CN111550435A - Multistage rotor disk connection structure - Google Patents
Multistage rotor disk connection structure Download PDFInfo
- Publication number
- CN111550435A CN111550435A CN202010451068.7A CN202010451068A CN111550435A CN 111550435 A CN111550435 A CN 111550435A CN 202010451068 A CN202010451068 A CN 202010451068A CN 111550435 A CN111550435 A CN 111550435A
- Authority
- CN
- China
- Prior art keywords
- stage
- connecting edge
- edge
- annular connecting
- rotor disk
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
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
- F04D29/26—Rotors specially for elastic fluids
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
-
- 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
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/233—Electron beam welding
Landscapes
- 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 aero-engine compressor rotor disc connection design, concretely relates to multistage rotor disc connection structure, include: the outer edge of one side of the preceding-stage rotor wheel disc is provided with an annular connecting bulge which forms a preceding-stage annular connecting edge; the outer edge of one side of the rear-stage rotor wheel disc is provided with an annular connecting bulge which forms a rear-stage drum connecting edge; the connecting edge of the rear-stage drum barrel is butted with the annular connecting edge of the front-stage drum barrel; the butt joint part between the connecting edge of the rear-stage drum barrel and the annular connecting edge of the front-stage drum barrel is connected through electron beam welding.
Description
Technical Field
The application belongs to the technical field of aero-engine compressor rotor disc connection design, and particularly relates to a multistage rotor disc connection structure.
Background
The rotor discs at all levels in the air compression of the aero-engine are connected through the drum, the connecting parts of the drum and the rotor discs are mostly connected through bolts and centered through interference rabbets, and the specific structure can be seen in figure 1.
The technical scheme that the connecting part of the existing drum barrel and the rotor wheel disc is centered through an interference seam allowance is characterized in that the requirements on tolerance size and assembly precision are strict, the prior art is difficult to guarantee the machining tolerance of the drum barrel and the rotor wheel disc thereof, the assembly precision between the drum barrel and the rotor wheel disc is also difficult to guarantee under the condition of over-poor machining, a multi-stage rotor wheel disc exists in the compressor, the size between the one-stage rotor wheel disc and the drum barrel is over-poor, the assembly is not in place, the assembly between the rotor wheel disc and the drum barrel at each stage is easy to influence, larger stress exists between the rotor wheel disc and the drum barrel, the vibration of a rotor part in the working process of the compressor is easy to aggravate, the working environment of a front. In addition, the connecting part of the existing drum and the rotor disc is connected through bolts, the assembling process is complicated, the connecting edge for assembling the bolts needs to be additionally designed, and the weight of the rotor part of the gas compressor is increased.
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 multi-stage rotor disk connection structure that overcomes or alleviates at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
a multi-stage rotor disk connection comprising:
the outer edge of one side of the preceding-stage rotor wheel disc is provided with an annular connecting bulge which forms a preceding-stage annular connecting edge;
the outer edge of one side of the rear-stage rotor wheel disc is provided with an annular connecting bulge which forms a rear-stage drum connecting edge; the connecting edge of the rear-stage drum barrel is butted with the annular connecting edge of the front-stage drum barrel; the butt joint part between the connecting edge of the rear-stage drum barrel and the annular connecting edge of the front-stage drum barrel is connected through electron beam welding.
According to at least one embodiment of the present application, in the above-mentioned multistage rotor disk connection structure, an inner side of the preceding stage rotor disk, which is opposite to the preceding stage annular connection side, is connected with the preceding stage rotor journal; the inner wall of the backing rotor shaft neck is used for being connected with the outer ring of the backing bearing of the backing rotor.
According to at least one embodiment of the present application, the multistage rotor disk connection structure described above has a plurality of through holes in the preceding stage rotor journal.
According to at least one embodiment of the present application, in the multi-stage rotor disk connection structure, an outer edge of a side of the rear-stage rotor disk, which is opposite to a connection edge of the rear-stage drum, is connected with a rear-stage rotor journal; the inner wall of the rear-stage rotor journal is used for being connected with the outer ring of the rear-stage rotor support bearing.
According to at least one embodiment of the present application, the multi-stage rotor disk connection structure has a plurality of through holes on the rear stage rotor journal.
According to at least one embodiment of the present application, the above multistage rotor disk connection structure further includes:
the outer edge of one side of the middle rotor wheel disc is provided with an annular connecting bulge, and the annular bulge forms a middle drum connecting edge; the connecting edge of the middle drum barrel is butted with the annular connecting edge of the preceding stage; the butt joint part between the connecting edge of the middle drum and the annular connecting edge of the front stage is welded and connected through an electron beam; the outer edge of the other side of the middle rotor wheel disc is provided with an annular connecting bulge which forms a middle annular connecting edge; the middle annular connecting edge is butted with the connecting edge of the rear-stage drum barrel; the middle annular connecting edge is connected with the butt joint part of the connecting edge of the rear-stage drum barrel through electron beam welding.
