CN116000604B - Turbine disc of aero-engine and front sealing disc assembly device and method thereof - Google Patents
Turbine disc of aero-engine and front sealing disc assembly device and method thereof Download PDFInfo
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- CN116000604B CN116000604B CN202211741386.2A CN202211741386A CN116000604B CN 116000604 B CN116000604 B CN 116000604B CN 202211741386 A CN202211741386 A CN 202211741386A CN 116000604 B CN116000604 B CN 116000604B
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- 238000007789 sealing Methods 0.000 title claims abstract description 131
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000001816 cooling Methods 0.000 claims abstract description 15
- 238000003825 pressing Methods 0.000 claims description 15
- 239000000523 sample Substances 0.000 claims description 6
- 230000000694 effects Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application provides an aircraft engine turbine disk and a front sealing disk assembly device and a method thereof, wherein the aircraft engine turbine disk and the front sealing disk assembly device thereof comprise: the pulling disc is provided with a mounting hole at the disc center part and countersunk head pulling holes and large abdication holes distributed along the circumferential direction at the edge part; each countersunk head pulling hole is correspondingly communicated with one big abdicating hole; the hook end of each draw hook is correspondingly hooked into one cooling hole of the front sealing disc, the root of each draw hook correspondingly passes through one large abdication hole and is clamped into the corresponding countersunk head draw hole; the hydraulic cylinder is in threaded connection with the mounting hole; the pressure plate is pressed at the end part of the front shaft neck of the front sealing disc, positioned with the end part of the front shaft neck of the front sealing disc through a spigot and positioned with the output end of the hydraulic cylinder through the spigot; the plane pressure bearing is pressed at the center of the turbine disk, is positioned with the spigot between the center of the turbine disk and the pressure disk, and is positioned with the pressure disk through the spigot.
Description
Technical Field
The application belongs to the technical field of assembly design of an aeroengine turbine disc and a front sealing disc thereof, and particularly relates to an aeroengine turbine disc and a front sealing disc assembly device and method thereof.
Background
The working environment of the turbine disk of the aeroengine is severe and bears severe high-temperature load, and the turbine disk is provided with a front sealing disk which is connected to the front side of the turbine disk, a cooling cavity is formed between the turbine disk and the front sealing disk, cooling holes communicated with the cooling cavity are formed in the cooling cavity, the cooling holes are circumferentially distributed, cooling gas is introduced into the cooling cavity through the cooling holes, and the turbine disk is subjected to impact cooling.
In order to realize connection between a turbine disc and a front sealing disc of an aeroengine, an annular bayonet is arranged on the front side of the turbine disc 1, a plurality of turbine disc lugs 3 distributed along the circumferential direction are arranged on the outer side of a front shaft neck of the turbine disc 1, annular folded edges are arranged on the front sealing disc 2 and clamped into the annular bayonet, a plurality of front sealing disc lugs 4 distributed along the circumferential direction are arranged on the inner side of the front shaft neck of the front sealing disc 2, and each front sealing disc lug 4 correspondingly abuts against one turbine disc lug 3 from the inner side, so that connection between the turbine disc and the front sealing disc is realized, and the connection between the turbine disc and the front sealing disc is shown in fig. 1.
When assembling the turbine disk and the front sealing disk of the aeroengine, the annular edge folding clamp on the front sealing disk 2 is required to be clamped into the annular bayonet, after the annular edge folding clamp is clamped into the annular bayonet, each front sealing disk lug 4 is higher than the turbine disk lug 3, when the assembly is further carried out, the front sealing disk 2 is required to be further forced, the front sealing disk 2 is deformed, each front sealing disk lug 4 can enter the bottom through the discontinuous part between each turbine disk lug 3, each front sealing disk lug 4 is aligned with the corresponding turbine disk lug 3 through rotation, each front sealing disk lug 4 can be propped against the corresponding turbine disk lug 3 from the inner side after the assembly is released, the assembly is finished, the process is carried out by manpower by means of a simple tool, the situation of insufficient forcing or overlarge forcing exists, time and labor are consumed, and the damage to components is easily caused.
