CN111577652B - Drum barrel structure and compressor rotor disc connecting structure thereof - Google Patents
Drum barrel structure and compressor rotor disc connecting structure thereof Download PDFInfo
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- CN111577652B CN111577652B CN202010394477.8A CN202010394477A CN111577652B CN 111577652 B CN111577652 B CN 111577652B CN 202010394477 A CN202010394477 A CN 202010394477A CN 111577652 B CN111577652 B CN 111577652B
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- drum
- stage rotor
- rotor disk
- barrel
- compressor rotor
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- 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
- F04D29/26—Rotors specially for elastic fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to the technical field of design is connected to compressor rotor disc, concretely relates to compressor rotor disc connection structure, include: a preceding stage rotor disk; the rear-stage rotor disk is adjacent to the front-stage rotor disk; the outer drum is arranged between the front-stage rotor wheel disc and the rear-stage rotor wheel disc, one end of the outer drum is connected with the front-stage rotor wheel disc, and the other end of the outer drum is connected with the rear-stage rotor wheel disc; and the inner side drum barrel is arranged on the inner side of the outer side drum barrel, one end of the inner side drum barrel is connected with the front-stage rotor wheel disc, and the other end of the inner side drum barrel is connected with the rear-stage rotor wheel disc. In addition, the drum structure comprises an outer drum and an inner drum in the compressor rotor disc connecting structure.
Description
Technical Field
The application belongs to the technical field of connection design of compressor rotor discs, and particularly relates to a drum structure and a compressor rotor disc connection structure thereof.
Background
The compressor is a main part of an aeroengine and a gas turbine, adjacent two-stage rotor discs of the compressor are mostly connected by a drum, the existing drum is mostly of a single-layer structure, the strength reserve, particularly the circumferential stress reserve, of the drum is limited by the performance of the current material, the compressor is difficult to adapt to the working environment with high rotating speed and high temperature of a rotor system of the compressor, the improvement of the performance of the rotor system of the compressor is limited, and the compressor can be damaged seriously so as to cause disastrous results.
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 patent application.
Disclosure of Invention
It is an object of the present application to provide a drum arrangement and a compressor rotor disk attachment arrangement therefor that overcomes or mitigates at least one of the known disadvantages.
The technical scheme of the application is as follows:
one aspect provides a compressor rotor disk connection structure, including:
a preceding stage rotor disk;
the rear-stage rotor disk is adjacent to the front-stage rotor disk;
the outer drum is arranged between the front-stage rotor wheel disc and the rear-stage rotor wheel disc, one end of the outer drum is connected with the front-stage rotor wheel disc, and the other end of the outer drum is connected with the rear-stage rotor wheel disc;
and the inner side drum barrel is arranged on the inner side of the outer side drum barrel, one end of the inner side drum barrel is connected with the front-stage rotor wheel disc, and the other end of the inner side drum barrel is connected with the rear-stage rotor wheel disc.
According to at least one embodiment of the application, in the compressor rotor disc connecting structure, one end of the outer drum connected with the preceding stage rotor disc is the front end of the outer drum, and one end connected with the subsequent stage rotor disc is the rear end of the outer drum;
the end of the inner drum connected with the preceding-stage rotor wheel disc is the front end of the inner drum, and the end connected with the rear-stage rotor wheel disc is the rear end of the inner drum; wherein, the front end of the inner drum barrel is connected with the front end of the outer drum barrel; the rear end of the inner drum barrel is connected with the rear end of the outer drum barrel.
According to at least one embodiment of the present application, in the compressor rotor disk attachment structure, the outer drum projects away from the inner drum.
According to at least one embodiment of the present application, in the compressor rotor disk attachment structure, the inner drum projects away from the outer drum.
According to at least one embodiment of the application, in the compressor rotor disk connecting structure, an outer side drum is provided with an outer side circulating hole;
the inside drum has inside flow holes.
According to at least one embodiment of the application, in the compressor rotor disk connecting structure, the outer drum and the inner drum are integrally formed.
According to at least one embodiment of the application, in the compressor rotor disk connecting structure, the outer drum and the inner drum are manufactured through an additive process.
In another aspect, a drum structure is provided, which includes an outer drum and an inner drum in any of the above compressor rotor disk connection structures.
The application has at least the following beneficial effects:
on the one hand, the compressor rotor disk connecting structure is provided, the front-stage rotor disk and the rear-stage rotor disk which are adjacent in front and back are designed to be connected through a double-layer drum barrel structure consisting of an outer-side drum barrel and an inner-side drum barrel, and the double-layer drum barrel structure can effectively reduce circumferential stress under the same working condition compared with the existing single-layer drum barrel structure, so that the compressor rotor disk connecting structure has relatively large strength reserve, is suitable for the working environment with high rotating speed and high temperature of a current compressor rotor system, avoids being damaged, and effectively ensures the performance of the compressor rotor system.
