CN112177692B - Assembling tool and assembling method for low-pressure turbine rotor - Google Patents
Assembling tool and assembling method for low-pressure turbine rotor Download PDFInfo
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- CN112177692B CN112177692B CN201910593936.2A CN201910593936A CN112177692B CN 112177692 B CN112177692 B CN 112177692B CN 201910593936 A CN201910593936 A CN 201910593936A CN 112177692 B CN112177692 B CN 112177692B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present disclosure relates to an assembly tool for a low pressure turbine rotor including a turbine disc assembly and a turbine shaft assembly, the assembly tool comprising: the first hoisting assembly is detachably connected to the first end, close to the high-pressure stage, of the turbine disc assembly; and a second lifting assembly removably connected to a second end of the turbine disc assembly proximate the low pressure stage; the first hoisting assembly and the second hoisting assembly or the turbine shaft assembly are connected to the turbine disc assembly together, so that the turbine disc assembly can turn over when being hoisted. Based on above-mentioned technical scheme, this disclosed embodiment can reduce low pressure turbine rotor's mounting height at least, improves the assembly convenience, shortens the butt joint time.
Description
Technical Field
The disclosure relates to the field of aircraft engines, in particular to an assembling tool and an assembling method for a low-pressure turbine rotor.
Background
The low-pressure turbine rotor is composed of a turbine shaft assembly and a turbine disc assembly, and the turbine shaft assembly and the turbine disc assembly are connected through short bolts of a fastening seam as shown in figure 1. In the conventional assembly process, the turbine shaft assembly is fixed on the vertical assembly frame, then the turbine disc assembly is placed on the hoisting assembly frame, and the turbine shaft assembly and the turbine disc assembly are connected with each other through the hoisting function of the hoisting assembly frame.
However, this assembly process has three drawbacks:
(1) The turbine shaft assembly has a large axial span (about 2500 mm) so that the height of the vertical assembly frame is high, and therefore, the assembly operation process between the turbine shaft assembly and the turbine shaft assembly can belong to ascending operation, ascending protection is required, and the assembly convenience is insufficient;
(2) The turbine shaft assembly and the turbine disc assembly are connected through a tight seam allowance, the seam allowance needs to be heated in the assembling process, and due to the fact that the vertical assembling convenience is insufficient and the operation process is too long, the temperature of the seam allowance is reduced when the turbine shaft assembly and the turbine disc assembly are attached, the thermal deformation amount of the seam allowance of the turbine shaft is insufficient, and the butt joint work cannot be completed;
(3) When the turbine disc assembly is assembled, the low-pressure stage is taken as a reference, so that the turbine rotor is in a posture with the low-pressure stage at the lower part and the high-pressure stage at the upper part; after the low-pressure turbine rotor is assembled, the low-pressure turbine rotor needs to be stored in a posture that the turbine shaft is parallel to the horizontal plane and sent to the subsequent step.
Therefore, before and after the assembling process, the low-pressure turbine rotor has different postures, and the conventional assembling process lacks adjusting steps and adjusting tools for the postures of the low-pressure turbine rotor, so that the whole assembling period of the aircraft engine is prolonged.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide an assembling tool and an assembling method for a low-pressure turbine rotor, which can reduce the installation height of the low-pressure turbine rotor, improve the assembly convenience, and shorten the docking time.
In one aspect of the present disclosure, there is provided an assembly tool for a low pressure turbine rotor including a turbine disk assembly and a turbine shaft assembly, the assembly tool comprising:
the first hoisting assembly is detachably connected to the first end, close to the high-pressure stage, of the turbine disc assembly; and
the second hoisting assembly is detachably connected to the second end, close to the low-pressure stage, of the turbine disc assembly;
the first hoisting assembly and the second hoisting assembly or the turbine shaft assembly are connected to the turbine disc assembly together, so that the turbine disc assembly can turn over when being hoisted.
In some embodiments, the assembly tool further comprises:
a first support base having a first support plane and a first cavity structure perpendicular to the first support plane, supportable at the first end by the first support plane; and
a second support seat having a second support plane and a second cavity structure perpendicular to the second support plane, supportable at the second end by the second support plane.
In some embodiments, when the first and second hoist assemblies are connected to the turbine disc assembly, a projection of the first cavity structure on the first support plane covers a projection of the first and second hoist assemblies on the first support plane;
when the first hoisting assembly and the turbine shaft assembly are connected to the turbine disc assembly, the projection of the second cavity structure on the second support plane covers the projection of the first hoisting assembly and the turbine shaft assembly on the second support plane.
In some embodiments, the turbine disk assembly comprises a plurality of first mounting through holes distributed along a circumference, the first hoisting assembly comprises a first mounting disk comprising:
at least three second mounting through-holes capable of being interconnected with a portion of the plurality of first mounting through-holes by first bolts; and
and at least three arc-shaped through holes which are positioned between the adjacent at least three second mounting through holes and correspond to the other part of the plurality of first mounting through holes in position.
In some embodiments, the second hoist assembly comprises a second mounting plate comprising:
at least three third mounting through holes capable of being interconnected with a portion of the plurality of first mounting through holes by a second bolt; and
at least three circular through holes corresponding in position to the at least three second mounting through holes;
when the first hoisting assembly and the second hoisting assembly are connected to the turbine disc assembly, the second bolts can penetrate through the at least three arc-shaped through holes, and the first bolts can penetrate through the at least three circular through holes.