The present application has been made in view of the above-described technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present patent application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide an aircraft engine turbine disc and a front sealing disc assembling device and method thereof, which overcome or alleviate at least one technical defect of the prior art.
The technical scheme of the application is as follows:
an aspect provides an aeroengine turbine disk and front seal disk assembly device thereof, includes:
the pulling disc is provided with a mounting hole at the disc center part and countersunk head pulling holes and large abdication holes distributed along the circumferential direction at the edge part; each countersunk head pulling hole is correspondingly communicated with one big abdicating hole;
the hook end of each draw hook is correspondingly hooked into one cooling hole of the front sealing disc, the root of each draw hook correspondingly passes through one large abdication hole and is clamped into the corresponding countersunk head draw hole; the annular folded edges on the front sealing disc are clamped into annular bayonets on the turbine disc, and lugs of each front sealing disc and lugs of each turbine disc are distributed in a staggered manner;
the hydraulic cylinder is in threaded connection with the mounting hole;
the pressure plate is pressed at the end part of the front shaft neck of the front sealing disc, positioned with the end part of the front shaft neck of the front sealing disc through a spigot and positioned with the output end of the hydraulic cylinder through the spigot;
the plane pressure bearing is pressed at the center of the turbine disk, positioned with the spigot between the center of the turbine disk and positioned with the pressure disk through the spigot;
the pneumatic cylinder can exert pressure to the pressure disk, produces pulling force simultaneously on the pulling disc, makes preceding sealing disc take place to warp to this makes each preceding sealing disc lug enter into the bottom through the intermittent type position between each turbine disc lug, and then can rotate the pulling disc and drive preceding sealing disc rotation, makes each preceding sealing disc lug align with corresponding turbine disc lug, releases the pressure of pneumatic cylinder to the pressure disk, makes each preceding sealing disc lug from inboard support to on the turbine disc lug that corresponds.
According to at least one embodiment of the present application, in the above-mentioned turbine disk of an aeroengine and front seal disk assembly device thereof, further comprises:
the cushion block is positioned between the output end of the hydraulic cylinder and the pressure plate and positioned between the cushion block and the output end of the hydraulic cylinder and the pressure plate through the spigot.
According to at least one embodiment of the application, in the turbine disc of the aeroengine and the front sealing disc assembly device thereof, through holes are formed in the hydraulic cylinder, the pressure disc and the cushion block;
further comprises:
one end of the positioning rod passes through the through holes on the hydraulic cylinder, the pressure plate and the cushion block and is connected to the plane pressure bearing.
According to at least one embodiment of the present application, in the turbine disc of an aeroengine and the front seal disc assembly device thereof, the planar pressure bearing is provided with a plurality of first positioning holes distributed along the circumferential direction;
the turbine disc of the aero-engine and the front sealing disc assembly device thereof further comprise:
the base is arranged at the bottom of the turbine disc;
the first positioning pins are connected to the turbine disk and distributed along the circumferential direction; each first locating pin is correspondingly inserted into one second locating hole on the turbine disk;
one end of the positioning ring is connected to the base through a pin, and the other end of the positioning ring is provided with a plurality of third positioning holes;
the positioning plate is provided with a plurality of fourth positioning holes, and is positioned at one end of the positioning ring, which is opposite to the base, and one end of the positioning ring, which is opposite to the base, is positioned through the spigot;
and each second locating pin correspondingly penetrates through one fourth locating hole, one end of each second locating pin is correspondingly inserted into one first locating hole, and the other end of each second locating pin is correspondingly inserted into one third locating hole.
