CN116857016A - Turbine shaft end locking assembly and gas turbine engine - Google Patents
Turbine shaft end locking assembly and gas turbine engine Download PDFInfo
- Publication number
- CN116857016A CN116857016A CN202210316754.2A CN202210316754A CN116857016A CN 116857016 A CN116857016 A CN 116857016A CN 202210316754 A CN202210316754 A CN 202210316754A CN 116857016 A CN116857016 A CN 116857016A
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- Prior art keywords
- turbine shaft
- locking
- shaft end
- locking assembly
- rotation
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 210000000078 claw Anatomy 0.000 claims abstract description 36
- 206010061258 Joint lock Diseases 0.000 claims abstract description 20
- 230000002093 peripheral effect Effects 0.000 claims description 7
- 238000007789 sealing Methods 0.000 claims description 7
- 230000006835 compression Effects 0.000 description 9
- 238000007906 compression Methods 0.000 description 9
- 210000004907 gland Anatomy 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- 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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
Abstract
The application aims to provide a turbine shaft end locking assembly and a gas turbine engine, wherein the turbine shaft end locking assembly comprises an external thread part and an internal thread part which are respectively arranged at the turbine shaft end, a first locking piece, a second locking piece and a combined lock ring. The external thread part and the internal thread part have opposite thread directions, the first locking piece and the second locking piece are respectively in threaded connection with the external thread part and the internal thread part, the first locking piece is provided with a first rotation preventing groove, the second locking piece is provided with a second rotation preventing groove, and the combined locking ring is provided with an inner claw and an outer claw; wherein, be formed with the annular space between first retaining member and second retaining member, the joint lock collar sets up in the annular space after, and interior clamping jaw is connected in the second prevents changeing the inslot, and outer clamping jaw is connected in the first groove of preventing changeing. The shaft end locking assembly of the turbine shaft is convenient for locking shaft end parts, and meanwhile processing and assembling cost can be saved.
Description
Technical Field
The application relates to the field of aeroengines, in particular to a turbine shaft end locking assembly and a gas turbine engine.
Background
The turbine shaft is supported by a bearing, and the bearing is used as a main supporting part of the engine rotor, so that the anti-loosening measure must be considered in design. Fig. 1 shows a perspective view of an existing turbine shaft end, and fig. 2 shows a sectional view of an existing turbine shaft end. The figure shows turbine shaft 91, bearing 92, outer gland nut 93, outer nut lock ring 94, sealing runway 95, interior gland nut 96, interior nut lock ring 97 and retaining ring 98, in order to realize that the back fulcrum bearing safety operation is guaranteed to the connection reliability, all be equipped with on outer gland nut 93, turbine shaft 91 and interior gland nut 96 and evenly cloth anti-rotation groove 900, be equipped with inside and outside jack catch on the outer nut lock ring 94, jack catch on the outer nut lock ring 94 is located outer gland nut anti-rotation groove 900 respectively and the anti-rotation groove 900 on the turbine shaft 91. The inner compression nut 96 is also locked in a similar manner to the outer compression nut 94.
The inventor finds that by adopting the anti-loosening measure, the anti-loosening of the compression nut is effectively realized, but the structure is complicated, an anti-rotation groove is required to be arranged on the turbine shaft, the end face of the turbine shaft is required to be higher than the rear end faces of the inner compression nut and the outer compression nut by additionally arranging the anti-rotation groove, and the length of the turbine shaft is required to be increased to meet the locking requirement of the inner nut and the outer nut. The rear end of the turbine shaft is required to be provided with an anti-rotation groove, the axial length is increased, the turbine shaft is made of high-temperature alloy and difficult to process, the processing period is long, the outline size of the turbine shaft is large, the anti-rotation groove is in an irregular shape, and the processing and positioning difficulty of the anti-rotation groove is high.
Disclosure of Invention
The application aims to provide a turbine shaft end locking assembly which is convenient for locking shaft end parts and can save processing and assembly costs.