In some embodiments, the assembly tool further comprises:
and the heights of the plurality of first adjusting sleeves are greater than the thickness of the first mounting disc, and the first adjusting sleeves are respectively sleeved on the outer sides of the studs of the second bolts when the first supporting seat and the second supporting seat are connected with the turbine disc assembly, and the heights of the plurality of adjusting sleeves are the same.
In some embodiments, the turbine shaft assembly includes a third mounting disk including thereon:
a fourth mounting through hole interconnectable with the first mounting through hole by a third bolt, and the third bolt is passable through the at least three arc-shaped through holes when the first lifting assembly and the turbine shaft assembly are coupled to the turbine disc assembly.
In some embodiments, the assembly tool further comprises:
and the heights of the second adjusting sleeves are greater than the thickness of the third mounting disc, the second adjusting sleeves are provided with cutting surfaces which can be limited by the third mounting disc, and are used for being sleeved outside the studs of the first bolt when the first supporting seat and the turbine shaft assembly are connected to the turbine shaft assembly, and the heights of the second adjusting sleeves are the same.
In some embodiments, the assembly tool further comprises:
the third hoisting assembly is detachably connected with one end of the turbine shaft assembly; and
a lifting lug rotatably connected to at least one of the first lifting assembly, the second lifting assembly and the third lifting assembly for connecting a lifting rope.
In some embodiments, the lifting lug connecting the first lifting assembly or the second lifting assembly comprises:
the annular boss is arranged at one end, far away from the lifting rope, of the lifting lug, and the relative position of the lifting rope and the turbine disc assembly can be limited by abutting against the first hoisting assembly or the second hoisting assembly when the lifting lug is lifted.
In another aspect of the present disclosure, there is provided a method of assembling a low pressure turbine rotor, comprising:
under the supporting action of the first supporting seat, assembling the turbine disc assembly in a posture that the low-pressure stage is arranged above and the high-pressure stage is arranged below;
after a first hoisting assembly and a second hoisting assembly are installed on the turbine disc assembly, hoisting the first hoisting assembly and the second hoisting assembly, overturning the turbine disc assembly to a posture that a low-pressure stage is on a lower stage and a high-pressure stage is on an upper stage, then detaching the second hoisting assembly, and placing the turbine disc assembly on a second supporting seat; and
and removing the first hoisting assembly, and then installing the turbine shaft assembly on the turbine disc assembly to form the low-pressure turbine rotor.
In some embodiments, the method of assembling further comprises:
after the low-pressure turbine rotor is formed, the first hoisting assembly is installed at the first end, the third hoisting assembly is installed at the turbine shaft assembly, the low-pressure turbine rotor is hoisted through the first hoisting assembly and the third hoisting assembly, the low-pressure turbine rotor is placed in a horizontal storage rack after being overturned to the axis direction which is parallel to the horizontal direction, and then the first hoisting assembly and the third hoisting assembly are dismantled.
In some embodiments, the step of mounting the first and second lifting assemblies to the turbine disc assembly comprises:
connecting the first hoisting assembly and the turbine disc assembly through a first bolt;
connecting the second hoisting assembly and the turbine disc assembly through a second bolt, so that the first bolt is positioned in the circular through hole on the second hoisting assembly, and the second bolt is positioned in the arc-shaped through hole on the first hoisting assembly; and
and a first adjusting sleeve is sleeved outside the first bolt.
In some embodiments, the step of mounting the turbine shaft assembly to the turbine disc assembly comprises:
connecting the turbine shaft assembly and the turbine disc assembly through a third bolt, and reserving the installation position of the first bolt;
connecting the first hoisting assembly and the turbine disc assembly through a first bolt, and enabling the third bolt to be located in an arc-shaped through hole in the first hoisting assembly; and
and a second adjusting sleeve is sleeved outside the first bolt.
In some embodiments, the turbine disk assembly is heated to a set temperature during installation of the turbine shaft assembly to the turbine disk assembly to form a low pressure turbine rotor.
Therefore, according to the embodiment of the disclosure, the installation height of the low-pressure turbine rotor can be at least reduced, the assembly convenience is improved, and the butt joint time is shortened.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description, serve to explain the principles of the disclosure.