According to at least one embodiment of the application, in the turbine disc of the aeroengine and the front sealing disc assembly device thereof, the base is provided with a plurality of supporting bulges;
the turbine disc of the aero-engine and the front sealing disc assembly device thereof further comprise:
the connecting ring is sleeved on the periphery of the front shaft neck of the front sealing disc, and is provided with a plurality of perforations distributed along the circumferential direction and a plurality of protruding parts; each draw hook correspondingly penetrates through one perforation, and the outer wall is provided with a stop protrusion so as to support the connecting ring;
the jackscrews are correspondingly screwed on one supporting protrusion;
each jackscrew can correspondingly lean against a convex part on the connecting ring through rotation, so that the pulling disc and the front sealing disc are pushed to rotate.
According to at least one embodiment of the present application, in the above-mentioned turbine disk of an aeroengine and front seal disk assembly device thereof, further comprises:
and a plurality of dial indicators connected to the pull disc, wherein the probes are in end surface contact with the mounting edge of the front sealing disc.
According to at least one embodiment of the present application, in the above-mentioned turbine disk of an aeroengine and front seal disk assembly device thereof, further comprises:
the position checking pin is detachably connected to the pull disc, and when the position checking pin is detached, position calibration holes on the turbine disc and the front sealing disc can be detected.
According to at least one embodiment of the application, in the turbine disc of the aeroengine and the front sealing disc assembly device thereof, the pull disc and the pressure disc are provided with a plurality of lifting lugs.
In another aspect, an aircraft engine turbine disk and a method for assembling a front seal disk thereof are provided, including:
the annular folded edges on the front sealing disc are clamped into annular bayonets on the turbine disc, and the front sealing disc lugs and the turbine disc lugs are distributed in a staggered manner by rotation;
the method comprises the steps that a first locating pin, a locating ring, a locating plate, a second locating pin and a jackscrew are assembled on a base;
the turbine disc is placed on the base, and is circumferentially positioned by using the first positioning pin and axially positioned by using the positioning ring;
pressing the plane pressure bearing assembled with the positioning rod to the center part of the turbine disc, and assembling with a second positioning pin;
hooking the hook end of each draw hook into a corresponding cooling hole on the front sealing disc;
the connecting ring is sleeved on the periphery of the front shaft neck of the front sealing disc, and is assembled with each drag hook to position each drag hook;
the pressing plate, the cushion block, the pulling plate and the hydraulic cylinder are assembled on the positioning rod, so that the pressing plate is pressed on the end part of the front shaft neck of the front sealing plate;
rotating the pulling disc to enable each big abdication hole to be aligned with the root of the corresponding pulling hook, pressing down the sleeve to the root of the corresponding pulling hook, and clamping the root of each pulling hook into the corresponding countersunk head pulling hole through rotation;
assembling a dial indicator on the pull disc, enabling a dial indicator probe to be in contact with the end face of the mounting edge of the front sealing disc, and adjusting the dial indicator to be in a zero position;
the hydraulic cylinder applies pressure to the pressure plate to deform the front sealing plate;
after judging that all the lugs of the front sealing disc enter the bottom in place through the intermittent parts among the lugs of the turbine disc through the indication number of the dial indicator, rotating jackscrews to abut against the corresponding protruding parts on the connecting ring to push the pulling disc and the front sealing disc to rotate;
the position checking pins are used for detecting position calibration holes on the turbine disk and the front sealing disk, and after judging that each front sealing disk lug is aligned with the corresponding turbine disk lug, the pressure of the hydraulic cylinder on the pressure disk is released, so that each front sealing disk lug is propped against the corresponding turbine disk lug from the inner side.