The shaft end locking assembly of the turbine shaft for locking the bearing and the sealing track at the shaft end of the turbine shaft respectively comprises:
an external thread portion provided on an outer peripheral side of the shaft end of the turbine shaft;
an internal thread portion provided on an inner peripheral side of an axial end of the turbine shaft, the external thread portion and the internal thread portion having opposite thread directions;
the first locking piece is in threaded connection with the external thread part and is provided with a first anti-rotation groove, the bearing is pressed on the turbine shaft by the first locking piece in a threaded connection state, and at least one part of the first anti-rotation groove is higher than the end face of the shaft end of the turbine shaft;
the second locking piece is in threaded connection with the internal thread part and is provided with a second anti-rotation groove, the second locking piece presses the sealing runway in the turbine shaft in a threaded connection state, and at least one part of the second anti-rotation groove is higher than the end face of the shaft end of the turbine shaft; and
the combined lock ring is provided with an inner claw and an outer claw;
the first locking piece and the second locking piece are connected through the inner clamping claw and the outer clamping claw, an annular space is formed between the first locking piece and the second locking piece, the combined locking ring is arranged in the annular space, the inner clamping claw is connected in the second anti-rotation groove, and the outer clamping claw is connected in the first anti-rotation groove.
In one or more embodiments, the first anti-rotation slot is a plurality and/or the second anti-rotation slot is two or more.
In one or more embodiments, the number of the first anti-rotation grooves and the second anti-rotation grooves is an even number, the first anti-rotation grooves are uniformly distributed on the first locking member, and the second anti-rotation grooves are uniformly distributed on the second locking member.
In one or more embodiments, in the installed state, the centroid of the combination lock collar is located on the axis of the turbine shaft.
In one or more embodiments, the inner claws and the outer claws are respectively even in number, the inner claws are uniformly distributed along the inner circumference of the combined lock ring, and the outer claws are uniformly distributed along the outer circumference of the combined lock ring.
In one or more embodiments, the inner claws are a pair arranged at the inner periphery of the combined lock ring, the outer claws are a pair arranged at the outer periphery of the combined lock ring, and the inner claws and the outer claws are distributed in a staggered manner along the circumferential direction of the combined lock ring.
In one or more embodiments, the inner circumference of the first locking member and/or the outer circumference of the second locking member is provided with a mounting groove, and the turbine shaft end locking assembly further comprises a retainer ring, wherein the retainer ring is arranged in the mounting groove and limits the joint lock ring from falling out of the annular space along the axial direction of the turbine shaft.
In one or more embodiments, an adjustment pad is disposed between the retainer ring and the combination lock collar.
In one or more embodiments, the retainer ring is a circlip.
It is another object of the present application to provide a gas turbine engine comprising a turbine shaft end locking assembly as described above to lock the turbine shaft end member.
The gain effect of the application is as follows:
the mode that traditional locking components are provided with anti-rotation grooves at the shaft ends of the turbine shafts can be canceled through the shaft end locking components of the turbine shafts, so that the length of the turbine shafts is reduced, the processing difficulty of the turbine shafts is reduced, and the locking difficulty of shaft end parts of the turbine shafts is simplified. Meanwhile, compared with the traditional locking assembly, the locking assembly needs to adopt a pair of lock rings to prevent the inner and outer compression nuts from loosening respectively, and the turbine shaft end locking assembly can prevent the inner and outer locking pieces from loosening respectively only by adopting one combined lock ring, so that the number of parts is reduced, and the cost is further saved.
The foregoing description is only an overview of the present application, and is intended to be implemented in accordance with the teachings of the present application in order that the same may be more clearly understood and to make the same and other objects, features and advantages of the present application more readily apparent.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the application. Also, like reference numerals are used to designate like parts throughout the accompanying drawings. In the drawings:
FIG. 1 illustrates a schematic perspective view of a prior art turbine shaft end;
FIG. 2 illustrates a schematic cross-sectional view of a prior art turbine shaft end;
FIG. 3 illustrates a schematic view, in semi-section, of a turbine shaft end locking assembly in accordance with some embodiments of the application;
FIG. 4 illustrates a perspective view of a turbine shaft end locking assembly according to some embodiments of the present application;
FIG. 5 illustrates a schematic top view of a turbine shaft end locking assembly in accordance with some embodiments of the application;
FIG. 6 illustrates an exploded view of a turbine shaft end locking assembly according to some embodiments of the application.
