CN213628074U - Gas compressor and aircraft engine - Google Patents
Gas compressor and aircraft engine Download PDFInfo
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- CN213628074U CN213628074U CN202022328242.7U CN202022328242U CN213628074U CN 213628074 U CN213628074 U CN 213628074U CN 202022328242 U CN202022328242 U CN 202022328242U CN 213628074 U CN213628074 U CN 213628074U
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Abstract
The present disclosure relates to a compressor and an aircraft engine, wherein the compressor includes: the rotor disc is provided with a mortise extending along the circumferential direction, and the side wall of the mortise along the axial direction is provided with a limiting groove; the roots of the blades are provided with tenons, and the tenons of the blades are arranged in the mortises along the circumferential direction; the locking block is arranged in the mortise and movably arranged along the radial direction, and is provided with a through hole along the radial direction; the locking screw penetrates through the through hole; and a reset element disposed between the locking block and the locking screw, configured to provide a reset force to the locking block moving radially outward; when the locking block moves to the first position, the locking block is separated from the limiting groove, when the locking block moves to the second position, the locking block is embedded into the limiting groove under the action of the reset element, the plurality of blades are circumferentially limited through the locking screws, and the second position is located on the radial outer side of the first position.
Description
Technical Field
The disclosure relates to the technical field of aero-engines, in particular to a gas compressor and an aero-engine.
Background
At present, a large number of compressor blades of an aeroengine or a gas turbine adopt circumferential tenon design. As shown in fig. 1 to 3, in order to realize circumferential fixation on the rotor disc, a locking block 2a is adopted, and notches 12a with specific shapes are respectively designed at the edge plate of the rotor blade and the mortise 11a of the rotor disc 1 a.
During assembly, as shown in fig. 2, when the locking block 2a slides to the notch 12a inside the mortise 11a, a rotating moment is applied to the inner square hole 31a at the top of the locking screw 3a, so that the locking block 2a is jacked up upwards through thread fit until the final height is reached to perform circumferential limit on the blade.
In actual operation, whether the locking block 2a is in the correct position of the notch 12a is difficult to judge, and only the judgment can be made by trial screwing the locking screw 3a, and the locking block 2a may rotate in the mortise 11a during installation and cannot be pushed into the notch 12a as required. In order to avoid the situation, the relative size of the locking block 2a needs to be strictly controlled according to the size of the mortise 11a, so that the universal configuration is difficult to realize, the requirement on the skill of field personnel is high, and certain cost consumption is caused.
SUMMERY OF THE UTILITY MODEL
The embodiment of the disclosure provides a gas compressor and an aircraft engine, which can enable a locking block to be conveniently and reliably located at a locking position.
According to an aspect of the present disclosure, there is provided a compressor including:
the rotor disc is provided with a mortise extending along the circumferential direction, and the side wall of the mortise along the axial direction is provided with a limiting groove;
the roots of the blades are provided with tenons, and the tenons of the blades are arranged in the mortises along the circumferential direction;
the locking block is arranged in the mortise and movably arranged along the radial direction, and is provided with a through hole along the radial direction;
the locking screw penetrates through the through hole; and
a reset element disposed between the locking block and the locking screw, configured to provide a reset force to the locking block moving radially outward;
when the locking block moves to the first position, the locking block is separated from the limiting groove, when the locking block moves to the second position, the locking block is embedded into the limiting groove under the action of the reset element, the plurality of blades are circumferentially limited through the locking screws, and the second position is located on the radial outer side of the first position.
In some embodiments, the locking screw includes a screw head disposed toward the bottom of the mortise, and the reduction element is located between the radially inner side of the locking block and the screw head.
In some embodiments, the return element is a conical spring that increases in diameter from an inner end to an outer end in a radial direction.
In some embodiments, the through hole comprises a first unthreaded hole section, a first threaded hole section and a second threaded hole section along the self axial direction, the first threaded hole section is connected to the radial inner side of the first unthreaded hole section, and the second threaded hole section is connected to the radial outer side of the first unthreaded hole section; the locking screw sequentially comprises a first polished rod section, a first screw rod section and a second polished rod section from inside to outside along the radial direction;
the first screw rod section is positioned in the first unthreaded hole section and can move along the first unthreaded hole section, the first unthreaded rod section penetrates through the first threaded hole section, and the second unthreaded rod section penetrates through the second threaded hole section; when the locking block is at the second position, the first screw section is abutted against the boss of the first unthreaded hole section adjacent to the first threaded hole section.