Drawings
FIG. 1 is a schematic illustration of an aircraft engine turbine disk, front seal inter-disk connection;
FIG. 2 is a schematic view of an aircraft engine turbine disk and its front seal disk assembly apparatus provided by an embodiment of the present application;
FIG. 3 is a top view of an aircraft engine turbine disk and its front seal disk assembly device provided by an embodiment of the present application;
FIG. 4 is a schematic working diagram of an aircraft engine turbine disk and a front seal disk assembly device thereof according to an embodiment of the present application;
wherein:
1-a turbine disk; 2-a front sealing disc 2; 3-turbine disk lugs 3; 4-front sealing the disc lugs 4; 5-pulling a disc; 6-drag hook; 7-a hydraulic cylinder; 8-pressing plates; 9-plane pressure bearings; 10-cushion blocks; 11-positioning rod; 12-a base; 13-a first positioning pin; 14-positioning rings; 15-positioning plates; 16-a second locating pin; 17-connecting ring; 18-jackscrews; 19-percent meter; 20-position checking pin.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The application is described in further detail below with reference to fig. 1 to 4.
In one aspect, an aeroengine turbine disk and a front seal disk assembly device thereof are provided, as shown in fig. 2, including:
the pulling disc 5 is provided with a mounting hole at the disc center part and countersunk pulling holes and large abdicating holes distributed along the circumferential direction at the edge part; each countersunk head pulling hole is correspondingly communicated with one big abdicating hole;
the hook end of each draw hook 6 is correspondingly hooked into one cooling hole of the front sealing disc 2, the root part correspondingly passes through one large abdication hole and is blocked into the corresponding countersunk head draw hole; the annular folded edges on the front sealing disc 2 are clamped into annular bayonets on the turbine disc 1, and all the front sealing disc lugs 4 and all the turbine disc lugs 3 are distributed in a staggered manner;
the hydraulic cylinder 7 is arranged in the mounting hole in a threaded manner;
the pressure plate 8 is pressed at the end part of the front shaft neck of the front sealing disc 2, is positioned with the end part of the front shaft neck of the front sealing disc 2 through a spigot, and is positioned with the output end of the hydraulic cylinder 7 through the spigot;
a plane pressure bearing 9 which is pressed on the center of the turbine disk 1, is positioned with a spigot between the center of the turbine disk 1 and a pressure disk 8 through the spigot;
the pneumatic cylinder 7 can exert pressure to pressure disk 8, simultaneously produce pulling force on pulling disc 5, make preceding sealing disc 2 take place to warp to this makes each preceding sealing disc lug 4 enter into the bottom through the intermittent part between each turbine disc lug 3, and then can rotate pulling disc 5 and drive preceding sealing disc 2 and rotate, makes each preceding sealing disc lug 4 align with corresponding turbine disc lug 3, releases the pneumatic cylinder 7 to pressure disk 8's pressure, makes each preceding sealing disc lug 4 from the inboard support to corresponding turbine disc lug 3 on.
After the annular folded edges on the front sealing disc 2 are clamped into the annular bayonets on the turbine disc 1 and rotated to enable the lugs 4 of each front sealing disc and the lugs 3 of each turbine disc to be distributed in a staggered manner, the aeroengine turbine disc and the front sealing disc assembly device thereof disclosed by the embodiment can be used for applying force to the front sealing disc 2 to deform the front sealing disc 2, so that the assembly of the turbine disc 1 and the front sealing disc 2 can be easily completed, and the specific process can refer to the aeroengine turbine disc and the front sealing disc assembly method thereof disclosed by the embodiment of the application.
In some optional embodiments, in the above turbine disk of an aeroengine and the front seal disk assembly device thereof, the method further includes:
the cushion block 10 is positioned between the output end of the hydraulic cylinder 7 and the pressure plate 8 and positioned between the output end of the hydraulic cylinder 7 and the pressure plate 8 through the spigot.
In some alternative embodiments, in the turbine disc of the aeroengine and the front sealing disc assembly device thereof, the hydraulic cylinder 7, the pressure disc 8 and the cushion block 10 are provided with through holes;
further comprises:
one end of the positioning rod 11 penetrates through the through holes in the hydraulic cylinder 7, the pressure plate 8 and the cushion block 10 and is connected to the plane pressure bearing 9, so that the positioning and the assembly of the plane pressure bearing 9 and the positioning and the assembly of the hydraulic cylinder 7, the pressure plate 8 and the cushion block 10 can be facilitated.