Detailed Description
Embodiments of the technical scheme of the present application will be described in detail below with reference to the accompanying drawings. The following examples are only for more clearly illustrating the technical aspects of the present application, and thus are merely examples, and are not intended to limit the scope of the present application.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application; the terms "comprising" and "having" and any variations thereof in the description of the application and the claims and the description of the drawings above are intended to cover a non-exclusive inclusion.
In order to solve the problems of high processing difficulty, high cost and the like of the existing turbine shaft end locking assembly, the application provides a turbine shaft end locking assembly with a new configuration according to some embodiments. Referring to fig. 3-6, fig. 3 illustrates a schematic view of a turbine shaft end locking assembly in semi-section according to some embodiments of the present application, fig. 4 illustrates a schematic perspective view of a turbine shaft end locking assembly in accordance with some embodiments of the present application, fig. 5 illustrates a schematic top view of a turbine shaft end locking assembly in accordance with some embodiments of the present application, and fig. 6 illustrates an exploded schematic view of a turbine shaft end locking assembly in accordance with some embodiments of the present application.
It is to be understood that one or more embodiments as described below employ a reference number system that is independent of the background art.
The turbine shaft end locking assembly locks the bearing 2 and the sealing track 3 at the end part of the turbine shaft 1 respectively, and comprises an external thread part arranged on the outer peripheral side 10 of the shaft end of the turbine shaft 1 and an internal thread part arranged on the inner peripheral side 11 of the shaft end of the turbine shaft 1. The external thread part on the outer circumference side 10 of the turbine shaft and the internal thread part on the inner circumference side 11 of the turbine shaft have opposite thread directions, and the external thread part and the internal thread part are arranged in positive and negative teeth. That is, when the external thread portion is a left-handed thread, the internal thread portion is a right-handed thread, and similarly, when the external thread portion is a right-handed thread, the internal thread portion is a left-handed thread. The arrangement is such that when threaded connection with the male and female threaded portions is required, respectively, the tightening is required in the opposite direction.
The turbine shaft end locking assembly further comprises a first locking piece 4, a second locking piece 5 and a combined locking ring 6. The first locking member 4 is threadably connected to the outer thread portion of the turbine shaft outer circumferential side 10, and has a first rotation preventing groove 40, and in the threaded connection state, the first locking member 4 presses the bearing 2 against the turbine shaft 1, and at least a part of the first rotation preventing groove 40 is higher than the end face 12 of the shaft end of the turbine shaft 1. The second locking member 5 is threadably connected to the female screw portion located on the turbine shaft inner peripheral side 11 and has a second rotation preventing groove 50, and in the threaded connection state, the second locking member 5 presses the seal race 3 into the turbine shaft 1, and at least a part of the second rotation preventing groove 50 is higher than the end face 12 of the turbine shaft end. The combination lock collar 6 has an inner jaw 61 and an outer jaw 62.
Wherein, an annular space 13 is formed between the first locking member 4 and the second locking member 5, and at least a portion of the first anti-rotation groove 40 and at least a portion of the second anti-rotation groove 50 are respectively higher than the end face 12 of the turbine shaft end, so that the annular space 13 is respectively communicated with the first anti-rotation groove 40 and the second anti-rotation groove 50, as shown in fig. 3 and fig. 4, in the locked state, the combined locking ring 6 is disposed in the annular space 13, the inner clamping claw 61 is connected in the second anti-rotation groove 50, and the outer clamping claw 62 is connected in the first anti-rotation groove 40. Wherein the inner pawl 61 is capable of cooperating with the second anti-rotation groove 50 to limit the relative rotation between the second locking member 5 and the associated locking collar 6, and the outer pawl 62 is capable of cooperating with the first anti-rotation groove 40 to limit the relative rotation between the first locking member 4 and the associated locking collar 6.
