade disc 13 and a rear double-stage low-pressure turbine blade disc 14 are respectively arranged on the front side and the rear side of the annular mounting edge of the conical shaft 12, and low-pressure turbine rotor blades 15 are respectively arranged on the front double-stage low-pressure turbine blade disc 13 and the rear double-stage low-pressure turbine blade disc 14; the standard deep groove ball bearing 3 is sleeved at the rear part of the low-pressure turbine main shaft 11;
the static components comprise a low-pressure turbine casing 21, a low-pressure turbine stator vane ring 22, a bearing support plate 23 and a low-pressure turbine rear support 24; the low-pressure turbine casing 21 is sleeved outside the rotating part, the low-pressure turbine stator vane rings 22 are arranged on the inner wall of the low-pressure turbine casing 21 and are sequentially and alternately distributed with the low-pressure turbine rotor blades 15 along the axial direction, the rear end of the low-pressure turbine casing 21 is connected with the outer annular mounting edge of the low-pressure turbine rear support 24, the front end of the bearing support plate 23 is sleeved on the standard deep groove ball bearing 3, and the rear end of the bearing support plate 23 is connected with the inner annular mounting edge of the low-pressure turbine rear support 24;
the conical shaft 12 can transmit torque to the front double-stage low-pressure turbine blade disc 13, the rear double-stage low-pressure turbine blade disc 14 and the low-pressure turbine rotor blades 15, and transmit radial loads generated when the front double-stage low-pressure turbine blade disc 13, the rear double-stage low-pressure turbine blade disc 14 and the low-pressure turbine rotor blades 15 rotate to the low-pressure turbine main shaft 11 through the conical shaft 12, and the load bearing support plate 23 and the low-pressure turbine rear support 24 transmit loads of rotating parts to the low-pressure turbine casing 21 so as to ensure that the load bearing is safe and reliable.
The low-pressure turbine main shaft 11 comprises a main shaft body 11-1, a conical part 11-2 arranged on the outer wall of the middle part of the main shaft body 11-1, and a bearing front positioning boss arranged on the outer wall of the rear part of the main shaft body 11-1 and used for axially limiting the standard deep groove ball bearing 3; the outer edge of the conical part 11-2 is an annular mounting edge and is used for being connected with the conical shaft 12 to transmit torque to the conical shaft 12;
the conical shaft 12 comprises an inner diameter-reducing conical part 12-1 and an outer flaring conical part 12-2, the front ends of the inner diameter-reducing conical part 12-1 and the outer flaring conical part 12-2 are connected into an integral structure, the rear annular mounting edge of the inner diameter-reducing conical part 12-1 of the conical shaft 12 is coaxially opposite to the annular mounting edge of the low-pressure turbine main shaft 11 and is connected with the annular mounting edge through bolts, and the rear annular mounting edge of the outer flaring conical part 12-2 of the conical shaft 12 can be connected with the front double-stage low-pressure turbine blade disc 13 and the rear double-stage low-pressure turbine blade disc 14.
The front double-stage low-pressure turbine blade disc 13 comprises a first-stage low-pressure turbine blade disc and a second-stage low-pressure turbine blade disc which are connected, and the rear double-stage low-pressure turbine blade disc 14 comprises a third-stage low-pressure turbine blade disc and a fourth-stage low-pressure turbine blade disc which are connected; the first-stage low-pressure turbine blade disc, the second-stage low-pressure turbine blade disc, the third-stage low-pressure turbine blade disc and the fourth-stage low-pressure turbine blade disc are sequentially arranged along the axial direction from front to back; the rear annular mounting edge of the front double-stage low-pressure turbine blade disc 13 is mounted on the rear annular mounting edge front wall of the outer flaring cone 12-2 of the conical shaft 12 through bolts, and the front annular mounting edge of the rear double-stage low-pressure turbine blade disc 14 is mounted on the rear annular mounting edge rear wall of the outer flaring cone 12-2 of the conical shaft 12 through bolts;
the low pressure turbine rotor blades 15 include annular rotor outer and inner rings and rotor blades disposed between the rotor inner and outer rings, the rotor blades having a curved, twisted characteristic; the low pressure turbine rotor blades 15 are mounted on the first stage low pressure turbine blade disc, the second stage low pressure turbine blade disc, the third stage low pressure turbine blade disc and the fourth stage low pressure turbine blade disc, respectively.
The low-pressure turbine casing 21 is of a flaring cylindrical structure, the front annular mounting edge of the low-pressure turbine casing can be connected with a high-pressure turbine, the rear annular mounting edge of the low-pressure turbine casing can be connected with a low-pressure turbine rear support 24, and a plurality of annular grooves 21-1 are formed in the inner wall of the low-pressure turbine casing 21 and used for mounting low-pressure turbine stator vane rings 22; the low-pressure turbine casing 21 is formed by splicing two semi-arc shells.
