CN113847283A - Assembling structure and method for casings of stator blades of gas compressor - Google Patents
Assembling structure and method for casings of stator blades of gas compressor Download PDFInfo
- Publication number
- CN113847283A CN113847283A CN202111134910.5A CN202111134910A CN113847283A CN 113847283 A CN113847283 A CN 113847283A CN 202111134910 A CN202111134910 A CN 202111134910A CN 113847283 A CN113847283 A CN 113847283A
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- stator
- upper edge
- assembly
- edge plates
- annular clamping
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000003754 machining Methods 0.000 claims abstract description 11
- 210000001503 joint Anatomy 0.000 claims description 7
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000007717 exclusion Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/642—Mounting; Assembling; Disassembling of axial pumps by adjusting the clearances between rotary and stationary parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
An assembly structure between compressor stator blade casings, comprising: the inner wall of the stator casing is provided with an annular clamping groove; a plurality of stator blades arranged in the stator casing in a circumferential direction; the upper edge plate of each stator blade is clamped into the annular clamping groove, wherein an assembly adjusting groove is formed between the upper edge plates of two adjacent stator blades; and the assembly adjusting sheet is clamped in the annular clamping groove and is positioned in the assembly adjusting groove, so that the upper edge plates of the stator blades are pressed together in the annular clamping groove. And, a method for assembling compressor stator blade casings, comprising: according to the deviation between the sum of the sizes of the upper edge plates of the stator blades and a design value, machining an assembly adjusting groove between the upper edge plates of two adjacent stator blades and machining corresponding assembly adjusting pieces; the upper edge plates and the assembly adjusting sheets of the stator blades are clamped into the annular clamping grooves in the inner wall of the stator casing, and the assembly adjusting sheets are located in the assembly adjusting grooves and are consistent with the sum of the effective sizes of the upper edge plates of the stator blades with the design value.
Description
Technical Field
The application belongs to the technical field of assembling design among compressor stator blade casings, and particularly relates to an assembling structure and method among compressor stator blade casings.
Background
In the engine, the stator blades of the compressor are arranged in the stator casing along the circumferential direction, the upper edge plates of the blade tips are clamped in the annular clamping grooves in the inner wall of the stator casing, and the upper edge plates clamped in the annular clamping grooves in the inner wall of the stator casing are mutually squeezed together to form a stable structure.
Each stator blade in the compressor is separately processed, so that a size error is inevitably introduced, when the upper edge plate of each stator blade is clamped into the annular clamping groove in the inner wall of the stator casing under the condition of a large number of stator blades, the size error of the upper edge plate of each stator blade is accumulated, and the situation that the size error deviates from a design value is large exists; if the size of the upper edge plate of each stator blade is accumulated and is smaller than the design value and exceeds the allowable range, a larger gap exists between the upper edge plates of the stator blades clamped into the annular clamping groove in the inner wall of the stator casing, so that the upper edge plates of the stator blades are easy to rotate circumferentially in the annular clamping groove in the inner wall of the stator casing, on one hand, the upper edge plates of the stator blades are damaged by violent impact when the gas compressor works, on the other hand, the upper edge plates of the stator blades rotate back and forth in a larger range when the gas compressor works, the stability of gas flow in a flow channel of the gas compressor is difficult to ensure, the performance of influence is influenced, and the improvement of the overall performance of an engine is limited.
In view of the above problems, the current practice is to rework and replace one or more stator blades so that the size of the upper edge plate of each stator blade is accumulated within the allowable range of the design value, and this practice has the following disadvantages:
1) the stator blades have higher manufacturing cost, and one or more stator blades are reprocessed and replaced, so the cost is higher and is not economical;
2) stator blade structure is complicated, and the machining precision requires highly, needs special personnel and its equipment to process, reprocesses, replaces one or more stator blade, and the cycle is longer.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The present application is directed to a compressor stator vane casing assembly and method thereof that overcomes or mitigates at least one known technical disadvantage.
The technical scheme of the application is as follows:
one aspect provides an assembly structure between compressor stator blade casings, including:
the inner wall of the stator casing is provided with an annular clamping groove;
a plurality of stator blades arranged in the stator casing in a circumferential direction; the upper edge plate of each stator blade is clamped into the annular clamping groove, wherein an assembly adjusting groove is formed between the upper edge plates of two adjacent stator blades;
and the assembly adjusting sheet is clamped in the annular clamping groove and is positioned in the assembly adjusting groove, so that the upper edge plates of the stator blades are pressed together in the annular clamping groove.