In some alternative embodiments, in the turbine disc of the aeroengine and the front sealing disc assembly device thereof, the planar pressure bearing 9 is provided with a plurality of first positioning holes distributed along the circumferential direction;
the turbine disc of the aero-engine and the front sealing disc assembly device thereof further comprise:
a base 12 provided at the bottom of the turbine disk 1;
a plurality of first positioning pins 13 connected to the turbine disk 1 and distributed in the circumferential direction; each first locating pin 13 is correspondingly inserted into one second locating hole on the turbine disc 1, so that the turbine disc 1 can be circumferentially located, rotation of the front sealing disc 2 in the rotation process is prevented, and smooth assembly is ensured;
one end of the positioning ring 14 is connected to the base 12 through a pin, and the other end of the positioning ring is provided with a plurality of third positioning holes, so that the positioning ring 14 can be used for axially positioning the turbine disk 1 when in use;
the positioning plate 15 is provided with a plurality of fourth positioning holes, and is positioned between one end of the positioning ring 14, which is away from the base 12, and one end of the positioning ring 14, which is away from the base 12, through a spigot;
and each second positioning pin 16 is correspondingly penetrated through one fourth positioning hole, one end of each second positioning pin 16 is correspondingly inserted into one first positioning hole, and the other end of each second positioning pin is correspondingly inserted into one third positioning hole, so that the positioning and the assembly of the plane pressure bearing 9 are facilitated.
In some alternative embodiments, the turbine disk of the aero-engine and its front seal disk assembly device described above, the base 12 has a plurality of support protrusions thereon;
the turbine disc of the aero-engine and the front sealing disc assembly device thereof further comprise:
the connecting ring 17 is sleeved on the outer periphery of the front shaft neck of the front sealing disc 2, and is provided with a plurality of perforations distributed along the circumferential direction and a plurality of protruding parts; each draw hook 6 is correspondingly arranged through one perforation, and the outer wall is provided with a stop protrusion for supporting the connecting ring 17;
a plurality of jackscrews 18, each of which is screwed onto a corresponding one of the support projections;
each jackscrew 18 can correspondingly abut against a protruding part on the connecting ring 17 through rotation, so that the pulling disc 5 and the front sealing disc 2 are pushed to rotate, and the counter thrust is acted on the base 12.
In some optional embodiments, in the above turbine disk of an aeroengine and the front seal disk assembly device thereof, the method further includes:
and a plurality of dial indicators 19 connected to the pull disc 5, wherein the probes are in contact with the end surface of the mounting side of the front sealing disc 2, and can indicate the deformation of the front sealing disc 2.
In some optional embodiments, in the above turbine disk of an aeroengine and the front seal disk assembly device thereof, the method further includes:
the position checking pin 20 is detachably connected to the pull disk 5, and can detect the position calibration holes in the turbine disk 1 and the front seal disk 2 when detached.
In some alternative embodiments, in the turbine disc of the aeroengine and the front sealing disc assembly device thereof, the pull disc 5 and the pressure disc 8 are provided with a plurality of lifting lugs so as to facilitate lifting.