The present disclosure may be more clearly understood from the following detailed description taken in conjunction with the accompanying drawings, in which:
FIG. 1 is a schematic view of a prior art mounting location for assembling a low pressure turbine rotor;
FIG. 2 is a schematic structural view of a turbine disk assembly according to some embodiments of the present disclosure carried in a first support saddle;
FIG. 3 is a cross-sectional angled structural schematic of a turbine disk assembly coupled to a first lifting assembly according to some embodiments of the present disclosure;
FIG. 4 is a structural schematic diagram from a top view of a state in which a turbine disk assembly and a first lifting assembly are connected according to some embodiments of the present disclosure;
FIG. 5 is a cross-sectional angled structural schematic view of a turbine disk assembly coupled to first and second lifting assemblies according to some embodiments of the present disclosure;
FIG. 6 is a structural schematic diagram from a top perspective of a turbine disk assembly coupled to a first and second lifting assembly according to some embodiments of the present disclosure;
FIG. 7 is a structural schematic diagram of a first state of a turbine disk assembly upset process according to some embodiments of the present disclosure;
FIG. 8 is a structural schematic diagram of a second state of a turbine disk assembly upset process according to some embodiments of the present disclosure;
FIG. 9 is a structural schematic diagram of a third state of a turbine disk assembly flipping process according to some embodiments of the present disclosure;
FIG. 10 is a schematic structural view of a turbine disk assembly carried in a second support seat state according to some embodiments of the present disclosure;
FIG. 11 is a structural schematic diagram of a turbine disk assembly and turbine shaft assembly in a connected state according to some embodiments of the present disclosure;
FIG. 12 is a schematic structural view of a turbine disk assembly coupled to a turbine shaft assembly and a first lifting assembly according to some embodiments of the present disclosure;
FIG. 13 is a cross-sectional angular structure schematic view of the connection of the turbine disk assembly with the turbine shaft assembly and the first hanger assembly according to some embodiments of the present disclosure;
FIG. 14 is a schematic view of a bottom view angle configuration of the connection of the turbine disk assembly to the turbine shaft assembly and the first hoist assembly in accordance with some embodiments of the present disclosure;
FIG. 15 is a top view angle configuration of the connection of the turbine disk assembly to the turbine shaft assembly and the first hanger assembly according to some embodiments of the present disclosure.
In the figure:
1. the turbine disc assembly 11, the first mounting through hole 2, the turbine shaft assembly 21, the third mounting disc and the fourth mounting through hole 211; 31. the first lifting assembly comprises 311, a first mounting disc, 311a, a second mounting through hole, 311b, an arc-shaped through hole, 32, a second lifting assembly, 321, a second mounting disc, 321a, a third mounting through hole, 33, a first supporting seat, 331, a first supporting plane, 332, a first cavity structure, 34, a second supporting seat, 341, a second supporting plane, 342, a second cavity structure, 351, a first adjusting sleeve, 352, a second adjusting sleeve, 361, a first bolt, 362, a second bolt, 363, a third bolt, 37, a third lifting assembly, 38, a lifting lug, 381 and an annular boss.
It should be understood that the dimensions of the various parts shown in the drawings are not drawn to scale. Further, the same or similar reference numerals denote the same or similar components.
Detailed Description
Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. The description of the exemplary embodiments is merely illustrative and is in no way intended to limit the disclosure, its application, or uses. The present disclosure may be embodied in many different forms and is not limited to the embodiments described herein. These embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that: the relative arrangement of parts and steps, the composition of materials, numerical expressions and numerical values set forth in these embodiments are to be construed as merely illustrative, and not as limitative, unless specifically stated otherwise.
The use of "first," "second," and similar terms in this disclosure is not intended to indicate any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element preceding the word covers the element listed after the word, and does not exclude the possibility that other elements are also covered. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.
In the present disclosure, when a specific device is described as being located between a first device and a second device, there may or may not be intervening devices between the specific device and the first device or the second device. When a particular device is described as being coupled to another device, it can be directly coupled to the other device without intervening devices or can be directly coupled to the other device with intervening devices.
All terms (including technical or scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs unless specifically defined otherwise. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate.
As shown in fig. 1, for a schematic view of an installation state of a low-pressure turbine rotor in the prior art, since an assembly standard of the turbine disc assembly 1 is a high-pressure stage, in the process of organizing the turbine disc assembly 1 and the turbine shaft assembly 2, the high-pressure stage of the turbine disc assembly 1 needs to be assembled with the turbine shaft assembly 2 downwards, so that a working height of an assembly operation is high. And the spigot at the connection needs to be heated to a set temperature during the connection of the turbine disc assembly 1 to the turbine shaft assembly 2, the higher mounting height makes the heating operation more difficult and precise temperature control more difficult.
Based on this, as shown in fig. 2 to 15:
in one aspect of the present disclosure, there is provided an assembly tool for a low pressure turbine rotor including a turbine disk assembly 1 and a turbine shaft assembly 2, the assembly tool comprising:
a first lifting assembly 31 detachably connected to a first end of the turbine disc assembly 1 near the high-pressure stage; and
the second hoisting assembly 32 is detachably connected to the second end, close to the low-pressure stage, of the turbine disc assembly 1;
the first hoisting assembly 31 and the second hoisting assembly 32 or the turbine shaft assembly 2 can be connected to the turbine disc assembly 1 together, so that the turbine disc assembly 1 can be overturned when being hoisted.
The first hoisting assembly 31 and the second hoisting assembly 32 can be respectively connected to two sides of the turbine disc assembly 1, and provide hoisting points which can be pulled by hoisting ropes, so that the turbine disc assembly 1 can be turned over when being hoisted, and the turbine disc assembly 1 alone or integrally assembled with the turbine shaft assembly 2 can be adjusted in posture so as to meet the position requirement of the turbine disc assembly 1 in the low-pressure turbine rotor machining process.
The turbine disk assembly 1 which can be turned over not only facilitates the installation process of the low-pressure turbine rotor, so that the turbine disk assembly 1 and the turbine shaft assembly 2 are installed at a lower height from each other, thereby avoiding high-altitude operation and enabling the temperature of the heating process to be more controllable, but also enables the requirements of the turbine disk assembly 1 or the low-pressure turbine rotor on a carrier or an installation platform to be lower, thereby simplifying the assembly process of the whole aeroengine.