According to at least one embodiment of the application, in the assembling structure between the stator blade casings of the compressor, the assembling adjusting grooves are divided in half, and the upper edge plates of the two stator blades with the assembling adjusting grooves are machined between the assembling adjusting grooves.
According to at least one embodiment of the application, in the compressor stator vane casing-to-casing assembly structure, the assembly adjusting groove is opened towards the stator casing.
According to at least one embodiment of the application, in the assembling structure between the stator blade casings of the compressor, the assembling adjusting sheets are in contact with the corner parts of the assembling adjusting grooves in a matched mode through fillets.
According to at least one embodiment of the application, in the assembling structure between the stator blade casings of the compressor, the stator casing is composed of two parts which are in butt joint in the radial direction;
stop notches are formed at the butt joint position of the two stator casings and on the upper edge plate of the stator blade at the butt joint position;
compressor stator blade machine casket is assembling structure within a definite time, still includes:
and each stop block is correspondingly clamped in one stop notch.
In another aspect, a method for assembling compressor stator blade casings includes:
according to the deviation between the sum of the sizes of the upper edge plates of the stator blades and a design value, machining an assembly adjusting groove between the upper edge plates of two adjacent stator blades and machining corresponding assembly adjusting pieces;
the upper edge plates and the assembly adjusting sheets of the stator blades are clamped into the annular clamping groove in the inner wall of the stator casing, the assembly adjusting sheets are located in the assembly adjusting grooves, the sum of the effective sizes of the upper edge plates of the stator blades is consistent with a design value, and the upper edge plates of the stator blades are squeezed together in the annular clamping groove.
Drawings
FIG. 1 is a schematic view of an assembly structure between compressor stator vane casings provided by an embodiment of the application;
FIG. 2 is a schematic view of an assembly adjustment groove machined between upper edge plates of two adjacent stator blades provided by an embodiment of the application;
FIG. 3 is a schematic view of an assembled tab provided by an embodiment of the present application;
FIG. 4 is a schematic view of an annular clamping groove for clamping an assembly adjustment sheet between two adjacent stator vane upper flanges provided by an embodiment of the present application;
wherein:
1-a stator case; 2-stator blades; and 3, assembling the adjusting blade.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 4.
One aspect provides an assembly structure between compressor stator blade casings, including:
the stator casing 1 is provided with an annular clamping groove on the inner wall;
a plurality of stator blades 2 arranged in the stator case 1 in the circumferential direction; the upper edge plate of each stator blade 2 is clamped into the annular clamping groove, wherein an assembly adjusting groove is machined between the upper edge plates of two adjacent stator blades 2;
and the assembly adjusting sheet 3 is clamped in the annular clamping groove and is positioned in the assembly adjusting groove, so that the upper edge plates of the stator blades 2 are pressed together in the annular clamping groove.
For the assembling structure between the stator blade casings of the compressor disclosed in the above embodiments, it can be understood by those skilled in the art that the assembling structure can be assembled by referring to the following steps:
according to the deviation between the sum of the sizes of the upper edge plates of each stator blade 2 and a design value, machining an assembly adjusting groove between the upper edge plates of two adjacent stator blades 2 and machining a corresponding assembly adjusting sheet 3;
the upper edge plates of the stator blades 2 and the assembly adjusting sheets 3 are clamped into the annular clamping groove in the inner wall of the stator casing, the assembly adjusting sheets 3 are located in the assembly adjusting grooves, the sum of the effective sizes of the upper edge plates of the stator blades 2 is consistent with a design value, namely, the sum is located within an allowable range of the design value, and the upper edge plates of the stator blades 2 are squeezed together in the annular clamping groove to form a stable structure.