In another aspect, an aircraft engine turbine disk and a method for assembling a front seal disk thereof are provided, including:
the annular folded edges on the front sealing disc 2 are clamped into annular bayonets on the turbine disc 1, and the front sealing disc lugs 4 and the turbine disc lugs 3 are distributed in a staggered manner by rotating;
the first positioning pin 13, the positioning ring 14, the positioning plate 15, the second positioning pin 16 and the jackscrew 18 are assembled on the base 12;
placing the turbine disk 1 on a base 12, performing circumferential positioning by using a first positioning pin 13, and performing axial positioning by using a positioning ring 14;
pressing the plane pressure bearing 9 of the assembly positioning rod 11 to the center part of the turbine disc 1, and assembling with the second positioning pin 16;
hooking the hook end of each draw hook 6 into a corresponding cooling hole on the front sealing disc 2;
the connecting ring 17 is sleeved on the periphery of the front shaft neck of the front sealing disc 2, and is assembled with each drag hook 6 to position each drag hook 6;
the pressing disc 8, the cushion block 10, the pulling disc 5 and the hydraulic cylinder 7 are assembled on the positioning rod 11, so that the pressing disc 8 is pressed on the end part of the front journal of the front sealing disc 2;
rotating the pull disc 5 to enable each big abdication hole to be aligned with the root of the corresponding pull hook 6, pressing down the corresponding pull hook 6, and clamping the root of each pull hook 6 into the corresponding countersunk head pull hole through rotation;
the dial 19 is assembled on the pull disc 5, so that a probe of the dial 19 contacts with the end surface of the mounting side of the front sealing disc 2, and the dial 19 is adjusted to be in a zero position;
the hydraulic cylinder 7 applies pressure to the pressure plate 8 to deform the front sealing plate 2;
after the fact that all front sealing disc lugs 4 enter the bottom to be in place through the intermittent parts among all turbine disc lugs 3 is judged through the indication of the dial indicators 19, the rotary jackscrews 18 are abutted against the corresponding protruding parts on the connecting ring 17, and the pull disc 5 and the front sealing disc 2 are pushed to rotate;
the position checking pins 20 are used for detecting the position calibration holes on the turbine disk 1 and the front sealing disk 2, and after judging that each front sealing disk lug 4 is aligned with the corresponding turbine disk lug 3, the pressure of the hydraulic cylinder 7 on the pressure disk 8 is released, so that each front sealing disk lug 4 is abutted against the corresponding turbine disk lug 3 from the inner side.
For the method for assembling the turbine disk of the aeroengine and the front sealing disk thereof disclosed in the foregoing embodiment, which is implemented with the turbine disk of the aeroengine and the front sealing disk assembly device thereof disclosed in the foregoing embodiment, the description is simpler, and specific relevant places can be referred to the relevant description of the turbine disk of the aeroengine and the front sealing disk assembly device thereof, and the technical effects thereof can also be referred to the technical effects of the relevant parts of the turbine disk of the aeroengine and the front sealing disk assembly device thereof, which are not repeated herein.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (6)
1. An aeroengine turbine disk and front seal disk assembly device thereof, which is characterized by comprising:
the pulling disc (5) is provided with a mounting hole at the center part and countersunk head pulling holes and large abdicating holes distributed along the circumferential direction at the edge part; each countersunk head pulling hole is correspondingly communicated with one big abdicating hole;
the hook end of each draw hook (6) is correspondingly hooked into one cooling hole of the front sealing disc (2), the root of each draw hook correspondingly passes through one large abdication hole and is blocked into the corresponding countersunk head draw hole; the annular folded edges on the front sealing disc (2) are clamped into annular bayonets on the turbine disc (1), and all the front sealing disc lugs (4) and all the turbine disc lugs (3) are distributed in a staggered manner;
the hydraulic cylinder (7) is in threaded connection with the mounting hole;
