CN114109539A - Connecting structure and method between turbine casings - Google Patents
Connecting structure and method between turbine casings Download PDFInfo
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- CN114109539A CN114109539A CN202111342685.4A CN202111342685A CN114109539A CN 114109539 A CN114109539 A CN 114109539A CN 202111342685 A CN202111342685 A CN 202111342685A CN 114109539 A CN114109539 A CN 114109539A
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- turbine
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- 238000000034 method Methods 0.000 title claims abstract description 10
- 230000000712 assembly Effects 0.000 claims abstract description 4
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- 125000003003 spiro group Chemical group 0.000 claims description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- Engineering & Computer Science (AREA)
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Abstract
The application belongs to the field of design of aero-engines and gas turbines, and particularly relates to a connecting structure and a connecting method between turbine casings. The structure includes: the turbine outer casing is connected with the turbine inner casing through bolts. A plurality of bosses are arranged on the outer wall of the turbine inner casing along the circumferential direction, and unthreaded holes are formed in the bosses; the outer-layer turbine casing is sleeved on the outer side of the inner-layer turbine casing, and is provided with a mounting edge; the casing support ring comprises a first support ring and a second support ring which are integrally formed, the first support ring is provided with a radial bolt hole matched with the boss, and the second support ring is connected with the mounting edge of the outer casing of the turbine through a plurality of bolt assemblies which are circumferentially arranged; the bolt positioning pin comprises a thread section and a polished rod section, and the bolt positioning pin penetrates through the bolt hole in the first supporting ring and then is matched with the boss.
Description
Technical Field
The application belongs to the field of design of aero-engines and gas turbines, and particularly relates to a connecting structure and a connecting method between turbine casings.
Background
In the prior art aircraft engines and gas turbines, the turbine casing is generally constructed from an inner turbine casing and an outer turbine casing, which are generally positioned by radial spigots and then bolted and screwed together. The inner casing of the turbine is used for forming a gas flow channel of the engine, so that high-temperature gas flows in the inner casing of the turbine. Because the flowing high-temperature gas is arranged in the inner-layer casing of the turbine, the environment temperature is higher, and the radial thermal expansion amount is larger; and the outer casing of the turbine is not in direct contact with high-temperature gas, and the environment temperature is lower, so the radial thermal expansion amount of the outer casing of the turbine is smaller. Because the expansion amounts of the two parts are not matched and are restrained by the radial spigot, the vertical mounting edge part on the inner casing of the turbine can generate large internal stress, and the parts are easy to deform or crack after long-term operation.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
An object of the present application is to provide a connection structure and method between turbine casings to solve at least one problem of the prior art.
The technical scheme of the application is as follows:
a first aspect of the present application provides a connection structure between turbine casings, including:
the outer wall of the turbine inner-layer casing is provided with a plurality of bosses along the circumferential direction, and the bosses are provided with unthreaded holes;
the outer-layer turbine casing is sleeved on the outer side of the inner-layer turbine casing, and is provided with a mounting edge;
the cross section of the casing support ring is L-shaped, the casing support ring comprises a first support ring and a second support ring which are integrally formed, a radial bolt hole matched with the boss is formed in the first support ring, and the second support ring is connected with the mounting edge of the outer casing of the turbine through a plurality of bolt assemblies which are circumferentially arranged;
the bolt positioning pin, the bolt positioning pin includes screw thread section and polished rod section, the bolt positioning pin pass behind the bolt hole on the first support ring with the boss cooperation, wherein, the screw thread section with the bolt hole spiro union of first supporting tube, the polished rod section holds in the unthreaded hole of boss.
In at least one embodiment of the present application, the second support ring is positioned with the mounting edge of the outer turbine casing along the radial spigot.
In at least one embodiment of the present application, the bolt holes on the boss and the first support ring are all uniformly arranged in the circumferential direction.
In at least one embodiment of this application, the outer wall of turbine inner casing is provided with the multirow boss along the axial, and every row the boss includes a plurality of along arranging circumferentially, and the bolt hole on the first support ring is seted up the multirow along the axial, and every row the bolt hole includes a plurality of along arranging circumferentially.