With regard to the assembly structure between stator vane casings of the compressor disclosed in the above embodiments, it can be further understood by those skilled in the art that when the accumulated dimension of the upper edge plates of the respective stator vanes, which are clamped into the annular clamping grooves of the inner wall of the stator casing, deviates from the design value greatly, one or more stator vanes do not need to be re-processed and replaced, and only according to the dimension sum of the upper edge plates of the respective stator vanes 2 and the deviation of the design value, an assembly adjustment groove is processed between the upper edge plates of the two adjacent stator vanes 2, and corresponding assembly adjustment pieces 3 are processed, the upper edge plates of the respective stator vanes 2 and the assembly adjustment pieces 3 are clamped into the annular clamping grooves of the inner wall of the stator casing, so that the assembly adjustment pieces 3 are located in the assembly adjustment grooves, and the sum of the effective dimensions of the upper edge plates of the respective stator vanes 2 conforms to the design value, and only is designed to locally reform the upper edge plates of the two adjacent stator vanes 2, the main structure of the original stator blade 2 is reserved, the required cost is low, the processing is simple, special personnel and equipment are not needed, and the required time is short.
In some optional embodiments, in the above-mentioned assembly structure between stator vane casings of a compressor, the assembly adjustment groove is divided into two halves, and the upper edge plates of the two stator vanes 2 between which the assembly adjustment groove is processed are provided, that is, half of the assembly adjustment groove is provided on each of the upper edge plates of the two stator vanes 2, so as to avoid a situation that one stator vane 2 is seriously deviated from the designed position after the assembly is completed.
In some optional embodiments, in the assembly structure between stator blade casings of the compressor, the opening of the assembly adjusting groove faces the stator casing 1, and when the structure is assembled, the assembly adjusting piece 3 can be clamped into the assembly adjusting groove first, so that the assembly adjusting piece 3 is reliably clamped between two adjacent stator blades 2, and then clamped into the annular clamping groove, so that the assembly adjusting piece 3 can be accurately positioned in the assembly process, and the clamping stagnation and falling-off situations are avoided. .
In some optional embodiments, in the assembly structure between compressor stator blade casings, the assembly adjusting sheet 3 is in contact with a corner portion of the assembly adjusting groove in a round corner fit manner, so as to avoid generating large local stress and causing structural damage.
In some optional embodiments, in the above assembling structure between stator blade casings of a compressor, the stator casing 1 is composed of two parts which are butted in the radial direction, so as to facilitate the assembling of the structure, and an assembling adjusting groove is processed between the upper edge plates of two adjacent stator blades 3 in the corresponding stator blade 2 in each part of the stator casing 1, and is used for installing and assembling the adjusting sheet 3;
stop notches are formed at the butt joint position of the two stator casings 1 and the upper edge plate of the stator blade 2 at the butt joint position;
compressor stator blade machine casket is assembling structure within a definite time, still includes:
and each stop block is correspondingly clamped in one stop notch so as to reliably limit the upper edge plate of each stator blade 3 clamped in the ring-shaped clamping groove from rotating.
In another aspect, a method for assembling compressor stator blade casings includes:
according to the deviation between the sum of the sizes of the upper edge plates of each stator blade 2 and a design value, machining an assembly adjusting groove between the upper edge plates of two adjacent stator blades 2 and machining a corresponding assembly adjusting sheet 3;
the upper edge plates of the stator blades 2 and the assembly adjusting sheets 3 are clamped into the annular clamping grooves in the inner wall of the stator casing, the assembly adjusting sheets 3 are located in the assembly adjusting grooves, the sum of the effective sizes of the upper edge plates of the stator blades 2 is consistent with a design value, and the upper edge plates of the stator blades 2 are squeezed together in the annular clamping grooves.
For the assembling method between the compressor stator blade casings disclosed in the above embodiments, to implement the assembling of the assembling structure between the compressor stator blade casings disclosed in the above embodiments, the description is simple, and specific relevant points can be referred to the description of relevant parts of the assembling structure between the compressor stator blade casings, and the technical effects can also be referred to the technical effects of relevant parts of the assembling structure between the compressor stator blade casings, which are not described herein again.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (6)
1. The utility model provides an assembly structure between compressor stator blade machine casket which characterized in that includes:
the stator casing (1) is provided with an annular clamping groove on the inner wall;
a plurality of stator blades (2) arranged in the stator case (1) in the circumferential direction; the upper edge plate of each stator blade (2) is clamped into the annular clamping groove, wherein an assembly adjusting groove is formed between the upper edge plates of two adjacent stator blades (2);
and the assembling adjusting sheet (3) is clamped in the annular clamping groove and is positioned in the assembling adjusting groove, so that the upper edge plates of the stator blades (2) are pressed together in the annular clamping groove.