The application has at least the following beneficial technical effects:
the connecting structure of the multistage rotor disk can be applied to a compressor rotor part, the connecting edges of a rear-stage drum barrel on a front-stage rotor disk and the rear-stage drum barrel on the rear-stage rotor disk are connected in a welding mode, namely, the rotor disk and the drum barrel are connected in a welding mode instead of a bolt connection mode in the compressor rotor part, the stress between the rotor disk and the drum barrel can be reduced, the vibration of the rotor part in the starting working process caused by inaccurate size matching between the rotor disk and the drum barrel can be effectively overcome, the assembling is easy, the connecting edges for assembling bolts do not need to be additionally arranged, and the weight of the compressor rotor part can be relatively reduced. In addition, the multistage rotor disk connection structure that this application provided designs on the preceding stage rotor disk have with the preceding stage annular connection limit of the last butt joint of last back stage drum barrel connection limit of back stage rotor disk, can be convenient for realize the welded connection of back stage drum barrel connection limit and preceding stage rotor disk.
Drawings
FIG. 1 is a schematic illustration of a prior art multi-stage rotor disk attachment configuration provided by an embodiment of the present application;
FIG. 2 is a schematic view of a multi-stage rotor disk attachment configuration provided by an embodiment of the present application;
FIG. 3 is a schematic view of part A of FIG. 2;
FIG. 4 is a partial schematic view B of FIG. 2;
wherein:
1-a preceding stage rotor disk; 2-preceding stage annular connecting edge; 3-a rear-stage rotor disk; 4-a rear-stage drum connecting edge; 5-preceding stage rotor journal; 6-rear stage rotor journal; 7-an intermediate rotor disk; 8-intermediate drum connecting edge; 9-middle annular connecting edge.
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 to 4.
A multi-stage rotor disk connection comprising:
the front-stage rotor disk 1 is provided with an annular connecting bulge at the outer edge of one side, and the annular connecting bulge forms a front-stage annular connecting edge 2;
a rear-stage rotor wheel disc 3, one side of which has an annular connecting bulge, and the annular connecting bulge forms a rear-stage drum connecting edge 4; the connecting edge 4 of the rear-stage drum barrel is butted with the annular connecting edge 2 of the front-stage drum barrel; the butt joint part between the rear-stage drum connecting edge 4 and the front-stage annular connecting edge 2 is connected through electron beam welding.
For the multi-stage rotor disk connection structure disclosed in the above embodiments, those skilled in the art can understand that the front-stage rotor disk 1 and the rear-stage drum connecting edge 4 on the rear-stage rotor disk 3 are designed in the compressor rotor component and connected in a welding manner, that is, the rotor disk and the drum are connected in a welding manner instead of a bolt connection manner in the compressor rotor component, so that the stress therebetween can be reduced, the vibration of the rotor component in the starting operation process caused by inaccurate size matching between the rotor disk and the drum can be effectively overcome, the assembly is easy, the additional arrangement of the connecting edge for assembling bolts is not required, and the weight of the compressor rotor component can be relatively reduced.
For the multi-stage rotor disk connection structure disclosed in the above embodiments, it can be further understood by those skilled in the art that the front-stage rotor disk 1 is designed to have a front-stage annular connection edge butted with the rear-stage drum connection edge 4 on the rear-stage rotor disk 3, so that the welding connection between the rear-stage drum connection edge 4 and the front-stage rotor disk 1 can be conveniently realized.
In some optional embodiments, in the above-mentioned multi-stage rotor disk connecting structure, a preceding stage rotor journal 5 is connected to the inner side of the preceding stage rotor disk 1 facing away from the preceding stage annular connecting edge 2; the inner wall of the backing rotor journal 5 is adapted to be connected to the outer race of the backing rotor bearing.
In some alternative embodiments, the multi-stage disk connection structure described above has a plurality of through holes in the preceding stage rotor journal 5.
In some optional embodiments, in the multi-stage rotor disk connection structure, the outer edge of the rear-stage rotor disk 3 on the side opposite to the rear-stage drum connection edge 4 is connected with the rear-stage rotor journal 6; the inner wall of the rear stage rotor journal 6 is used for connecting with the outer ring of the rear stage rotor support bearing.
For the multi-stage rotor disk connection structure disclosed in the above embodiment, it can be understood by those skilled in the art that end surfaces matched with the front-stage rotor support bearing and the rear-stage rotor support bearing may be designed on the front-stage rotor journal 5 and the rear-stage rotor journal 6, respectively, for axially positioning each stage of the rotor disk.