Since the external thread portion on the outer circumferential side 10 of the turbine shaft and the internal thread portion on the inner circumferential side 11 of the turbine shaft have opposite thread directions, the first locking member 4 and the second locking member 5 are screwed on the turbine shaft 1 in opposite thread directions, that is, if the first locking member 4 is locked counterclockwise, the second locking member 5 is locked clockwise, and vice versa. After the first locking member 4 and the second locking member 5 are locked respectively, the locking relevance of the first locking member 4 and the second locking member 5 is established through the combined locking ring 6, and the combined locking ring 6 follows the first locking member 4 to have a rotating trend and pushes the second locking member 5 to rotate towards the screwing direction when the first locking member 4 is loosened, and is blocked by the axial direction of the sealing runway 3, so that the second locking member 5 has no axial movement space and cannot rotate, and the combined locking of the inner locking member and the outer locking member is realized. On the contrary, when the second locking member 5 is loosened, the combined locking ring 6 follows the second locking member 5 to have a rotating trend, so that the first locking member 4 is pushed to rotate towards the screwing direction, and is blocked by the axial direction of the bearing 2, the first locking member 4 also has no axial movement space and cannot rotate, and the combined locking of the inner locking member and the outer locking member is realized.
The mode that traditional locking components are provided with anti-rotation grooves at the shaft ends of the turbine shafts can be canceled through the shaft end locking component of the turbine shafts, so that the length of the turbine shafts 1 is reduced, the processing difficulty of the turbine shafts 1 is reduced, and the locking difficulty of shaft end parts of the turbine shafts 1 is simplified. Meanwhile, compared with the traditional locking assembly, the locking assembly needs to adopt a mode that a pair of lock rings are used for locking the inner and outer compression nuts respectively, the locking assembly for the shaft end of the turbine shaft can meet the locking of the inner and outer locking pieces respectively only by adopting one combined lock ring 6, the number of parts is reduced, and further cost is saved.
In the description of embodiments of the present application, the technical terms "first," "second," and the like are used merely to distinguish between different objects and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated, a particular order or a primary or secondary relationship.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly appreciate that the embodiments described herein may be combined with other embodiments.
According to some embodiments of the present application, the first anti-rotation groove 40 and/or the second anti-rotation groove 50 are two or more, and by providing two or more anti-rotation grooves, the anti-rotation grooves are convenient to cooperate with the combined lock ring 6 during assembly, and meanwhile, the multi-rotation grooves can also be used as a force transmission part for connecting the first locking member 4 and/or the second locking member 5 with a tightening wrench.
In the description of the embodiments of the present application, the term "and/or" is merely an association relationship describing an association object, and indicates that three relationships may exist, for example, a and/or B may indicate: a exists alone, A and B exist together, and B exists alone. In addition, the character "/" herein generally indicates that the front and rear associated objects are an "or" relationship.
According to some embodiments of the present application, the number of the first anti-rotation slots 40 and the second anti-rotation slots 50 is an even number, the first anti-rotation slots 40 are uniformly arranged on the first locking member 4, and the second anti-rotation slots 50 are uniformly arranged on the second locking member 5. The first anti-rotation grooves 40 and the second anti-rotation grooves 50 which are even in number and uniformly distributed can ensure the uniformity of mass distribution, so that unbalance of the rotor is not introduced, and the difficulty of dynamic balance of the subsequent rotor is reduced.
According to some embodiments of the present application, in the installed state, the centroid of the joint lock ring 6 is located on the axis of the turbine shaft 1, so that in the locked state, the joint lock ring 6 is arranged without introducing the unbalance amount of the rotor, and the difficulty of the dynamic balance of the subsequent rotor is reduced.
According to some embodiments of the present application, the number of the inner claws 61 and the number of the outer claws 62 are respectively even, and the inner claws 61 are uniformly distributed along the inner circumference of the joint lock ring 6, and the outer claws 62 are uniformly distributed along the outer circumference of the joint lock ring, so that the symmetry of the shape of the joint lock ring 6 can be ensured, the uniformity of mass distribution can be ensured, and the joint lock ring 6 can be arranged in a locked state without introducing unbalance of the rotor, thereby reducing the difficulty of dynamic balance of the subsequent rotor.