In some embodiments, the locking screw further comprises a second screw section located radially outward of the second rod section;
when the locking block is at the second position, the second screw section is abutted against the outer end of the second threaded hole section.
In some embodiments, the locking screw includes a screw head disposed toward the bottom of the mortise, and the reduction element is disposed outside the first polished rod segment and between the radially inner side of the locking block and the screw head.
In some embodiments, the locking block is movable in the circumferential direction of the tongue and groove.
In some embodiments, the locking segment includes, in order from the inside to the outside in the radial direction, a blocking portion configured to be caught at a position where the mortise is located radially inside the stopper groove when in the second position, a first portion configured to be fitted into the stopper groove when in the second position, and a second portion having an outer diameter sized to be smaller than a minimum axial width of the mortise.
In some embodiments, the two side walls of the mortise in the axial direction are both provided with limiting grooves, and the two limiting grooves are arranged oppositely.
In some embodiments, an end of the locking screw protruding out of the mortise is provided with an operation hole configured to provide a circumferential screwing force to the locking screw.
According to another aspect of the present disclosure, an aircraft engine is provided, which includes the compressor of the above embodiment.
According to the compressor disclosed by the embodiment of the disclosure, the reset element is arranged between the locking block and the locking screw, so that when the locking block moves to the position of the limiting groove along the circumferential direction of the mortise, the reset force moving outwards along the radial direction is provided for the locking block, the locking block is embedded into the limiting groove, and the locking screw is used for circumferentially limiting the plurality of blades. The structure can ensure that the locking block is in a correct circumferential position in the assembling process, and can prevent the locking block from being knocked in the mortise and being incapable of jacking up during assembling, so that the locking block is accurately and reliably embedded into the limiting groove for locking; in addition, the design requirement of the locking block can be reduced, the universality of the locking structure is improved, and the technical requirement on assembly personnel is reduced.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the disclosure and together with the description serve to explain the disclosure and not to limit the disclosure. In the drawings:
FIG. 1 is a schematic diagram of a blade locking device in a compressor of the prior art;
FIG. 2 is a schematic view of the blade locking device shown in FIG. 1, wherein the locking block is moved to the notch along the circumferential direction;
FIG. 3 is a schematic view of the blade locking device shown in FIG. 1 in a state of jacking a locking block to limit the position;
FIG. 4 is a schematic view of a blade locking arrangement in some embodiments of the compressor of the present disclosure;
FIG. 5 is a schematic view of the blade locking device shown in FIG. 4 showing a state in which the locking block is lifted up to achieve a limit;
FIG. 6 is a schematic view of some embodiments of a locking block in a blade locking device according to the present disclosure;
FIG. 7 is a schematic structural view of some embodiments of a locking screw in the blade locking device of the present disclosure.
Description of the reference numerals
1a, a rotor disc; 11a, mortises; 12a, a gap; 2a, a locking block; 3a, locking screws; 31a, an inner square hole;
1. a rotor disk; 11. mortises; 12. a limiting groove; 2. a locking block; 21. a smooth hole section; 22. a first threaded bore section; 23. a second threaded bore section; 24. a blocking portion; 25. a first part; 26. a second section; 3. locking the screw; 31. an operation hole; 32. a screw head; 33. a first polished rod segment; 34. a first screw section; 35. a second polished rod segment; 36. a second screw section; 4. and resetting the element.
Detailed Description
The present disclosure is described in detail below. In the following paragraphs, different aspects of the embodiments are defined in more detail. Aspects so defined may be combined with any other aspect or aspects unless clearly indicated to the contrary. In particular, any feature considered to be preferred or advantageous may be combined with one or more other features considered to be preferred or advantageous.
The terms "first", "second", and the like in the present disclosure are merely for convenience of description to distinguish different constituent elements having the same name, and do not denote a sequential or primary-secondary relationship.
In the description of the present invention, it is to be understood that the terms "inner", "outer", "upper", "lower", "left" and "right", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention, and do not indicate or imply that the device referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the scope of the present invention. Moreover, references to "circumferential," "axial," and "radial" in various embodiments are made with respect to the compressor, unless otherwise specified.
As shown in fig. 4-7, the present disclosure provides a compressor that may be used in an aircraft engine or gas turbine. For example, the compressor may be an axial compressor, and the multistage compression device with the airflow flowing direction consistent with or close to the rotating axial lead direction of the working wheel is formed by alternately arranging a series of stators and rotors.
In some embodiments, the compressor comprises: rotor disc 1, a plurality of blades, locking block 2, locking screw 3 and reset element 4.