In some alternative embodiments, the multi-stage disk connection structure has a plurality of through holes on the rotor journal 6 of the rear stage.
In some optional embodiments, the multi-stage rotor disk connecting structure further includes:
an intermediate rotor disk 7, one side of which has an annular coupling projection on its outer edge, which annular projection forms an intermediate drum coupling edge 8; the middle drum connecting edge 8 is butted with the preceding stage annular connecting edge 2; the butt joint part between the middle drum connecting edge 8 and the preceding stage annular connecting edge 2 is welded and connected through electron beams; the outer edge of the other side of the middle rotor disk 7 is provided with an annular connecting bulge which forms a middle annular connecting edge 9; the middle annular connecting edge 9 is butted with the connecting edge 4 of the rear-stage drum barrel; the middle annular connecting edge 9 is connected with the butt joint part of the connecting edge 4 of the rear-stage drum barrel through electron beam welding.
For the multi-stage rotor disk connection structure disclosed in the above embodiment, those skilled in the art can understand that a plurality of intermediate rotor disks 7 may be provided between the front stage rotor disk 1 and the rear stage rotor disk 3, and the intermediate rotor disks are connected in this manner, so that the stress between the rotor disk and the drum can be effectively reduced, the vibration of the rotor component during the starting operation process caused by inaccurate size matching between the rotor disk and the drum can be effectively overcome, the assembly is easy, a connection edge for assembling bolts is not required to be additionally provided, and the weight of the rotor component of the compressor can be relatively reduced.
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. A multi-stage rotor disk connection structure, comprising:
the front-stage rotor disk (1) is provided with an annular connecting bulge at the outer edge of one side, and the annular connecting bulge forms a front-stage annular connecting edge (2);
the outer edge of one side of the rear-stage rotor wheel disc (3) is provided with an annular connecting bulge which forms a rear-stage drum connecting edge (4); the rear-stage drum connecting edge (4) is butted with the front-stage annular connecting edge (2); the butt joint part between the rear-stage drum barrel connecting edge (4) and the front-stage annular connecting edge (2) is connected through electron beam welding.
2. The multi-stage rotor disk connection structure of claim 1,
the inner side of one side of the preceding-stage rotor wheel disc (1), which is back to the preceding-stage annular connecting edge (2), is connected with a preceding-stage rotor shaft neck (5); the inner wall of the backing stage rotor journal (5) is used for being connected with the outer ring of the backing bearing of the backing stage rotor.
3. The multi-stage rotor disk connection structure of claim 2,
the preceding stage rotor journal (5) is provided with a plurality of through holes.
4. The multi-stage rotor disk connection structure of claim 2,
the outer edge of one side of the rear-stage rotor wheel disc (3), which is back to the connecting edge (4) of the rear-stage drum barrel, is connected with a rear-stage rotor shaft neck (6); the inner wall of the rear-stage rotor journal (6) is used for being connected with the outer ring of the rear-stage rotor supporting bearing.
5. The multi-stage rotor disk connection structure of claim 4,
the rear-stage rotor journal (6) is provided with a plurality of through holes.
6. The multi-stage rotor disk connection structure of claim 1,
further comprising:
an intermediate rotor disk (7) having an annular connecting projection on one outer edge, the annular projection forming an intermediate drum connecting edge (8); the middle drum connecting edge (8) is butted with the preceding stage annular connecting edge (2); the butt joint part between the middle drum connecting edge (8) and the preceding stage annular connecting edge (2) is connected through electron beam welding; the outer edge of the other side of the middle rotor disk (7) is provided with an annular connecting bulge which forms a middle annular connecting edge (9); the middle annular connecting edge (9) is butted with the connecting edge (4) of the rear drum; the middle annular connecting edge (9) is connected with the butt joint part of the connecting edge (4) of the rear-stage drum barrel through electron beam welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010451068.7A CN111550435A (en) | 2020-05-25 | 2020-05-25 | Multistage rotor disk connection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010451068.7A CN111550435A (en) | 2020-05-25 | 2020-05-25 | Multistage rotor disk connection structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111550435A true CN111550435A (en) | 2020-08-18 |