On the other hand, the drum structure comprises an outer drum and an inner drum in the compressor rotor disk connecting structure, wherein the outer drum and the inner drum form a double-layer drum structure which is used for connecting a front-stage rotor disk and a rear-stage rotor disk which are adjacent in a front-and-rear direction.
Drawings
FIG. 1 is a schematic view of a compressor rotor disk connection structure provided by an embodiment of the application;
FIG. 2 is a schematic diagram of a comparison of circumferential stress of a compressor rotor disk connection structure provided by an embodiment of the application and a conventional compressor rotor disk connection structure;
wherein:
1-a preceding stage rotor disk; 2-a rear-stage rotor disk; 3-an outer drum; 4-an inner drum; 5-rotor blades.
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 use of the terms "comprising" or "including" and the like in the description of the present application is intended to indicate that the element or item preceding the term covers the element or item listed after the term and its equivalents, without excluding 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. 1-2.
One aspect provides a compressor rotor disk connection structure, including:
a preceding stage rotor disk 1;
the rear-stage rotor disk 2 is adjacent to the front-stage rotor disk 1;
the outer drum barrel 3 is arranged between the front-stage rotor disk 1 and the rear-stage rotor disk 2, one end of the outer drum barrel is connected with the front-stage rotor disk 1, and the other end of the outer drum barrel is connected with the rear-stage rotor disk 2;
and the inner drum barrel 4 is arranged on the inner side of the outer drum barrel 3, one end of the inner drum barrel is connected with the front-stage rotor disk 1, and the other end of the inner drum barrel is connected with the rear-stage rotor disk 2.
For the compressor rotor disk connecting structure disclosed in the above embodiment, as can be understood by those skilled in the art, the front-stage rotor disk 1 and the rear-stage rotor disk 2 adjacent to each other in front and rear are designed to be connected by a double-layer drum structure consisting of the outer drum 3 and the inner drum 4, and the double-layer drum structure can effectively reduce circumferential stress under the same working condition compared with the existing single-layer drum structure, so that the double-layer drum structure has relatively large strength reserve, is suitable for the working environment of high rotating speed and high temperature of the compressor rotor system, avoids being damaged, and effectively ensures the performance of the compressor rotor system.
In some optional embodiments, in the compressor rotor disc connecting structure, one end of the outer drum 3 connected to the preceding-stage rotor disc 1 is a front end of the outer drum, and one end connected to the subsequent-stage rotor disc 2 is a rear end of the outer drum;
one end of the inner drum barrel 4 connected with the front-stage rotor wheel disc 1 is the front end of the inner drum barrel, and the other end connected with the rear-stage rotor wheel disc 2 is the rear end of the inner drum barrel; wherein, the front end of the inner drum barrel is connected with the front end of the outer drum barrel; the rear end of the inner drum barrel is connected with the rear end of the outer drum barrel.
For the compressor rotor disk connection structure disclosed in the above embodiment, it can be understood by those skilled in the art that the front and rear ends of the outer drum 3 and the inner drum 4 are designed to be correspondingly connected to form an integral structure, so as to have better structural stability and facilitate the connection with the front-stage rotor disk 1 and the rear-stage rotor disk 2.
In some alternative embodiments, in the above compressor rotor disk connecting structure, the outer drum 3 protrudes away from the inner drum 4; and/or the inner drum 4 is convex away from the outer drum 3.
For the compressor rotor disk connection structure disclosed in the above embodiments, it can be understood by those skilled in the art that the outer drum 3 protrudes in a direction away from the inner drum 4 or the inner drum 4 protrudes in a direction away from the outer drum 3, so that a larger space is provided between the outer drum 3 and the inner drum 4, and a double-layer drum structure composed of the outer drum 3 and the inner drum 4 can further effectively reduce circumferential stress, thereby having a larger strength reserve.
In some alternative embodiments, in the compressor rotor disk connection structure, the outer drum 3 has an outer flow hole;
the inside drum 4 has inside flow holes.
For the compressor rotor disk connecting structure disclosed in the above embodiment, as can be understood by those skilled in the art, the gas in the dead cavity between the structures can repeatedly impact the structures, and low cycle fatigue is easily caused, so as to cause bulging, and even break the structures.
In some alternative embodiments, the compressor rotor disk connecting structure is formed by integrally forming the outer drum 3 and the inner drum 4.
In some alternative embodiments, the compressor rotor disk connecting structure is formed by manufacturing the outer drum 3 and the inner drum 4 in an additive process.
On the other hand, the drum structure comprises an outer drum 3 and an inner drum 4 in any one of the compressor rotor disc connecting structures, wherein the outer drum 3 and the inner drum 4 form a double-layer drum structure which is used for connecting the front-stage rotor disc 1 and the rear-stage rotor disc 2 which are adjacent to each other in the front and the rear, and compared with the existing single-layer drum structure, the drum structure can effectively reduce circumferential stress under the same working condition, so that the drum structure has relatively large strength reserve, is suitable for the working environment with high rotating speed and high temperature of a compressor rotor system, avoids being damaged, and effectively ensures the performance of the compressor rotor system.