The low pressure turbine stator vane ring 22 includes a stator outer ring and a stator inner ring and stator vanes disposed between the stator inner ring and the stator outer ring, the stator vanes having a curved and twisted characteristic; the front end and the rear end of the stator outer ring are respectively provided with an inverted L-shaped hook, and the structure can be matched with the annular groove 21-1 of the inner wall of the low-pressure turbine casing 21 to install the low-pressure turbine stator vane ring 22 on the inner wall of the low-pressure turbine casing 21; in the embodiment, each stage of stator vane ring is composed of two groups of stator vane groups, the circumferential rotation degree of each stator vane group is 177.5 degrees, and the stator vane groups are combined to be 355 degrees, so that a stator vane ring positioning notch 5.4 with the degree of 5 degrees is formed; after the stator blade group rotationally slides into the two half-casing through the annular grooves, circumferential positioning is completed through one positioning flange at the tail end of the annular groove of the half-casing.
The three low-pressure turbine stator vane rings 22 are arranged, the three low-pressure turbine stator vane rings 22 are respectively arranged in the three annular grooves 21-1, and the three low-pressure turbine stator vane rings 22 are sequentially arranged among the first-stage low-pressure turbine vane disk, the second-stage low-pressure turbine vane disk, the third-stage low-pressure turbine vane disk and the fourth-stage low-pressure turbine vane disk so that the low-pressure turbine stator vane rings 22 and the low-pressure turbine rotor blades 15 are sequentially and alternately distributed along the axial direction;
the stator inner ring and the rotor inner ring of the low-pressure turbine stator vane ring 22 jointly form the inner wall surface of the low-pressure turbine runner, and the stator outer ring and the rotor outer ring jointly form the outer wall surface of the low-pressure turbine runner.
The bearing support plate 23 is of a horn-shaped structure and comprises a front end cylindrical part 23-1 and a rear conical cylindrical part 23-2, the front end cylindrical part 23-1 is sleeved on the deep groove ball bearing 3, a bearing rear positioning boss is arranged at the rear part of the inner wall of the front end cylindrical part 23-1 and used for axially positioning the rear end of the deep groove ball bearing 3, and the rear end of the rear conical cylindrical part 23-2 is a rear mounting edge of the bearing support plate and is connected with the rear support 24 of the low-pressure turbine.
The low pressure turbine aft support 24 includes a low pressure turbine aft support inner ring 24-1, a low pressure turbine aft support outer ring 24-2, and a plurality of circumferentially uniform support tabs 24-3 connected between the low pressure turbine aft support inner ring 24-1 and the low pressure turbine aft support outer ring 24-2; the support piece is used for leveling low-pressure turbine outlet air flow, the annular baffle structure outside the inner ring of the low-pressure turbine rear support forms the end structure of the low-pressure turbine runner through a simple structure, and the sealing structure of the aeroengine turbine is shown.
The front end mounting ring of the low-pressure turbine rear support inner ring 24-1 is used for being connected with the rear mounting edge of the bearing support plate, and the front end mounting ring of the low-pressure turbine rear support outer ring 24-2 is used for being connected with the rear annular mounting edge of the low-pressure turbine casing 21.
In the embodiment, the components are connected by adopting bolts, nuts are fixed at bolt holes at the bolt connection positions, specifically, the nuts are glued and fixed by utilizing a counter bore structure, and then bolts are screwed into the nuts fixed at the counter bore positions to complete the bolt connection so as to complete the bolt connection at a narrow space without tools; in this way, the low-pressure turbine is connected and mounted by mounting the rotor disk at each stage on the tapered shaft, mounting and connecting the tapered tube and the low-pressure turbine main shaft, and the like.
The positioning structure of the low-pressure turbine main shaft and the standard deep groove ball bearing thereof is formed by the standard deep groove ball bearing, the front bearing positioning boss of the low-pressure turbine main shaft, the rear bearing positioning boss of the bearing support plate and the front mounting edge of the bearing support plate, and after the standard deep groove ball bearing is arranged at the corresponding position of the positioning structure, the assembly can be completed by only carrying out bolt connection on the low-pressure turbine bearing retainer ring and the bearing support plate through the front mounting edge of the bearing support plate, and the assembly is convenient and simple.