As shown in fig. 2, 10 and 11, further, in order to support the turbine disk assembly 1 in different postures during the assembling process, in some embodiments, the assembling tool further includes:
a first support base 33 having a first support plane 331 and a first cavity structure 332 perpendicular to the first support plane 331, supportable at the first end by the first support plane 331; and
the second support seat 34 has a second support plane 341 and a second cavity structure 342 perpendicular to the second support plane 341, and can be supported at the second end by the second support plane 341.
Further, as shown in fig. 12, in order to facilitate the interconnection of the turbine shaft assembly 1 and the turbine shaft assembly 2, the first lifting assembly 31 and/or the second lifting assembly 32, in some embodiments, when the first lifting assembly 31 and the second lifting assembly 32 are connected to the turbine shaft assembly 1, the projection of the first cavity structure 332 on the first support plane 331 covers the projection of the first lifting assembly 31 and the second lifting assembly 32 on the first support plane 331;
when the first lifting assembly 31 and the turbine shaft assembly 2 are connected to the turbine disc assembly 1, the projection of the second cavity structure 342 on the second support plane 341 covers the projection of the first lifting assembly 31 and the turbine shaft assembly 2 on the second support plane 341.
The projection of the first cavity structure 332 onto the first support plane 331 and the projection of the second cavity structure 342 onto the second support plane 341 refer in particular to the projection of the contours of the first cavity structure 332 and the second cavity structure 342.
The projection of the first cavity structure 332 covers the projections of the first hoisting assembly 31 and the second hoisting assembly 32, so that the first hoisting assembly 31 or the second hoisting assembly 32 can freely shuttle from the first cavity structure 332 and can be connected with the turbine disc assembly 1 from two ends of the turbine disc assembly 1; correspondingly, the projection of the second cavity structure 342 covers the projections of the first hoisting assembly 31 and the turbine shaft assembly 2, so that the first hoisting assembly 31 or the second hoisting assembly 32 can freely shuttle from the first cavity structure 332 and can be connected with the turbine disc assembly 1 from two ends of the turbine disc assembly 1.
In addition, the first cavity structure 332 and the second cavity structure 342 with a larger projection range can also avoid structural damage of the turbine disc assembly 1 and the turbine shaft assembly 2 due to collision or friction during the process of connecting the first hoisting assembly 31, the second hoisting assembly 32 and/or the turbine shaft assembly 2 to the turbine disc assembly 1.
As shown in fig. 3 to 4, further, in order to achieve interconnection between the turbine disk assembly 1 and the first hoisting assembly 31, in some embodiments, the turbine disk assembly 1 includes a plurality of first mounting through holes 11 distributed along a circumference, the first hoisting assembly 31 includes a first mounting disk 311, and the first mounting disk 311 includes:
at least three second mounting through-holes 311a capable of being interconnected with a part of the plurality of first mounting through-holes 11 by first bolts 361; and
and at least three arc-shaped through holes 311b located between the adjacent at least three second mounting through holes 311a and positioned corresponding to another portion of the plurality of first mounting through holes 11.
Preferably, the number of the second mounting through holes 311a is four, and the second mounting through holes are uniformly distributed with each other, so as to ensure a stable connection degree between the turbine disc assembly 1 and the first hoisting assembly 31. The arc-shaped through hole 311b is disposed such that the first mounting through hole 11, which is not connected to the second connecting through hole, can be exposed out of the second mounting plate 321, so that the second hoisting assembly 32 or the turbine shaft assembly 2 and the first hoisting assembly 31 can be connected to the turbine plate assembly 1 at the same time.
As shown in fig. 5 to 6, further, in some embodiments, the second hoisting assembly 32 includes a second mounting plate 321, and the second mounting plate 321 includes:
at least three third mounting through-holes 321a capable of being interconnected with a portion of the plurality of first mounting through-holes 11 by second bolts 362; and
at least three circular through holes corresponding in position to the at least three second mounting through holes 311a;
when the first and second hoisting assemblies 31 and 32 are connected to the turbine disk assembly 1, the second bolts 362 can pass through the at least three arc-shaped through holes 311b, and the first bolts 361 can pass through the at least three circular through holes.
The number of the third mounting through holes 321a is preferably the same as that of the second mounting through holes 311a, so that the third mounting through holes 321a can be correspondingly and respectively disposed in the different arc-shaped through holes 311b, and thus the stress of the turbine disc assembly 1 is more uniform when the turbine disc assembly is connected by the first hoisting assembly 31 and the second hoisting assembly 32.
That is, when the number of the second mounting through holes 311a is four, the number of the third mounting through holes 321a is also preferably four. As shown in fig. 6, the second bolt 362 can pass through the at least three arc-shaped through holes 311b from a top view, and the first bolt 361 can pass through the circular through hole on the second mounting plate 321 from another side (a bottom view not shown), so that the first hoisting assembly 31 and the second hoisting assembly 32 can be simultaneously connected to the turbine disk assembly 1, and the first bolt 361 and the second bolt 362 can be twisted.