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 (7)
1. A compressor rotor disk connection structure, comprising:
a preceding stage rotor disk (1);
the rear-stage rotor disk (2) is adjacent to the front-stage rotor disk (1);
the outer drum barrel (3) is arranged between the front-stage rotor disc (1) and the rear-stage rotor disc (2), one end of the outer drum barrel is connected with the front-stage rotor disc (1), and the other end of the outer drum barrel is connected with the rear-stage rotor disc (2);
the inner drum barrel (4) is arranged on the inner side of the outer drum barrel (3), one end of the inner drum barrel is connected with the front-stage rotor wheel disc (1), and the other end of the inner drum barrel is connected with the rear-stage rotor wheel disc (2);
the end of the outer drum (3) connected with the front-stage rotor disc (1) is the front end of the outer drum, and the end connected with the rear-stage rotor disc (2) is the rear end of the outer drum;
the end of the inner drum (4) connected with the preceding-stage rotor disc (1) is the front end of the inner drum, and the end connected with the rear-stage rotor disc (2) is the rear end of the inner drum; wherein the front end of the inner drum is connected with the front end of the outer drum; the rear end of the inner drum barrel is connected with the rear end of the outer drum barrel.
2. The compressor rotor disk attachment structure of claim 1,
the outer drum (3) protrudes in a direction away from the inner drum (4).
3. The compressor rotor disk attachment structure of claim 1,
the inner drum (4) protrudes in a direction away from the outer drum (3).
4. The compressor rotor disk attachment structure according to any one of claims 2 to 3,
the outer drum (3) is provided with an outer circulation hole;
the inner drum (4) is provided with inner side circulation holes.
5. The compressor rotor disk attachment structure of claim 4,
the outer side drum barrel (3) and the inner side drum barrel (4) are integrally formed.
6. The compressor rotor disk attachment structure of claim 5,
the outer drum (3), the inner drum (4) are manufactured in an additive process.
7. A drum structure, characterized by comprising an outer drum (3) and an inner drum (4) in a compressor rotor disk attachment structure according to any one of claims 1 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010394477.8A CN111577652B (en) | 2020-05-11 | 2020-05-11 | Drum barrel structure and compressor rotor disc connecting structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010394477.8A CN111577652B (en) | 2020-05-11 | 2020-05-11 | Drum barrel structure and compressor rotor disc connecting structure thereof |
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| Publication Number | Publication Date |
|---|---|
| CN111577652A CN111577652A (en) | 2020-08-25 |
| CN111577652B true CN111577652B (en) | 2021-09-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010394477.8A Active CN111577652B (en) | 2020-05-11 | 2020-05-11 | Drum barrel structure and compressor rotor disc connecting structure thereof |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2681374B1 (en) * | 1991-09-18 | 1993-11-19 | Snecma | FIXING OF A TURBOREACTOR BLOWER BLADE. |
| DE102012100628A1 (en) * | 2012-01-25 | 2013-07-25 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Paddle wheel with intumescent coating |
| CN203584577U (en) * | 2013-12-11 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Connecting structure of gas compressor and turbine |
| CN205423303U (en) * | 2015-12-14 | 2016-08-03 | 中国燃气涡轮研究院 | Compressor drum barrel with bifurcation structure |
| CN106194828A (en) * | 2016-07-12 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of bleed structure for compressor rotor inner chamber |
| CN109538525A (en) * | 2017-09-21 | 2019-03-29 | 中国航发商用航空发动机有限责任公司 | Big Bypass Ratio Turbofan Engine and aero-engine compressibility |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10153412A1 (en) * | 2001-10-30 | 2003-05-15 | Bosch Gmbh Robert | Fan attachment with dynamic unbalance compensation |
| CN110094364B (en) * | 2018-01-31 | 2020-05-22 | 中国航发商用航空发动机有限责任公司 | Rotor blade and axial flow compressor |
-
2020
- 2020-05-11 CN CN202010394477.8A patent/CN111577652B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2681374B1 (en) * | 1991-09-18 | 1993-11-19 | Snecma | FIXING OF A TURBOREACTOR BLOWER BLADE. |
| DE102012100628A1 (en) * | 2012-01-25 | 2013-07-25 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Paddle wheel with intumescent coating |
| CN203584577U (en) * | 2013-12-11 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Connecting structure of gas compressor and turbine |
| CN205423303U (en) * | 2015-12-14 | 2016-08-03 | 中国燃气涡轮研究院 | Compressor drum barrel with bifurcation structure |
| CN106194828A (en) * | 2016-07-12 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of bleed structure for compressor rotor inner chamber |
| CN109538525A (en) * | 2017-09-21 | 2019-03-29 | 中国航发商用航空发动机有限责任公司 | Big Bypass Ratio Turbofan Engine and aero-engine compressibility |
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| CN111577652A (en) | 2020-08-25 |
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