Through the technical scheme, the novel rotatable and repeatable detachable low-pressure turbine teaching model of the aeroengine is provided, the precise blade structure, the supporting structure and the technical characteristics of the low-pressure turbine can be embodied, and the reasonable cost and reliable structure can be realized while the precision is enough to meet the teaching requirement; and the assembly process is innovated, a new non-tooling assembly mode is established, so that the assembly of the model can be completed under the condition of an external field, and the safety and the high efficiency of exhibition and popular science activities can be ensured. Specifically, the method comprises the following steps;
a. the invention designs a novel low-pressure turbine force transmission system, which has stable structure and strong fault tolerance rate, transmits torque and load, ensures that a low-pressure turbine rotor can stably operate under the force transmission of the system, greatly reduces the manufacturing difficulty and the assembly difficulty under the same complexity of parts, and ensures that parts are still reliable and effective under the condition of complex multi-part matching. b. The novel double-stage blisk structure is designed, so that the function of teaching aid showing the complex structure of the turbine blisk of the aero-engine is realized with relatively low complexity of parts. The integrated manufacturing of accessible 3D printing simplifies the assembly, avoids the problem that the internal structure size that single-stage leaf disc can face when teaching the assembly is narrow and small can't assemble with the bolt. c. A novel limited space installation mode is designed, nuts are glued to the parts to be connected by glue, and then bolts are assembled. The mode does not need a tool, avoids using complex tools, reduces assembly difficulty, solves the problem that automatic assembly cannot be performed, and achieves multiple disassembly and assembly functions. d. The novel low-pressure turbine main shaft and the positioning structure of the bearing thereof solve the problem of difficult positioning of the bearing, can directly use the conventional bearing on the market, and do not need to design a special bearing structure. Accurate positioning, convenient use and can meet the requirement of repeatable assembly. e. According to the scheme, the axial positioning of the low-pressure turbine main shaft is carried out by adopting the deep groove ball bearing, and the conventional rolling rod bearing connection which cannot bear excessive axial load is changed into the deep groove ball bearing connection which can bear axial load and radial load simultaneously, so that the axial load of the aeroengine teaching model in the repeated disassembly and assembly and carrying process can be borne, the radial load of the rotor during rotation can be borne, the bearing force is more stable, and the reliability is improved. f. Compared with an excessively simple engine teaching aid, the structure can show students the mounting mode and the fixing mode of stator blades of an engine more truly; compared with an excessively complex engine teaching aid, the novel stator blade set has the advantages that the number of stator blade sets is reduced, the novel stator blade hook structure is simplified, the novel stator blade set can be integrally manufactured through 3D printing, the assembly process is simplified, and the manufacturing cost is reduced. g. This scheme has designed novel low pressure turbine back support structure, compares in too simple engine teaching aid, and this structure can more conveniently demonstrate the runner structure of the low pressure turbine of engine to the student. Compared with an excessively complex engine teaching aid, the novel engine teaching aid reduces structural complexity, reduces processing difficulty, can be integrally manufactured through 3D printing, simplifies assembly process and reduces manufacturing cost.
The low-pressure turbine model of the aero-engine for teaching in the embodiment can be detachably combined with the fan model, the high-pressure turbine model, the high-pressure compressor model and the combustion chamber model to obtain the aero-engine model for teaching; specifically, the intermediate casing of the fan model is connected with the front end of the outer casing of the high-pressure compressor model, the high-pressure rotor transmission part of the fan model is arranged between the first-stage movable vane disk and the second-stage movable vane disk of the high-pressure compressor model, the rear ends of the outer casing and the inner casing of the high-pressure compressor model are connected with the front end of the outer casing of the combustion chamber model, the rear ends of the outer casing and the inner casing of the combustion chamber model are connected with the high-pressure turbine model, the rear end of the third-stage movable vane disk of the high-pressure compressor model is connected with the high-pressure shaft coupling of the high-pressure turbine model, and the guide at the rear end of the high-pressure turbine model is connected with the low-pressure turbine model.
Example 2:
the embodiment provides an assembly method of a low-pressure turbine model of an aeroengine for teaching, which comprises the following steps:
step 1, positioning a low-pressure turbine main shaft, connecting a conical shaft with the low-pressure turbine main shaft, and then installing a front double-stage low-pressure turbine blade disc and a rear double-stage low-pressure turbine blade disc on the conical shaft to finish the installation of a rotating part; specifically, circumferential positioning of the rear annular mounting edge of the inner diameter-reducing conical part of the conical shaft and the outer edge of the conical part on the low-pressure turbine main shaft at the rear section mounting position of the low-pressure turbine main shaft is completed;
step 2, loading a low-pressure turbine stator vane ring into a low-pressure turbine casing; specifically, two stator blade groups of each stage are installed in ring grooves of a low-pressure turbine half-casing, and then the stator assembly and the two half-casings of the low-pressure turbine are combined at the outer end of a rotating part through longitudinal installation edges;
step 3: assembling the low-pressure turbine casing together through a low-pressure turbine rear support, a bearing support plate, a deep groove ball bearing and a low-pressure turbine main shaft to complete the assembly of a rotating part and a static part; thus, the assembly of the low-pressure turbine model of the aero-engine for teaching is completed.