Further, according to some embodiments of the present application, the inner claws 61 are a pair disposed at the inner periphery of the joint lock ring 6, the outer claws 62 are a pair disposed at the outer periphery of the joint lock ring 6, and the inner claws 61 and the outer claws 62 are staggered along the circumferential direction of the joint lock ring, so as to ensure the symmetry of the shape of the joint lock ring 6.
According to some embodiments of the present application, the inner circumference of the first locking member 4 and/or the outer circumference of the second locking member 5 are provided with a mounting groove 40, and the shaft end locking assembly of the turbine shaft 1 further comprises a retainer ring 7, wherein the retainer ring 7 is arranged in the mounting groove 40, and limits the joint lock ring 6 from exiting the annular space along the axial direction of the turbine shaft.
In a specific embodiment, the mounting groove 40 is formed on the inner periphery of the first locking member 4, so that when the engine works, the retainer ring 7 assembled in the mounting groove 40 rotates at a high speed, and under the action of centrifugal force, the retainer ring 7 expands outwards, and the direction of the retainer ring is consistent with that of the mounting groove 40, so that the joint lock ring 6 can be effectively prevented from falling out, and the running safety of the rotor can be ensured.
In other embodiments than those shown in the figures, the joint lock ring 6 may also be directly engaged in the first anti-rotation groove 40 and the second anti-rotation groove 50 by a clamping groove or the like, so as to prevent the joint lock ring from being separated from the turbine shaft in the axial direction.
According to some embodiments of the application, the retainer ring 7 is a circlip, which can be elastically deformed to snap into the mounting groove 40 when mounted. In other suitable embodiments, the retainer 7 may be a retainer structure having a notch, where the outer diameter of the retainer 7 may be changed by applying a force to the notch, so as to be able to be snapped into the mounting groove 40.
According to some embodiments of the application, an adjusting pad 8 is arranged between the retainer ring 7 and the combined lock ring 6, and in order to reduce the influence of part processing and the influence of thermal deformation on the shape of the part when the engine works, the adjusting pad 8 is arranged between the retainer ring 7 and the combined lock ring 6, and the adjusting pads 8 with different thicknesses can be selected according to the actual installation size of each part, so that the installation compactness among the combined lock ring 6, the adjusting pad 8 and the retainer ring 7 is met, and only small axial movement exists among the three, thereby avoiding the risk of disengagement.
According to some embodiments of the application, the first locking member 4 and the second locking member 5 are compression threads, the compression nut is regular in shape, the outline is smaller than the turbine shaft, the positioning is convenient and fast, the processing difficulty is small, the processing of anti-rotation features on the turbine shaft is effectively avoided, and therefore the processing difficulty, period and cost of the turbine shaft are reduced.
During assembly, the anti-rotation groove angles of the first locking member 4 and the second locking member 5 are firstly in a specified tightening torque range so as to meet the installation requirement of the combined lock ring 6, specifically, the second locking member 5 can be firstly installed to be in the specified tightening torque range, and then the external thread part is further processed according to the jaw position of the combined lock ring 6, so that the jaw of the combined lock ring 6 can be clamped into the first anti-rotation groove 40 when the first locking member 4 is in the specified tightening torque range.
Subsequently, the combination lock collar 6 is simultaneously installed into the first anti-rotation groove 40 and the second anti-rotation groove 50, and the adjustment pad 8 is installed.
Finally, the check ring 7 is installed, so that the joint lock ring 6, the adjusting pad 8 and the check ring 7 are compactly installed.
In another aspect, according to some embodiments of the present application, there is also provided a gas turbine engine that employs the turbine shaft end locking assembly described in one or more of the embodiments described above to lock the turbine shaft end member.
In the description of the embodiments of the present application, the positional or positional relationship indicated by the technical terms "center", "up", "down", "front", "rear", "left", "right", "inner", "outer", "clockwise", "counterclockwise", "axial", "circumferential", etc. are based on the positional or positional relationship of the connection members in the connected state, are merely for convenience of describing the embodiments of the present application and for simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus are not to be construed as limiting the embodiments of the present application.