In at least one embodiment of the present application, the outer wall of the turbine inner casing is provided with two rows of bosses along the axial direction, each row of bosses comprises a plurality of bosses arranged along the circumferential direction, two rows of bolt holes on the first support ring are arranged along the axial direction, and each row of bolt holes comprises a plurality of bolts arranged along the circumferential direction.
In at least one embodiment of the present application, a predetermined gap is provided between the end surface of the boss and the first support ring, and a predetermined gap is provided between the end of the polished rod section of the bolt positioning pin and the bottom end of the polished hole of the boss.
A second aspect of the present application provides a method of connecting between turbine casings, based on the structure of connecting between turbine casings as described above, including:
determining the axial and circumferential relative positions of a turbine inner layer casing and a casing support ring;
screwing the bolt positioning pin into a bolt hole of the casing support ring, and simultaneously inserting a polished rod section of the bolt positioning pin into a polished hole of a boss of the turbine inner-layer casing, so that the turbine inner-layer casing and the casing support ring are connected into an integral assembly through the bolt positioning pin;
and step three, connecting the casing support ring with the outer casing of the turbine through a bolt assembly.
The invention has at least the following beneficial technical effects:
the utility model provides a connection structure between turbine machine casket, turbine inner layer machine casket can be along the radial free expansion of bolt locating pin, has solved in the traditional scheme because the part thermal expansion volume mismatch and receive radial tang constraint and produce the problem of great internal stress to improve part life, simple structure, the hookup is reliable, and the cost is lower, has great engineering using value.
Drawings
FIG. 1 is a schematic view of a connection between turbine casings according to an embodiment of the present application;
FIG. 2 is a view A-A of FIG. 1;
FIG. 3 is a schematic view of a bolt alignment pin according to one embodiment of the present application;
FIG. 4 is a schematic view of a connection between turbine casings according to another embodiment of the present application.
Wherein:
1-turbine inner casing; 11-a boss; 2-turbine outer casing; 3-a casing support ring; 4-bolt locating pin; 41-a thread segment; 42-polished rod segment.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 3.
One aspect of the present application provides a connection structure between turbine casings, including: the turbine inner layer casing 1, the turbine outer layer casing 2, the casing support ring 3 and the bolt positioning pin 4.
Specifically, the inner turbine casing 1, the outer turbine casing 2 and the casing support ring 3 are all of a whole ring structure. The outer wall of the turbine inner-layer casing 1 is circumferentially provided with a plurality of bosses 11 which can be uniformly distributed or non-uniformly distributed, and the bosses 11 are provided with unthreaded holes, so that the polished rod sections 42 of the bolt positioning pins 4 can be freely inserted during assembly. The outer turbine casing 2 is sleeved on the outer side of the inner turbine casing 1, and the outer turbine casing 2 is provided with a mounting edge; the casing support ring 3 is L-shaped in cross section and comprises a first support ring and a second support ring which are integrally formed, radial bolt holes matched with the bosses 11 in number and position are formed in the first support ring, and the second support ring is connected with the mounting edge of the outer casing 2 of the turbine through a plurality of bolt assemblies which are circumferentially arranged; the bolt positioning pin 4 comprises a threaded section 41 and a polished rod section 42, the bolt positioning pin 4 is matched with the boss 11 after penetrating through a bolt hole on the first support ring, wherein the threaded section 41 is in threaded connection with the bolt hole of the first support pipe, and the polished rod section 42 is accommodated in a polished hole of the boss 11.
Advantageously, in one embodiment of the present application, the second support ring is positioned radially spigot to the mounting edge of the outer turbine casing 2.
In the preferred embodiment of the present application, the boss 11 and the bolt holes on the first support ring are all uniformly arranged in the circumferential direction.