Claims (5)
1. The low-pressure turbine model of the aero-engine for teaching is characterized by comprising a rotating part, a static part and a standard deep groove ball bearing (3);
the rotating part comprises a low-pressure turbine main shaft (11), a conical shaft (12), a front double-stage low-pressure turbine blade disc (13), a rear double-stage low-pressure turbine blade disc (14) and low-pressure turbine rotor blades (15); the conical shaft (12) is sleeved outside the low-pressure turbine main shaft (11) and connected with the low-pressure turbine main shaft (11), a front double-stage low-pressure turbine blade disc (13) and a rear double-stage low-pressure turbine blade disc (14) are respectively arranged on the front side and the rear side of the annular mounting edge of the conical shaft (12), and the low-pressure turbine rotor blades (15) are arranged on the front double-stage low-pressure turbine blade disc (13) and the rear double-stage low-pressure turbine blade disc (14); the standard deep groove ball bearing (3) is sleeved at the rear part of the low-pressure turbine main shaft (11);
the static component comprises a low-pressure turbine casing (21), a low-pressure turbine stator vane ring (22), a bearing support plate (23) and a low-pressure turbine rear support (24); the low-pressure turbine casing (21) is sleeved outside the rotating part, low-pressure turbine stator vane rings (22) are arranged on the inner wall of the low-pressure turbine casing (21) and are sequentially and alternately distributed with low-pressure turbine rotor blades (15) along the axial direction, the rear end of the low-pressure turbine casing (21) is connected with the outer annular mounting edge of the low-pressure turbine rear support (24), the front end of the bearing support plate (23) is sleeved on the standard deep groove ball bearing (3), and the rear end of the bearing support plate (23) is connected with the inner annular mounting edge of the low-pressure turbine rear support (24);
the conical shaft (12) can transmit torque to the front double-stage low-pressure turbine blade disc (13), the rear double-stage low-pressure turbine blade disc (14) and the low-pressure turbine rotor blades (15), and transmit radial loads of the front double-stage low-pressure turbine blade disc (13), the rear double-stage low-pressure turbine blade disc (14) and the low-pressure turbine rotor blades (15) when rotating to the low-pressure turbine main shaft (11) through the conical shaft (12), and the bearing support plate (23) and the low-pressure turbine rear support (24) transmit loads of rotating parts to the low-pressure turbine casing (21) so that the bearing is safe and reliable;
the low-pressure turbine main shaft (11) comprises a main shaft body (11-1), a conical part (11-2) arranged on the outer wall of the middle part of the main shaft body (11-1), and a bearing front positioning boss arranged on the outer wall of the rear part of the main shaft body (11-1) for axially limiting a standard deep groove ball bearing (3); the outer edge of the conical part (11-2) is an annular mounting edge which is used for being connected with the conical shaft (12) to transmit torque to the conical shaft (12);
the conical shaft (12) comprises an inner diameter-reducing conical part (12-1) and an outer flaring conical part (12-2), the front ends of the inner diameter-reducing conical part and the outer flaring conical part are connected into an integral structure, the rear annular mounting edge of the inner diameter-reducing conical part (12-1) of the conical shaft (12) is coaxially opposite to the annular mounting edge of the low-pressure turbine main shaft (11) and is connected with the annular mounting edge of the low-pressure turbine main shaft through bolts, and the rear annular mounting edge of the outer flaring conical part (12-2) of the conical shaft (12) can be connected with a front two-stage low-pressure turbine blade disc (13) and a rear two-stage low-pressure turbine blade disc (14);
the front double-stage low-pressure turbine blade disc (13) comprises a first-stage low-pressure turbine blade disc and a second-stage low-pressure turbine blade disc which are connected, and the rear double-stage low-pressure turbine blade disc (14) comprises a third-stage low-pressure turbine blade disc and a fourth-stage low-pressure turbine blade disc which are connected; the first-stage low-pressure turbine blade disc, the second-stage low-pressure turbine blade disc, the third-stage low-pressure turbine blade disc and the fourth-stage low-pressure turbine blade disc are sequentially arranged along the axial direction from front to back; the rear annular mounting edge of the front two-stage low-pressure turbine blade disc (13) is mounted on the rear annular mounting edge front wall of the outer flaring cone part (12-2) of the conical shaft (12) through bolts, and the front annular mounting edge of the rear two-stage low-pressure turbine blade disc (14) is mounted on the rear annular mounting edge rear wall of the outer flaring cone part (12-2) of the conical shaft (12) through bolts;
the low-pressure turbine rotor blade (15) comprises an annular rotor outer ring, an annular rotor inner ring and rotor blades arranged between the rotor inner ring and the rotor outer ring, and the rotor blades have the characteristics of bending and twisting; the low-pressure turbine rotor blades (15) are respectively arranged on the first-stage low-pressure turbine blade disc, the second-stage low-pressure turbine blade disc, the third-stage low-pressure turbine blade disc and the fourth-stage low-pressure turbine blade disc;
the low-pressure turbine casing (21) is of a flaring cylindrical structure, the front annular mounting edge of the low-pressure turbine casing can be connected with the high-pressure turbine, the rear annular mounting edge of the low-pressure turbine casing can be connected with the low-pressure turbine rear support (24), and a plurality of annular grooves (21-1) are formed in the inner wall of the low-pressure turbine casing (21) and used for mounting low-pressure turbine stator vane rings (22); the low-pressure turbine casing (21) is formed by splicing two semi-arc-shaped shells.