Further, as shown in fig. 6, limited by the size of the arc-shaped through hole 311b, in order to make the second bolt 362 at least partially exposed from the arc-shaped through hole 311b to facilitate the operation of the second bolt 362, in some embodiments, the assembling tool further includes:
a plurality of first adjustment sleeves 351, having a height greater than the thickness of the first mounting plate 311, for being respectively sleeved outside the studs of the second bolts 362 when the first support seat 33 and the second support seat 34 are connected to the turbine disk assembly 1, and having the same height.
As shown in fig. 11 to 15, further, in some embodiments, the turbine shaft assembly 2 includes a third mounting plate 21, and the third mounting plate 21 includes thereon:
a fourth mounting through hole 211 which is mutually connectable with the first mounting through hole 11 by a third bolt 363, and the third bolt 363 is penetrated through the at least three arc-shaped through holes 311b when the first lifting assembly 31 and the turbine shaft assembly 2 are connected to the turbine shaft assembly 1.
The connection between the fourth mounting through hole 211 and the first mounting through hole 11 is the connection between the turbine disc assembly 1 and the turbine shaft assembly 2, and therefore the fourth mounting through hole 211 corresponds to the first mounting through hole 11 and is a circle of mounting through holes circumferentially arranged so as to ensure the connection stability between the turbine disc assembly 1 and the turbine shaft assembly 2 under the high-speed rotation of the low-pressure turbine rotor.
On this basis, in order to realize that the first hoisting assembly 31 and the turbine shaft assembly 2 can be connected to the turbine disk assembly 1 at the same time, as shown in fig. 13 and 15, four first bolts 361 connect the second mounting through hole 311a and four first mounting through holes 11, and the remaining first mounting through holes 11 are connected to the fourth mounting through hole 211 through third bolts 363, at this time, the arc-shaped through holes 311b reserve mounting positions for the third bolts 363. In an assembly environment, the low-pressure turbine rotor does not need to rotate at a high speed, so that the mounting of fewer four third bolts 363 between one circle of the first mounting through hole 11 and one circle of the fourth mounting through holes 211 does not affect the assembly strength between the turbine shaft assembly 2 and the turbine disk assembly 1.
As shown in fig. 13, in order to expose the first bolt 361 at least partially to the third mounting plate 21 to facilitate the handling of the first bolt 361 and to prevent the first bolt 361 from following up during the tightening process, in some embodiments, the assembling tool further includes:
the second adjusting bushings 352 have a height greater than the thickness of the third mounting plate 21, have a cut surface that can be limited by the third mounting plate 21, and are used for being sleeved outside the studs of the first bolts 361 when the first supporting seat 33 and the turbine shaft assembly 2 are connected to the turbine shaft assembly 1, and the second adjusting bushings 352 have the same height.
As shown in fig. 7 to 9 and 11, in some embodiments, to realize the connection between the turbine shaft assembly 2, the first hoisting assembly 31, the second hoisting assembly 32 and the hoisting ropes, the assembling tool further comprises:
a third hoisting assembly 37 detachably connected to one end of the turbine shaft assembly 2; and
a lifting lug 38 rotatably connected to at least one of the first hoist assembly 31, the second hoist assembly 32 and the third hoist assembly 37 for connecting a lifting rope.
Further, as shown in fig. 7 to 9, in order to prevent the blade from being damaged by a lifting rope or a sling during the lifting process of the turbine disc assembly 1, in some embodiments, the lifting lug 38 connected to the first lifting assembly 31 or the second lifting assembly 32 includes:
an annular boss 381 disposed at an end of the lifting lug 38 remote from the lifting rope, capable of limiting the relative position of the lifting rope and the turbine disc assembly 1 by abutting against the first lifting assembly 31 or the second lifting assembly 32 when the lifting lug 38 is lifted.
As shown in fig. 2 to 15, in another aspect of the present disclosure, there is provided a method of assembling a low pressure turbine rotor, including:
assembling the turbine disk assembly 1 in a posture that the low-pressure stage is positioned above the high-pressure stage and below the high-pressure stage under the supporting action of the first supporting seat 33;
after the first hoisting assembly 31 and the second hoisting assembly 32 are installed on the turbine disc assembly 1, hoisting the first hoisting assembly 31 and the second hoisting assembly 32, turning the turbine disc assembly 1 to a posture that the low-pressure stage is on the lower stage and the high-pressure stage is on the upper stage, then detaching the second hoisting assembly 32, and placing the turbine disc assembly 1 on a second support seat 34;
the first hoisting assembly 31 is removed, and the turbine shaft assembly 2 is mounted on the turbine disc assembly 1 to form the low-pressure turbine rotor.
Through to the upset of the high-low pressure level of turbine dish subassembly 1 in vertical direction, under the prerequisite that does not influence turbine dish subassembly 1 assembly benchmark, reduced turbine dish subassembly 1 with the adverse effect that high altitude construction produced the security and the convenience of assembly work is avoided appearing to turbine shaft subassembly 2 between, thereby shortened the butt joint time, and made the assembling process of low pressure turbine rotor safe and reliable more.