2. The compressor stator vane cartridge-to-cartridge assembly structure of claim 1,
the assembly adjusting grooves are divided in half, and the upper edge plates of the two stator blades (2) with the assembly adjusting grooves are machined between the assembly adjusting grooves.
3. The compressor stator vane cartridge-to-cartridge assembly structure of claim 1,
the assembly adjustment groove opens towards the stator casing (1).
4. The compressor stator vane cartridge to cartridge assembly structure of claim 3,
the assembly adjusting sheet (3) is in fit contact with the corner part of the assembly adjusting groove through a fillet.
5. The compressor stator vane cartridge-to-cartridge assembly structure of claim 1,
the stator casing (1) is formed by two parts which are butted in the radial direction;
a stop notch is formed at the butt joint part of the two stator casings (1) and the upper edge plate of the stator blade (2) at the butt joint part;
assembly structure between compressor stator blade machine casket still includes:
and each stop block is correspondingly clamped in one stop notch.
6. A method for assembling casings of stator blades of an air compressor is characterized by comprising the following steps:
machining an assembly adjusting groove between the upper edge plates of two adjacent stator blades (2) and machining corresponding assembly adjusting sheets (3) according to the deviation of the sum of the sizes of the upper edge plates of the stator blades (2) and a design value;
and (2) clamping the upper edge plate of each stator blade (2) and the assembly adjusting sheet (3) into an annular clamping groove in the inner wall of the stator casing, wherein the assembly adjusting sheet (3) is positioned in the assembly adjusting groove and conforms to the design value with the sum of the effective sizes of the upper edge plates of each stator blade (2), so that the upper edge plates of each stator blade (2) are squeezed together in the annular clamping groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111134910.5A CN113847283A (en) | 2021-09-27 | 2021-09-27 | Assembling structure and method for casings of stator blades of gas compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111134910.5A CN113847283A (en) | 2021-09-27 | 2021-09-27 | Assembling structure and method for casings of stator blades of gas compressor |
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| CN113847283A true CN113847283A (en) | 2021-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111134910.5A Pending CN113847283A (en) | 2021-09-27 | 2021-09-27 | Assembling structure and method for casings of stator blades of gas compressor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114962338A (en) * | 2022-04-27 | 2022-08-30 | 四川航天中天动力装备有限责任公司 | Split type stator casing structure of turbojet engine and assembly method thereof |
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| CN104819164A (en) * | 2015-05-15 | 2015-08-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Adjustable stator blade linkage adjusting device |
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| CN107542500A (en) * | 2017-09-30 | 2018-01-05 | 中国航发沈阳发动机研究所 | Aerial engine fan casing and its assembly method |
| US20190040752A1 (en) * | 2017-08-04 | 2019-02-07 | Pratt & Whitney Canada Corp. | Rotor casing |
| US20190211682A1 (en) * | 2016-09-13 | 2019-07-11 | Siemens Aktiengesellschaft | A technique for low-speed balancing of a rotor of a compressor for a gas turbine |
| KR102191556B1 (en) * | 2019-10-28 | 2020-12-15 | (주)코리아씨티씨 | Functional fan |
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2021
- 2021-09-27 CN CN202111134910.5A patent/CN113847283A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040081554A1 (en) * | 2002-10-23 | 2004-04-29 | General Electric | Tribologically improved design for variable stator vanes |
| CN104819164A (en) * | 2015-05-15 | 2015-08-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Adjustable stator blade linkage adjusting device |
| CN106545524A (en) * | 2015-09-23 | 2017-03-29 | 中航商用航空发动机有限责任公司 | Compressor stator blade governor motion |
| US20190211682A1 (en) * | 2016-09-13 | 2019-07-11 | Siemens Aktiengesellschaft | A technique for low-speed balancing of a rotor of a compressor for a gas turbine |
| US20190040752A1 (en) * | 2017-08-04 | 2019-02-07 | Pratt & Whitney Canada Corp. | Rotor casing |
| CN107542500A (en) * | 2017-09-30 | 2018-01-05 | 中国航发沈阳发动机研究所 | Aerial engine fan casing and its assembly method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114962338A (en) * | 2022-04-27 | 2022-08-30 | 四川航天中天动力装备有限责任公司 | Split type stator casing structure of turbojet engine and assembly method thereof |
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