The rotor disc 1 is provided with a mortise 11 extending along the circumferential direction, the mortise 11 is provided with a limiting groove 12 along the axial side wall, for example, the limiting groove 12 may be a notch formed in the side wall of the mortise 11. The respective roots of a plurality of blades all are equipped with the tenon, and the respective tenon of a plurality of blades is installed in the tongue-and-groove 11 along circumference in proper order. The blades of the rotor are a structure which applies work by rotating compressed air, and usually consist of a blade body, a flange plate and a tenon, and are fixed with other structures through the flange plate and rotate at high speed.
The locking block 2 is arranged in the mortise 11 and movably arranged along the radial direction, the locking block 2 is provided with a through hole along the radial direction, and the locking screw 3 penetrates through the through hole. The reset element 4 is disposed between the locking block 2 and the locking screw 3, and is configured to provide a reset force to the locking block 2 moving radially outward, for example, the reset element 4 may be a spring or the like.
When the locking block 2 moves to the first position along the radial direction, the locking block 2 is separated from the limiting groove 12 and is positioned on the inner side of the limiting groove 12 along the radial direction, and at the moment, under the limiting action of the mortise 11, the reset element 4 is in a compressed state; when the locking block 2 moves to the second position along the radial direction, the locking block 2 is embedded into the limiting groove 12, the plurality of blades are limited in the circumferential direction through the locking screws 3, and the second position is located on the radial outer side of the first position. The locking screws 3 can be positioned between adjacent blades, so that the plurality of blades are circumferentially limited, and one, two or more groups of locking devices formed by the locking blocks 2 and the locking screws 3 can be arranged.
According to the compressor disclosed by the embodiment of the disclosure, the reset element 4 is arranged between the locking block 2 and the locking screw 3, so that when the locking block 2 moves to the position of the limiting groove 12 along the circumferential direction of the mortise 11, the reset force moving outwards along the radial direction is provided for the locking block 2, the locking block 2 is embedded into the limiting groove 12, and the locking screw 3 is used for circumferentially limiting a plurality of blades. The structure can ensure that the locking block 2 is in a correct circumferential position in the assembling process, and can prevent the locking block 2 from being knocked in the mortise 11 and being incapable of jacking up during assembling, so that the locking block 2 is accurately and reliably embedded into the limiting groove 12 for locking; in addition, the design requirement of the locking block 2 can be reduced, the universality of the locking structure is improved, and the technical requirement on assembly personnel is reduced.
As shown in fig. 4, 5 and 7, the locking screw 3 comprises a screw head 32, the screw head 32 being arranged towards the bottom of the mortise slot 11, and the return element 4 being located between the radially inner side of the locking block 2 and the screw head 32. This embodiment has one end of the restoring member 4 abutting against the surface of the screw head 32 facing the radial outside, and can provide restoring force for the radial outward movement of the locking block 2, thereby reliably jacking up the locking block 2 into the insertion limiting groove 12.
As shown in fig. 4 and 5, the return element 4 is a conical spring, and the diameter of the conical spring is gradually increased from the inner end to the outer end in the radial direction. This embodiment makes it easier to move the locking piece 2 by using a conical spring, as the locking piece 2 is compressed circumferentially at the bottom of the mortise 11, the return element 4 is sufficiently compressed to a minimum thickness.
In some embodiments, as shown in fig. 4 to 6, the through hole comprises, in its own axial direction, a first unthreaded hole section 21, a first threaded hole section 22 and a second threaded hole section 23, the first threaded hole section 22 being connected radially inside the first unthreaded hole section 21, the second threaded hole section 23 being connected radially outside the first unthreaded hole section 21. As shown in fig. 7, the locking screw 3 includes a screw head 32, a first polished rod section 33, a first polished rod section 34 and a second polished rod section 35 in this order from inside to outside in the radial direction.
Wherein, the locking screw 3 penetrates into the through hole from the end where the first threaded hole section 22 is located, after penetrating into the through hole, as shown in fig. 4 and 5, the first threaded section 34 is located in the first unthreaded hole section 21 and is movable along the first unthreaded hole section 21, the first unthreaded rod section 33 penetrates through the first threaded hole section 22, and the second unthreaded rod section 35 penetrates through the second threaded hole section 23. As shown in fig. 5, when the locking block 2 is in the second position, the first screw section 34 abuts against the boss of the first unthreaded hole section 21 adjacent to the first threaded hole section 22.