In the preferred embodiment of the present application, the outer wall of the turbine inner casing 1 may be provided with a plurality of rows of bosses 11 along the axial direction, each row of bosses 11 includes a plurality of bosses arranged along the circumferential direction, bolt holes on the first support ring are matched with the bosses 11, a plurality of rows are also arranged along the axial direction, and each row of bolt holes includes a plurality of bolts arranged along the circumferential direction. In this embodiment, as shown in fig. 4, two rows of bosses 11 are axially disposed on the outer wall of the turbine inner casing 1, each row of bosses 11 includes a plurality of bosses arranged along the circumferential direction, two rows of bolt holes on the first support ring are axially formed, and each row of bolt holes includes a plurality of bosses arranged along the circumferential direction.
In the preferred embodiment of the present application, a certain radial clearance is designed between the end surface of the boss 11 of the turbine inner casing 1 and the first support ring of the casing support ring 3, and a certain radial clearance is also designed between the end of the polished rod section 42 of the bolt positioning pin 4 and the bottom end of the polished hole of the boss 11 of the turbine inner casing 1. When the turbine inner-layer casing 1 is heated, the turbine inner-layer casing can freely expand along the direction of the polished rod section 42 of the bolt positioning pin 4, and the problem that large internal stress is generated due to the fact that the thermal expansion amount of parts is not matched and the parts are restrained by radial rabbets in the traditional scheme is solved.
Based on the above-described connection structure between turbine casings, a second aspect of the present application provides a connection method between turbine casings, including:
determining the axial and circumferential relative positions of a turbine inner layer casing 1 and a casing support ring 3;
secondly, screwing the bolt positioning pin 4 into a bolt hole of the casing support ring 3, and simultaneously inserting a polished rod section 42 of the bolt positioning pin 4 into a polished hole of the boss 11 of the turbine inner-layer casing 1, so that the turbine inner-layer casing 1 and the casing support ring 3 are connected into an integral assembly through the bolt positioning pin 4;
and step three, connecting the casing support ring 3 with the outer casing 2 of the turbine through a bolt assembly.
According to the connecting structure and method between the turbine casings, the turbine inner casing can radially and freely expand along the bolt positioning pin, the problem that large internal stress is generated due to the fact that thermal expansion of parts is not matched and the parts are restrained by the radial seam allowance in the traditional scheme is solved, the service life of the parts is prolonged, and the connecting structure and method are simple in structure, reliable in connection, low in cost and high in engineering application value.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A connecting structure between turbine casings, characterized by comprising:
the turbine inner layer casing (1), the outer wall of the turbine inner layer casing (1) is provided with a plurality of bosses (11) along the circumferential direction, and the bosses (11) are provided with unthreaded holes;
the outer-layer turbine casing (2) is sleeved on the outer side of the inner-layer turbine casing (1), and the outer-layer turbine casing (2) is provided with a mounting edge;
the cross section of the casing support ring (3) is L-shaped, the casing support ring (3) comprises a first support ring and a second support ring which are integrally formed, the first support ring is provided with a radial bolt hole matched with the boss (11), and the second support ring is connected with the mounting edge of the outer casing (2) of the turbine through a plurality of bolt assemblies which are circumferentially arranged;
bolt locating pin (4), bolt locating pin (4) are including screw thread section (41) and polished rod section (42), bolt locating pin (4) pass behind the bolt hole on the first support ring with boss (11) cooperation, wherein, screw thread section (41) with the bolt hole spiro union of first supporting tube, polished rod section (42) hold in the unthreaded hole of boss (11).
2. The connection between turbine casings according to claim 1, characterized in that the second support ring is positioned radially spigot from the mounting edge of the outer turbine casing (2).
3. The connection structure between turbine casings according to claim 1, wherein the boss (11) and the bolt holes on the first support ring are uniformly arranged in the circumferential direction.
4. The connection structure between turbine casings as claimed in claim 1, wherein the outer wall of the turbine inner casing (1) is provided with a plurality of rows of bosses (11) in the axial direction, each row of bosses (11) includes a plurality of circumferentially arranged bosses, and the bolt holes on the first support ring are opened in a plurality of rows in the axial direction, each row of bolt holes includes a plurality of circumferentially arranged bolts holes.