In the description of the embodiments of the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured" and the like should be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally formed; or may be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the embodiments of the present application will be understood by those of ordinary skill in the art according to specific circumstances.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and not for limiting the same; although the application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the application, and are intended to be included within the scope of the appended claims and description. In particular, the technical features mentioned in the respective embodiments may be combined in any manner as long as there is no structural conflict. The present application is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions falling within the scope of the claims.
Claims (10)
1. A turbine shaft end locking assembly for locking bearings and sealing runways at the turbine shaft ends, respectively, the turbine shaft end locking assembly comprising:
an external thread portion provided on an outer peripheral side of the shaft end of the turbine shaft;
an internal thread portion provided on an inner peripheral side of an axial end of the turbine shaft, the external thread portion and the internal thread portion having opposite thread directions;
the first locking piece is in threaded connection with the external thread part and is provided with a first anti-rotation groove, the bearing is pressed on the turbine shaft by the first locking piece in a threaded connection state, and at least one part of the first anti-rotation groove is higher than the end face of the shaft end of the turbine shaft;
the second locking piece is in threaded connection with the internal thread part and is provided with a second anti-rotation groove, the second locking piece presses the sealing runway in the turbine shaft in a threaded connection state, and at least one part of the second anti-rotation groove is higher than the end face of the shaft end of the turbine shaft; and
the combined lock ring is provided with an inner claw and an outer claw;
the first locking piece and the second locking piece are connected through the inner clamping claw and the outer clamping claw, an annular space is formed between the first locking piece and the second locking piece, the combined locking ring is arranged in the annular space, the inner clamping claw is connected in the second anti-rotation groove, and the outer clamping claw is connected in the first anti-rotation groove.
2. The turbine shaft end locking assembly of claim 1 wherein the first anti-rotation slots are a plurality and/or the second anti-rotation slots are two or more.
3. The turbine shaft end locking assembly of claim 2 wherein the number of the first anti-rotation grooves and the second anti-rotation grooves is an even number, the first anti-rotation grooves are uniformly arranged on the first locking member, and the second anti-rotation grooves are uniformly arranged on the second locking member.
4. A turbine shaft-end locking assembly as in claim 3 wherein in the installed condition the center of mass of the combination lock collar is located on the axis of the turbine shaft.
5. A turbine shaft-end locking assembly according to claim 3 wherein said inner and outer jaws are each an even number and said inner jaws are uniformly distributed along the inner periphery of said joint collar and said outer jaws are uniformly distributed along the outer periphery of said joint collar.
6. A turbine shaft-end locking assembly according to claim 3 wherein the inner claws are a pair disposed at the inner periphery of the joint lock ring and the outer claws are a pair disposed at the outer periphery of the joint lock ring, the inner claws and the outer claws being staggered circumferentially of the joint lock ring.
7. The turbine shaft-end locking assembly of claim 1, wherein the inner circumference of the first locking member and/or the outer circumference of the second locking member is provided with a mounting groove, and further comprising a retainer ring disposed in the mounting groove and limiting the combined retainer ring from exiting the annular space in the axial direction of the turbine shaft.
8. The turbine shaft-end locking assembly of claim 7 wherein an adjustment pad is disposed between the retaining ring and the combination lock ring.
9. The turbine shaft-end locking assembly of claim 7 wherein the retainer ring is a circlip.
10. A gas turbine engine comprising a turbine shaft end locking assembly according to any one of claims 1 to 9 locking a turbine shaft end member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210316754.2A CN116857016A (en) | 2022-03-28 | 2022-03-28 | Turbine shaft end locking assembly and gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210316754.2A CN116857016A (en) | 2022-03-28 | 2022-03-28 | Turbine shaft end locking assembly and gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116857016A true CN116857016A (en) | 2023-10-10 |
Family
ID=88222200
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210316754.2A Pending CN116857016A (en) | 2022-03-28 | 2022-03-28 | Turbine shaft end locking assembly and gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116857016A (en) |
-
2022
- 2022-03-28 CN CN202210316754.2A patent/CN116857016A/en active Pending
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