the pressure plate (8) is pressed at the end part of the front shaft neck of the front sealing disc (2), positioned with the end part of the front shaft neck of the front sealing disc (2) through a spigot, and positioned with the output end of the hydraulic cylinder (7) through the spigot;
the plane pressure bearing (9) is pressed at the center of the turbine disc (1), positioned with the spigot between the center of the turbine disc (1) and positioned with the pressure plate (8) through the spigot; the plane pressure bearing (9) is provided with a plurality of first positioning holes distributed along the circumferential direction;
the hydraulic cylinder (7) can apply pressure to the pressure plate (8), and simultaneously generates tension on the pull disc (5) to deform the front sealing disc (2), so that all front sealing disc lugs (4) enter the bottom through the intermittent parts among all turbine disc lugs (3), and further the pull disc (5) can be rotated to drive the front sealing disc (2) to rotate, so that all front sealing disc lugs (4) are aligned with corresponding turbine disc lugs (3), the pressure of the hydraulic cylinder (7) to the pressure plate (8) is released, and all front sealing disc lugs (4) are propped against the corresponding turbine disc lugs (3) from the inner side;
the cushion block (10) is positioned between the output end of the hydraulic cylinder (7) and the pressure plate (8) and positioned between the output end of the hydraulic cylinder (7) and the pressure plate (8) through a spigot; the hydraulic cylinder (7), the pressure plate (8) and the cushion block (10) are provided with through holes;
one end of the positioning rod (11) passes through the through holes on the hydraulic cylinder (7), the pressure plate (8) and the cushion block (10) and is connected to the plane pressure bearing (9); the base (12) is arranged at the bottom of the turbine disc (1);
a plurality of first positioning pins (13) connected to the turbine disk (1) and distributed in the circumferential direction; each first locating pin (13) is correspondingly inserted into one second locating hole on the turbine disc (1);
one end of the positioning ring (14) is connected to the base (12) through a pin, and the other end of the positioning ring is provided with a plurality of third positioning holes;
the positioning plate (15) is provided with a plurality of fourth positioning holes, is positioned at one end of the positioning ring (14) opposite to the base (12) and is positioned between one end of the positioning ring (14) opposite to the base (12) through a spigot;
and a plurality of second positioning pins (16), wherein each second positioning pin (16) correspondingly penetrates through one fourth positioning hole, one end of each second positioning pin is correspondingly inserted into one first positioning hole, and the other end of each second positioning pin is correspondingly inserted into one third positioning hole.
2. The turbine disk of an aircraft engine and its front seal disk assembly device according to claim 1,
the base (12) is provided with a plurality of supporting bulges;
the turbine disc of the aero-engine and the front sealing disc assembly device thereof further comprise:
the connecting ring (17) is sleeved on the periphery of the front shaft neck of the front sealing disc (2), and is provided with a plurality of perforations distributed along the circumferential direction and a plurality of protruding parts; each draw hook (6) correspondingly penetrates through one perforation, and the outer wall is provided with a stop bulge so as to support the connecting ring (17);
a plurality of jackscrews (18), each of which is screwed onto one of the support projections;
each jackscrew (18) can correspondingly abut against a protruding part on the connecting ring (17) through rotation, so that the pulling disc (5) and the front sealing disc (2) are pushed to rotate.
3. The turbine disk of an aircraft engine and its front seal disk assembly device according to claim 2, wherein,
further comprises:
and a plurality of dial indicators (19) connected to the pull disc (5), wherein the probes are in end surface contact with the mounting edge of the front sealing disc (2).
4. An aircraft engine turbine disk and front seal disk assembly device thereof as claimed in claim 3 wherein,
further comprises:
the position checking pin (20) is detachably connected to the pull disc (5), and can detect position calibration holes on the turbine disc (1) and the front sealing disc (2) when the position checking pin is detached.
5. The turbine disk of an aircraft engine and its front seal disk assembly device according to claim 4, wherein,
the pulling disc (5) and the pressing disc (8) are provided with a plurality of lifting lugs.