5. The connection structure between turbine casings according to claim 4, wherein the outer wall of the turbine inner casing (1) is provided with two rows of bosses (11) in the axial direction, each row of bosses (11) includes a plurality of circumferentially arranged bosses, the bolt holes on the first support ring are axially opened in two rows, and each row of bolt holes includes a plurality of circumferentially arranged bosses.
6. The connection structure between turbine casings according to claim 1, characterized in that a predetermined gap is provided between the end face of the boss (11) and the first support ring, and a predetermined gap is provided between the end of the polished rod section (42) of the bolt positioning pin (4) and the bottom end of the polished hole of the boss (11).
7. A method of connecting between turbine casings according to any one of claims 1 to 6, characterized by comprising:
determining the axial and circumferential relative positions of a turbine inner layer casing (1) and a casing support ring (3);
secondly, screwing the bolt positioning pin (4) into a bolt hole of the casing support ring (3), and simultaneously inserting a polished rod section (42) of the bolt positioning pin (4) into a polished hole of a boss (11) of the turbine inner-layer casing (1) so that the turbine inner-layer casing (1) and the casing support ring (3) are connected into an integral assembly through the bolt positioning pin (4);
and thirdly, connecting the casing support ring (3) with the outer casing (2) of the turbine through a bolt assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111342685.4A CN114109539A (en) | 2021-11-12 | 2021-11-12 | Connecting structure and method between turbine casings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111342685.4A CN114109539A (en) | 2021-11-12 | 2021-11-12 | Connecting structure and method between turbine casings |
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| Publication Number | Publication Date |
|---|---|
| CN114109539A true CN114109539A (en) | 2022-03-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111342685.4A Pending CN114109539A (en) | 2021-11-12 | 2021-11-12 | Connecting structure and method between turbine casings |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203050809U (en) * | 2012-12-27 | 2013-07-10 | 中国燃气涡轮研究院 | Connecting structure of gas turbine engine case and outer ring |
| CN203476509U (en) * | 2013-08-22 | 2014-03-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Ejector of combustion gas turbine |
| CN205330743U (en) * | 2015-11-19 | 2016-06-22 | 中国燃气涡轮研究院 | Turbine middle level machine casket |
| CN107476885A (en) * | 2017-09-15 | 2017-12-15 | 中国科学院工程热物理研究所 | The structure of inner and outer ring casing compatible deformation under a kind of achievable hot environment |
| CN107882599A (en) * | 2017-11-01 | 2018-04-06 | 中国航发湖南动力机械研究所 | Monoblock type turbine outer ring attachment structure and turbogenerator |
| CN113062781A (en) * | 2021-05-06 | 2021-07-02 | 中国航发湖南动力机械研究所 | Centering and positioning structure for CMC gas turbine outer ring |
-
2021
- 2021-11-12 CN CN202111342685.4A patent/CN114109539A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203050809U (en) * | 2012-12-27 | 2013-07-10 | 中国燃气涡轮研究院 | Connecting structure of gas turbine engine case and outer ring |
| CN203476509U (en) * | 2013-08-22 | 2014-03-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Ejector of combustion gas turbine |
| CN205330743U (en) * | 2015-11-19 | 2016-06-22 | 中国燃气涡轮研究院 | Turbine middle level machine casket |
| CN107476885A (en) * | 2017-09-15 | 2017-12-15 | 中国科学院工程热物理研究所 | The structure of inner and outer ring casing compatible deformation under a kind of achievable hot environment |
| CN107882599A (en) * | 2017-11-01 | 2018-04-06 | 中国航发湖南动力机械研究所 | Monoblock type turbine outer ring attachment structure and turbogenerator |
| CN113062781A (en) * | 2021-05-06 | 2021-07-02 | 中国航发湖南动力机械研究所 | Centering and positioning structure for CMC gas turbine outer ring |
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