In some embodiments, to facilitate subsequent processing steps of the low pressure turbine rotor, the method of assembling further comprises:
after the low-pressure turbine rotor is formed, the first hoisting assembly 31 is installed at the first end, the third hoisting assembly 37 is installed at the turbine shaft assembly 2, the low-pressure turbine rotor is hoisted through the first hoisting assembly 31 and the third hoisting assembly 37, the low-pressure turbine rotor is turned to the axis direction parallel to the horizontal direction and then placed in a horizontal storage rack, and then the first hoisting assembly 31 and the third hoisting assembly 37 are detached.
Further, as shown in fig. 3 to 6, in some embodiments, the step of mounting the first and second lifting assemblies 31 and 32 to the turbine disc assembly 1 includes:
the first hoisting assembly 31 and the turbine disc assembly 1 are connected through a first bolt 361;
connecting the second hoisting assembly 32 and the turbine disc assembly 1 by a second bolt 362, so that the first bolt 361 is positioned in the circular through hole on the second hoisting assembly 32, and the second bolt 362 is positioned in the arc-shaped through hole 311b on the first hoisting assembly 31; and
a first adjustment sleeve 351 is fitted around the first bolt 361.
Further, as shown in fig. 11-15, in some embodiments, the step of mounting the turbine shaft assembly 2 to the turbine disk assembly 1 includes:
connecting the turbine shaft assembly 2 and the turbine disk assembly 1 through a third bolt 363, and reserving an installation position of a first bolt 361;
the first hoisting assembly 31 and the turbine disc assembly 1 are connected through a first bolt 361, and the third bolt 363 is located in the arc-shaped through hole 311b on the first hoisting assembly 31; and
a second adjusting sleeve 352 is sleeved outside the first bolt 361.
Further, as shown in fig. 11, in some embodiments, the turbine disk assembly 1 is heated to a set temperature during the process of mounting the turbine shaft assembly 2 to the turbine disk assembly 1 to form a low pressure turbine rotor.
The set temperature is preferably 150 degrees celsius to ensure a tight seam connection between the turbine disc assembly 1 and the turbine shaft assembly 2.
The assembly method provided in the present application will be further explained with reference to the accompanying drawings:
as shown in fig. 2, the assembly of the turbine disc assembly 1 is completed on the first support seat 33;
as shown in fig. 3 and 4, the first hoist is mounted on the turbine disk assembly 1 through four sets of first bolts 361, and a first adjusting sleeve 351 is placed at the head of a stud of each first bolt 361;
as shown in fig. 5 and 6, the second hoisting assembly 32 is mounted on the turbine disk assembly 1 by the second bolt 362, a second adjusting sleeve 352 is placed at the head of the stud of the second bolt 362, and the second bolt 362 is located at the middle position of the annular through hole;
as shown in fig. 7, 8 and 9, the lifting lugs 38 are mounted on the first lifting assembly 31 and the second lifting assembly 32, and the turbine disc assembly 1 is turned 180 degrees by a double crane, so that the high-pressure stage disc faces upwards. The lifting lug 38 is provided with an annular boss 381 for limiting, so that the blade can be effectively prevented from being damaged by the inclination of the sling;
as shown in fig. 10, after the four first bolts 361 for fixing the first hoisting assembly 31 are removed, the first hoisting assembly 31 is separated, and the turbine disc assembly 1 is placed on the second support seat 34 by the second hoisting assembly 32;
as shown in fig. 11, after the four second bolts 362 for fixing the second hoisting assembly 32 are removed, the second hoisting assembly 32 is separated, the turbine shaft is vertically placed right above the turbine disc assembly 1 through the third hoisting assembly 37, the first mounting plate 311 (at the joint with the turbine disc assembly 1) on the turbine shaft assembly 2 is heated to 150 °, the third bolts 363 are aligned, the turbine shaft assembly 2 is mounted on the turbine disc assembly 1 through the third hoisting assembly 37, the third bolts 363 of the turbine shaft assembly 2 and the turbine disc assembly 1 are mounted, and four holes are uniformly distributed in the circumferential direction, and the third bolts 363 are not mounted for mounting the first hoisting assembly 31.
As shown in fig. 12 to 15, the first lifting assembly 31 is mounted on the turbine disc assembly 1 by four sets of the first bolts 361, and the second adjusting sleeves 352 are placed at the positions of the stud heads of the first bolts 361;
finally, after the low-pressure turbine rotor is turned to be in a horizontal state through a double crane, the low-pressure turbine rotor is placed on a horizontal storage rack, four first bolts 361 for fixing the first hoisting assembly 31 are removed, the first hoisting assembly 31 is separated, and the other four third bolts 363 of the turbine shaft assembly 2 and the turbine disc assembly 1 are installed.
Therefore, according to the embodiment of the disclosure, the installation height of the low-pressure turbine rotor can be at least reduced, the assembly convenience is improved, and the butt joint time is shortened.