6. An aircraft engine turbine disk and a front sealing disk assembly method thereof are characterized by comprising the following steps:
the annular folded edges on the front sealing disc (2) are clamped into annular bayonets on the turbine disc (1), and the front sealing disc lugs (4) and the turbine disc lugs (3) are distributed in a staggered manner by rotation;
a first positioning pin (13), a positioning ring (14), a positioning plate (15), a second positioning pin (16) and a jackscrew (18) are assembled on a base (12);
placing the turbine disc (1) on a base (12), performing circumferential positioning by using a first positioning pin (13), and performing axial positioning by using a positioning ring (14);
pressing a plane pressure bearing (9) for assembling the positioning rod (11) to the center part of the turbine disc (1) and assembling with a second positioning pin (16);
hooking the hook end of each draw hook (6) into a corresponding cooling hole on the front sealing disc (2);
the connecting ring (17) is sleeved on the periphery of the front shaft neck of the front sealing disc (2), and is assembled with each drag hook (6) to position each drag hook (6);
the pressing disc (8), the cushion block (10), the pull disc (5) and the hydraulic cylinder (7) are assembled on the positioning rod (11), so that the pressing disc (8) is pressed on the end part of the front shaft neck of the front sealing disc (2);
rotating the pull disc (5) to enable each big abdication hole to be aligned with the root of the corresponding drag hook (6), pressing down the corresponding drag hook (6), and clamping the root of each drag hook (6) into the corresponding countersunk head pull hole through rotation;
assembling a dial indicator (19) on the pull disc (5), enabling a probe of the dial indicator (19) to be in contact with the end surface of the mounting edge of the front sealing disc (2), and adjusting the dial indicator (19) to be in a zero position;
the hydraulic cylinder (7) is used for applying pressure to the pressure plate (8) to deform the front sealing plate (2);
after the fact that all front sealing disc lugs (4) enter the bottom to be in place through the intermittent parts among all turbine disc lugs (3) is judged through the indication of the dial indicator (19), the rotary jackscrews (18) are abutted to the corresponding protruding parts on the connecting ring (17), and the pull disc (5) and the front sealing disc (2) are pushed to rotate;
position checking pins (20) are used for detecting position calibration holes on the turbine disc (1) and the front sealing disc (2), and after each front sealing disc lug (4) is judged to be aligned with the corresponding turbine disc lug (3), the pressure of the hydraulic cylinder (7) on the pressure disc (8) is released, so that each front sealing disc lug (4) is abutted against the corresponding turbine disc lug (3) from the inner side.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211741386.2A CN116000604B (en) | 2022-12-31 | 2022-12-31 | Turbine disc of aero-engine and front sealing disc assembly device and method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211741386.2A CN116000604B (en) | 2022-12-31 | 2022-12-31 | Turbine disc of aero-engine and front sealing disc assembly device and method thereof |
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| CN116000604A CN116000604A (en) | 2023-04-25 |
| CN116000604B true CN116000604B (en) | 2023-11-28 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117268309B (en) * | 2023-11-22 | 2024-04-05 | 四川川航航空发动机维修工程有限责任公司 | Automatic measurement device and measurement method for pin displacement of turbine disc of aeroengine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN207930351U (en) * | 2018-01-04 | 2018-10-02 | 鄂州富晶电子技术有限公司 | One kind exempting from seal modules vacuum fixture |
| CN214604104U (en) * | 2021-02-08 | 2021-11-05 | 中国航发商用航空发动机有限责任公司 | Sealed labyrinth disc decomposition tool |
| CN114151203A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Sealing ring connecting structure |
| CN114505803A (en) * | 2020-11-16 | 2022-05-17 | 中国航发商用航空发动机有限责任公司 | Comb fluted disc assembly fixture |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10689988B2 (en) * | 2014-06-12 | 2020-06-23 | Raytheon Technologies Corporation | Disk lug impingement for gas turbine engine airfoil |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN207930351U (en) * | 2018-01-04 | 2018-10-02 | 鄂州富晶电子技术有限公司 | One kind exempting from seal modules vacuum fixture |
| CN114505803A (en) * | 2020-11-16 | 2022-05-17 | 中国航发商用航空发动机有限责任公司 | Comb fluted disc assembly fixture |
| CN214604104U (en) * | 2021-02-08 | 2021-11-05 | 中国航发商用航空发动机有限责任公司 | Sealed labyrinth disc decomposition tool |
| CN114151203A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Sealing ring connecting structure |
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