2. The teaching aeroengine low-pressure turbine model of claim 1, wherein the low-pressure turbine stator vane ring (22) comprises a stator outer ring and a stator inner ring and stator blades arranged between the stator inner ring and the stator outer ring, the stator blades having bending and twisting characteristics; the front end and the rear end of the stator outer ring are respectively provided with an inverted L-shaped hook, and the structure can be matched with a ring groove (21-1) on the inner wall of the low-pressure turbine casing (21) to install a low-pressure turbine stator vane ring (22) on the inner wall of the low-pressure turbine casing (21);
the three low-pressure turbine stator vane rings (22) are respectively arranged in the three annular grooves (21-1), and the three low-pressure turbine stator vane rings (22) are sequentially positioned among the first-stage low-pressure turbine vane disk, the second-stage low-pressure turbine vane disk, the third-stage low-pressure turbine vane disk and the fourth-stage low-pressure turbine vane disk so that the low-pressure turbine stator vane rings (22) and the low-pressure turbine rotor blades (15) are alternately distributed along the axial direction;
the stator inner ring and the rotor inner ring of the low-pressure turbine stator vane ring (22) jointly form the inner wall surface of the low-pressure turbine runner, and the stator outer ring and the rotor outer ring jointly form the outer wall surface of the low-pressure turbine runner.
3. The teaching aircraft engine low-pressure turbine model as claimed in claim 1, wherein the bearing support plate (23) is of a horn-shaped structure and comprises a front end cylindrical part (23-1) and a rear cone cylindrical part (23-2), the front end cylindrical part (23-1) is sleeved on the deep groove ball bearing (3), a bearing rear positioning boss is arranged at the rear part of the inner wall of the front end cylindrical part (23-1) and used for axially positioning the rear end of the deep groove ball bearing (3), and the rear end of the rear cone cylindrical part (23-2) is provided with a bearing support plate rear mounting edge so as to be connected with the low-pressure turbine rear support (24).
4. A teaching aeroengine low pressure turbine model as claimed in claim 3, wherein the low pressure turbine aft support (24) comprises a low pressure turbine aft support inner ring (24-1), a low pressure turbine aft support outer ring (24-2) and a plurality of circumferentially equispaced support tabs (24-3) connected between the low pressure turbine aft support inner ring (24-1) and the low pressure turbine aft support outer ring (24-2);
the front end mounting ring of the low-pressure turbine rear support inner ring (24-1) is used for being connected with the rear mounting edge of the bearing support plate, and the front end mounting ring of the low-pressure turbine rear support outer ring (24-2) is used for being connected with the rear annular mounting edge of the low-pressure turbine casing (21).
5. A method of assembling a low pressure turbine model of an aircraft engine for teaching as claimed in claim 1, comprising the steps of:
step 1, positioning a low-pressure turbine main shaft, connecting a conical shaft with the low-pressure turbine main shaft, and then installing a front double-stage low-pressure turbine blade disc and a rear double-stage low-pressure turbine blade disc on the conical shaft to finish the installation of a rotating part;
step 2, loading a low-pressure turbine stator vane ring into a low-pressure turbine casing;
step 3: and assembling the low-pressure turbine casing together through the low-pressure turbine rear support, the bearing support plate, the deep groove ball bearing and the low-pressure turbine main shaft to complete the assembly of the rotating part and the static part.
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