This embodiment is through setting up first screw section 34 on locking screw 3 to set up first screw hole section 22 in the inner of the latch segment 2 through-hole, not only can make locking screw 3 pass the through-hole from the radial inner of latch segment 2, can also make first screw section 34 support and lean on the boss that first unthreaded hole section 21 and first screw hole section 22 adjoin when latch segment 2 is in the second position, thereby prescribes a limit to the radial position that latch segment 2 imbeds in spacing groove 12.
Further, as shown in fig. 7, the locking screw 3 further includes a second screw section 36 located radially outside the second screw section 35. Wherein the second screw section 36 abuts the outer end of the second threaded bore section 23 when the locking block 2 is in the second position, as shown in figure 5.
The end of the locking screw 3 protruding out of the mortise 11 is provided with an operation hole 31, such as a hexagonal hole, configured to provide a circumferential screwing force to the locking screw 3. During assembly, after the locking block 2 enters the limiting groove 12, the locking screw 3 is screwed through the operation hole 31 to enable the radial inner end of the second screw section 36 to abut against the locking block 2, so that the locking screw 3 and the locking block 2 are fixed relatively, and reliable circumferential limiting is provided for the blade.
As shown in fig. 4 and 5, the locking screw 3 includes a screw head 32, the screw head 32 is disposed toward the bottom of the mortise 11, and the restoring element 4 is sleeved outside the first polished rod section 33 and is located between the inner side surface of the locking block 2 in the radial direction and the screw head 32.
In some embodiments, the locking block 2 is movable along the circumferential direction of the mortise 11, and after the locking block 2 is placed in the mortise 11, the locking block 2 can be moved along the circumferential direction, and when the locking block 2 is moved to the position of the limiting groove 12, the locking block 2 is pushed into the limiting groove 12 under the action of the reset element 4.
In some embodiments, as shown in fig. 6, the locking block 2 includes a blocking portion 24, a first portion 25 and a second portion 26 in the radial direction from the inside to the outside, the blocking portion 24 is configured to be blocked at a position where the mortise 11 is located at the radial inside of the position-limiting groove 12 in the second position, the first portion 25 is configured to be embedded in the position-limiting groove 12 in the second position, and the outer diameter of the second portion 26 is configured to be smaller than the minimum axial width of the mortise 11. Specifically, the blocking portion 24 may have a triangular-like structure protruding the first portion in a longitudinal section of the locking block 2.
As shown in fig. 4 and 5, the two side walls of the mortise 11 along the axial direction are both provided with a limiting groove 12, and the two limiting grooves 12 are arranged oppositely. Like this when the latch segment 2 is in the second position, the latch segment 2 can get into two spacing grooves 12 simultaneously, makes the locking force of latch segment 2 more balanced to make locking screw 3 provide more reliable and stable circumference limiting displacement to a plurality of blades.
In a specific embodiment, by arranging the reset element 4 between the inner side surface of the locking block 2 in the radial direction and the locking screw 3, when the locking device is installed in the mortise 11, the reset element 4 is in a compressed state and can move in the mortise 11 along the circumferential direction, and when the locking device is moved to the position of the limiting groove 12, the reset element is released under the elastic force of the reset element 4, so that the locking block 2 is automatically lifted and jacked into the limiting groove 12, and the locking block 2 is ensured not to rotate in the mortise 11. Next, the locking screw 3 is tightened against the locking block 2.
Secondly, the disclosure also provides an aircraft engine which comprises the compressor of the embodiment.
The compressor and the aircraft engine provided by the disclosure are described in detail above. The principles and embodiments of the present disclosure are explained herein using specific examples, which are set forth only to help understand the method and its core ideas of the present disclosure. It should be noted that, for those skilled in the art, it is possible to make several improvements and modifications to the present disclosure without departing from the principle of the present disclosure, and such improvements and modifications also fall within the scope of the claims of the present disclosure.
Claims (10)
1. A compressor, comprising:
the rotor disc (1) is provided with a mortise (11) extending along the circumferential direction, and a limiting groove (12) is formed in the axial side wall of the mortise (11);
the roots of the blades are provided with tenons, and the tenons of the blades are installed in the mortises (11) along the circumferential direction;
the locking block (2) is arranged in the mortise (11) and can move in the radial direction, and a through hole is formed in the locking block (2) in the radial direction;
a locking screw (3) passing through the through hole; and
a reset element (4) provided between the locking block (2) and the locking screw (3) and configured to provide a reset force to the locking block (2) moving radially outwards;
when the locking block (2) moves to a first position, the locking block (2) is separated from the limiting groove (12), when the locking block (2) moves to a second position, the locking block (2) is embedded into the limiting groove (12) under the action of the reset element (4), the blades are circumferentially limited through the locking screw (3), and the second position is located on the radial outer side of the first position.