In addition, according to the embodiment of the disclosure, the turbine shaft assembly 2 is hoisted from the first end by turning over the turbine disc assembly 1, so that the installation height of the low-pressure turbine rotor is reduced, and the butt joint time is shortened;
the first hoisting assembly 31 and the second hoisting assembly 32 at the first end and the second end of the turbine disc assembly 1 are prevented from interfering with each other through a special hole cutting mode: an annular groove is designed on the first hoisting assembly 31 to avoid the interference of the second bolt 362 of the second hoisting assembly 32 and the interference of the turbine shaft assembly 2 and the third bolt 363 of the turbine disk assembly 1, and four uniformly-distributed large holes are designed on the second hoisting assembly 32 to contain the interference of the first bolt 361 of the first hoisting assembly 31;
the independent first adjusting sleeve 351 and the independent second adjusting sleeve 352 are used for facilitating the tightening of the fasteners when the first hoisting assembly 31 and the second hoisting assembly 32 are installed, and effectively preventing the first bolt 361 of the first hoisting assembly 31 from following during the tightening process;
through design cross boss or annular boss 381 on lug 38 for at the hoist and mount in-process lug 38 with first hoist and mount subassembly 31 with second hoist and mount subassembly 32 all can form spacingly, thereby prevents that the blade is crowded to the hoist and mount slope.
Thus, various embodiments of the present disclosure have been described in detail. Some details well known in the art have not been described in order to avoid obscuring the concepts of the present disclosure. Those skilled in the art can now fully appreciate how to implement the teachings disclosed herein, in view of the foregoing description.
Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the foregoing examples are for purposes of illustration only and are not intended to limit the scope of the present disclosure. It will be understood by those skilled in the art that various changes may be made in the above embodiments or equivalents may be substituted for elements thereof without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.
Claims (14)
1. An assembly tool for a low-pressure turbine rotor including a turbine disk assembly and a turbine shaft assembly, the assembly tool comprising:
the first hoisting assembly is detachably connected to the first end, close to the high-pressure stage, of the turbine disc assembly;
the second hoisting assembly is detachably connected to the second end, close to the low-pressure stage, of the turbine disc assembly;
a first support base having a first support plane and a first cavity structure perpendicular to the first support plane, supportable at the first end by the first support plane; and
a second support base having a second support plane and a second cavity structure perpendicular to the second support plane, supportable at the second end by the second support plane;
the first hoisting assembly and the second hoisting assembly or the turbine shaft assembly are jointly connected to the turbine disc assembly, so that the turbine disc assembly can turn over when being hoisted.
2. The assembly tool of claim 1, wherein a projection of the first cavity structure onto the first support plane covers a projection of the first and second hoist assemblies onto the first support plane when the first and second hoist assemblies are connected to the turbine disc assembly;
when the first hoisting assembly and the turbine shaft assembly are connected to the turbine disc assembly, the projection of the second cavity structure on the second support plane covers the projection of the first hoisting assembly and the turbine shaft assembly on the second support plane.
3. The assembly tool of claim 1, wherein the turbine disk assembly includes a plurality of first mounting through-holes distributed circumferentially, the first lifting assembly including a first mounting disk comprising:
at least three second mounting through-holes capable of being interconnected with a portion of the plurality of first mounting through-holes by first bolts; and
and at least three arc-shaped through holes which are positioned between the adjacent at least three second mounting through holes and correspond to the other part of the plurality of first mounting through holes in position.
4. The assembly tool of claim 3, wherein the second hoist assembly comprises a second mounting plate, the second mounting plate comprising:
at least three third mounting through holes capable of being interconnected with a portion of the plurality of first mounting through holes by a second bolt; and
at least three circular through holes corresponding in position to the at least three second mounting through holes;
when the first hoisting assembly and the second hoisting assembly are connected to the turbine disc assembly, the second bolts can pass through the at least three arc-shaped through holes, and the first bolts can pass through the at least three circular through holes.
5. The assembly tool of claim 4, further comprising:
and the heights of the first adjusting sleeves are greater than the thickness of the first mounting disc, the first supporting seat and the second supporting seat are respectively sleeved on the outer sides of the studs of the second bolts when the turbine disc assembly is connected with the turbine disc assembly, and the heights of the first adjusting sleeves are the same.
6. The assembly tool of claim 3, wherein the turbine shaft assembly includes a third mounting disk including thereon:
a fourth mounting through hole interconnectable with the first mounting through hole by a third bolt, and the third bolt is passable through the at least three arc-shaped through holes when the first lifting assembly and the turbine shaft assembly are coupled to the turbine disc assembly.
7. The assembly tool of claim 6, further comprising:
the height of the second adjusting sleeves is larger than the thickness of the third mounting disc, the second adjusting sleeves are provided with tangent planes which can be limited by the third mounting disc, the second adjusting sleeves are used for being sleeved outside studs of the first bolts when the first supporting seat and the turbine shaft assembly are connected to the turbine shaft assembly, and the heights of the second adjusting sleeves are the same.
8. The assembly tool of claim 1, further comprising:
the third hoisting assembly is detachably connected with one end of the turbine shaft assembly; and
a lifting lug rotatably connected to at least one of the first lifting assembly, the second lifting assembly and the third lifting assembly for connecting a lifting rope.
9. The assembly tool of claim 8, wherein the lifting lug connected to the first or second lifting assembly comprises:
the annular boss is arranged at one end, far away from the lifting rope, of the lifting lug, and the relative position of the lifting rope and the turbine disc assembly can be limited by abutting against the first hoisting assembly or the second hoisting assembly when the lifting lug is lifted.
10. A method of assembling a low pressure turbine rotor, comprising:
assembling the turbine disc assembly in a posture that the low-pressure stage is positioned above the high-pressure stage and the low-pressure stage is positioned below the high-pressure stage under the supporting action of the first supporting seat;
after a first hoisting assembly and a second hoisting assembly are installed on the turbine disc assembly, hoisting the first hoisting assembly and the second hoisting assembly, overturning the turbine disc assembly to a posture that a low-pressure stage is on a lower stage and a high-pressure stage is on an upper stage, then detaching the second hoisting assembly, and placing the turbine disc assembly on a second supporting seat; and
and removing the first hoisting assembly, and then installing a turbine shaft assembly on the turbine disc assembly to form the low-pressure turbine rotor.
11. The method of assembling of claim 10, further comprising:
after the low-pressure turbine rotor is formed, the first hoisting assembly is installed at the first end, close to a high-pressure stage, of the turbine disc assembly, the third hoisting assembly is installed on the turbine shaft assembly, the low-pressure turbine rotor is hoisted through the first hoisting assembly and the third hoisting assembly, the low-pressure turbine rotor is placed on a horizontal storage rack after being overturned to the direction of the axis of the low-pressure turbine rotor, the axis of the low-pressure turbine rotor is parallel to the horizontal direction, and then the first hoisting assembly and the third hoisting assembly are dismounted.
12. The method of assembling of claim 10, wherein the step of mounting the first and second lifting assemblies to the turbine disc assembly comprises:
connecting the first hoisting assembly and the turbine disc assembly through a first bolt;
connecting the second hoisting assembly and the turbine disc assembly through a second bolt, enabling the first bolt to be located in the circular through hole in the second hoisting assembly, and enabling the second bolt to be located in the arc-shaped through hole in the first hoisting assembly; and
and a first adjusting sleeve is sleeved outside the first bolt.
13. The method of assembling of claim 10, wherein the step of mounting the turbine shaft assembly to the turbine disc assembly comprises:
connecting the turbine shaft assembly and the turbine disc assembly through a third bolt, and reserving the installation position of the first bolt;
connecting the first hoisting assembly and the turbine disc assembly through a first bolt, and enabling the third bolt to be located in an arc-shaped through hole in the first hoisting assembly; and
and a second adjusting sleeve is sleeved outside the first bolt.
14. The method of assembling of claim 10, wherein the turbine disk assembly is heated to a set temperature during installation of the turbine shaft assembly to the turbine disk assembly to form a low pressure turbine rotor.
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| CN201910593936.2A CN112177692B (en) | 2019-07-03 | 2019-07-03 | Assembling tool and assembling method for low-pressure turbine rotor |
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| CN201910593936.2A CN112177692B (en) | 2019-07-03 | 2019-07-03 | Assembling tool and assembling method for low-pressure turbine rotor |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4567649A (en) * | 1983-05-04 | 1986-02-04 | General Electric Company | System for heating, disassembly, handling and reassembly of a turbine rotor |
| CN204195185U (en) * | 2014-11-06 | 2015-03-11 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aero-engine low-pressure turbine assembling detection device |
| CN104929779A (en) * | 2015-04-30 | 2015-09-23 | 中国科学院工程热物理研究所 | Turbine disk connecting structure and gas turbine engine with same |
| WO2015158513A1 (en) * | 2014-04-15 | 2015-10-22 | Siemens Aktiengesellschaft | Method for assembling and/or disassembling a rotor section of a turbomachine, associated assembly device and rotor disc |
| CN106429827A (en) * | 2016-11-23 | 2017-02-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotor overturning and hoisting device |
| CN108049921A (en) * | 2017-11-27 | 2018-05-18 | 大连理工大学 | A kind of assembly method of aero-engine low-pressure turbine shaft-disk component |
| CN109093378A (en) * | 2017-06-20 | 2018-12-28 | 中国航发商用航空发动机有限责任公司 | A kind of low-pressure turbine installation equipment and its application method |
| CN109339869A (en) * | 2018-11-30 | 2019-02-15 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine High Pressure Turbine Rotor centring means and its application method |
-
2019
- 2019-07-03 CN CN201910593936.2A patent/CN112177692B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4567649A (en) * | 1983-05-04 | 1986-02-04 | General Electric Company | System for heating, disassembly, handling and reassembly of a turbine rotor |
| WO2015158513A1 (en) * | 2014-04-15 | 2015-10-22 | Siemens Aktiengesellschaft | Method for assembling and/or disassembling a rotor section of a turbomachine, associated assembly device and rotor disc |
| CN204195185U (en) * | 2014-11-06 | 2015-03-11 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aero-engine low-pressure turbine assembling detection device |
| CN104929779A (en) * | 2015-04-30 | 2015-09-23 | 中国科学院工程热物理研究所 | Turbine disk connecting structure and gas turbine engine with same |
| CN106429827A (en) * | 2016-11-23 | 2017-02-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotor overturning and hoisting device |
| CN109093378A (en) * | 2017-06-20 | 2018-12-28 | 中国航发商用航空发动机有限责任公司 | A kind of low-pressure turbine installation equipment and its application method |
| CN108049921A (en) * | 2017-11-27 | 2018-05-18 | 大连理工大学 | A kind of assembly method of aero-engine low-pressure turbine shaft-disk component |
| CN109339869A (en) * | 2018-11-30 | 2019-02-15 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine High Pressure Turbine Rotor centring means and its application method |
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