2. Compressor according to claim 1, characterized in that the locking screw (3) comprises a screw head (32), the screw head (32) being arranged towards the bottom of the mortise (11), the return element (4) being located between the radially inner side of the locking block (2) and the screw head (32).
3. Compressor according to claim 1, characterized in that the return element (4) is a conical spring, which increases in diameter from the inner end to the outer end in the radial direction.
4. The compressor according to claim 1, characterized in that the through hole comprises a first unthreaded hole section (21), a first threaded hole section (22) and a second threaded hole section (23) along the axial direction of the through hole, the first threaded hole section (22) is connected to the radial inner side of the first unthreaded hole section (21), and the second threaded hole section (23) is connected to the radial outer side of the first unthreaded hole section (21); the locking screw (3) sequentially comprises a first polished rod section (33), a first screw rod section (34) and a second polished rod section (35) from inside to outside along the radial direction;
wherein the first screw section (34) is located within and movable along the first unthreaded bore section (21), the first unthreaded bore section (22) being passed through by the first unthreaded bore section (33), the second unthreaded bore section (23) being passed through by the second unthreaded bore section (35); when the locking block (2) is in the second position, the first screw section (34) abuts against a boss of the first unthreaded hole section (21) adjacent to the first threaded hole section (22).
5. Compressor according to claim 4, characterized in that the locking screw (3) further comprises a second screw section (36) located radially outside the second polished rod section (35);
wherein the second screw section (36) abuts against the outer end of the second threaded bore section (23) when the locking block (2) is in the second position.
6. The compressor as claimed in claim 4, characterised in that the locking screw (3) comprises a screw head (32), the screw head (32) being arranged towards the bottom of the mortise (11), the restoring element (4) being arranged around the first lever section (33) between a radially inner side of the locking block (2) and the screw head (32).
7. Compressor according to claim 1, characterized in that the locking piece (2) is movable in the circumferential direction of the mortise (11).
8. Compressor according to claim 1, characterized in that the locking block (2) comprises, in the radial direction, in order from the inside to the outside, a blocking portion (24), a first portion (25) and a second portion (26), the blocking portion (24) being configured to block in the second position a position in which the mortise (11) is located radially inside the retaining groove (12), the first portion (25) being configured to engage in the retaining groove (12) in the second position, the second portion (26) having an outer diameter dimension configured to be smaller than the smallest axial width of the mortise (11).
9. The compressor according to claim 1, characterized in that the two side walls of the mortise (11) along the axial direction are provided with the limiting grooves (12), and the two limiting grooves (12) are arranged oppositely.
10. An aircraft engine, characterized in that it comprises a compressor as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022328242.7U CN213628074U (en) | 2020-10-19 | 2020-10-19 | Gas compressor and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022328242.7U CN213628074U (en) | 2020-10-19 | 2020-10-19 | Gas compressor and aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN213628074U true CN213628074U (en) | 2021-07-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022328242.7U Active CN213628074U (en) | 2020-10-19 | 2020-10-19 | Gas compressor and aircraft engine |
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| CN (1) | CN213628074U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113586519A (en) * | 2021-08-24 | 2021-11-02 | 中国联合重型燃气轮机技术有限公司 | Locking device and compressor and gas turbine comprising same |
| CN113586520A (en) * | 2021-08-24 | 2021-11-02 | 中国联合重型燃气轮机技术有限公司 | Locking device and compressor and gas turbine comprising same |
-
2020
- 2020-10-19 CN CN202022328242.7U patent/CN213628074U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113586519A (en) * | 2021-08-24 | 2021-11-02 | 中国联合重型燃气轮机技术有限公司 | Locking device and compressor and gas turbine comprising same |
| CN113586520A (en) * | 2021-08-24 | 2021-11-02 | 中国联合重型燃气轮机技术有限公司 | Locking device and compressor and gas turbine comprising same |
| CN113586520B (en) * | 2021-08-24 | 2023-09-01 | 中国联合重型燃气轮机技术有限公司 | Locking device and gas compressor and gas turbine comprising same |
| CN113586519B (en) * | 2021-08-24 | 2023-09-26 | 中国联合重型燃气轮机技术有限公司 | Locking device and gas compressor and gas turbine comprising same |
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