Family
ID=71996967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010451068.7A Pending CN111550435A (en) | 2020-05-25 | 2020-05-25 | Multistage rotor disk connection structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111550435A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113606000A (en) * | 2021-07-28 | 2021-11-05 | 中国科学院工程热物理研究所 | Disc rotor system with vibration damping and weight reducing functions |
| CN114017385A (en) * | 2021-11-05 | 2022-02-08 | 中国航发沈阳发动机研究所 | Multistage rotor torque transmission structure in gas compressor |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3625634A (en) * | 1969-12-10 | 1971-12-07 | Gen Motors Corp | Turbomachine rotor |
| CN1474034A (en) * | 2003-07-16 | 2004-02-11 | 沈阳黎明航空发动机（集团）有限责任 | Heavy gas turbine |
| CN1514110A (en) * | 2003-07-16 | 2004-07-21 | 沈阳黎明航空发动机（集团）有限责任 | High efficiency compressor for gas turbine |
| DE102010001329A1 (en) * | 2010-01-28 | 2011-08-18 | Rolls-Royce Deutschland Ltd & Co KG, 15827 | Method for welding rotor disc of axial fluid flow machine e.g. gas turbine, involves checking quality of friction weld between intermediate elements, and welding intermediate elements with respective rotor discs |
| CN202266495U (en) * | 2011-07-19 | 2012-06-06 | 中航商用航空发动机有限责任公司 | Central draw bar type high pressure compressor rotor |
| CN202833300U (en) * | 2012-08-28 | 2013-03-27 | 中国航空动力机械研究所 | Gas compressor axial impeller unit |
| CN205001254U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Rotor blade dish, compressor and aeroengine |
| CN110566515A (en) * | 2019-09-22 | 2019-12-13 | 中国航发沈阳发动机研究所 | gas-entraining structure on inner side of gas compressor |
| CN110977131A (en) * | 2019-11-25 | 2020-04-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Electron beam welding deformation precise control method for rotor parts |
| CN111515513A (en) * | 2020-04-03 | 2020-08-11 | 中国航发哈尔滨东安发动机有限公司 | Welding method of high-temperature alloy drum barrel rotor assembly |
-
2020
- 2020-05-25 CN CN202010451068.7A patent/CN111550435A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3625634A (en) * | 1969-12-10 | 1971-12-07 | Gen Motors Corp | Turbomachine rotor |
| CN1474034A (en) * | 2003-07-16 | 2004-02-11 | 沈阳黎明航空发动机（集团）有限责任 | Heavy gas turbine |
| CN1514110A (en) * | 2003-07-16 | 2004-07-21 | 沈阳黎明航空发动机（集团）有限责任 | High efficiency compressor for gas turbine |
| DE102010001329A1 (en) * | 2010-01-28 | 2011-08-18 | Rolls-Royce Deutschland Ltd & Co KG, 15827 | Method for welding rotor disc of axial fluid flow machine e.g. gas turbine, involves checking quality of friction weld between intermediate elements, and welding intermediate elements with respective rotor discs |
| CN202266495U (en) * | 2011-07-19 | 2012-06-06 | 中航商用航空发动机有限责任公司 | Central draw bar type high pressure compressor rotor |
| CN202833300U (en) * | 2012-08-28 | 2013-03-27 | 中国航空动力机械研究所 | Gas compressor axial impeller unit |
| CN205001254U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Rotor blade dish, compressor and aeroengine |
| CN110566515A (en) * | 2019-09-22 | 2019-12-13 | 中国航发沈阳发动机研究所 | gas-entraining structure on inner side of gas compressor |
| CN110977131A (en) * | 2019-11-25 | 2020-04-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Electron beam welding deformation precise control method for rotor parts |
| CN111515513A (en) * | 2020-04-03 | 2020-08-11 | 中国航发哈尔滨东安发动机有限公司 | Welding method of high-temperature alloy drum barrel rotor assembly |
Non-Patent Citations (1)
| Title |
|---|
| 单冬敏、张兰芳、杨化书: "《机械制造基础》", 31 January 2009, 郑州：黄河水利出版社 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113606000A (en) * | 2021-07-28 | 2021-11-05 | 中国科学院工程热物理研究所 | Disc rotor system with vibration damping and weight reducing functions |
| CN113606000B (en) * | 2021-07-28 | 2023-03-14 | 中国科学院工程热物理研究所 | Disc rotor system with vibration damping and weight reducing functions |
| CN114017385A (en) * | 2021-11-05 | 2022-02-08 | 中国航发沈阳发动机研究所 | Multistage rotor torque transmission structure in gas compressor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111550435A (en) | Multistage rotor disk connection structure | |
| JP4918263B2 (en) | Stator blade ring of axial compressor | |
| US9638062B2 (en) | Geared turbofan engine with integral gear and bearing supports | |
| CN106368742A (en) | Method and system for interfacing a ceramic matrix composite component to a metallic component | |
| CN1776200B (en) | Method for making a repaired turbine engine stationary vane assembly and repaired assembly | |
| CN111664124B (en) | Stator structure, rotor and stator assembly structure with same and assembly method of rotor and stator assembly structure | |
| JP2004197742A (en) | Variable vane arm/unison ring attachment system | |
| WO2011058844A1 (en) | In-wheel motor driving device | |
| CN111561394B (en) | Structure of engine air inlet casing and assembling method thereof | |
| US10808561B2 (en) | Seal arrangement for a turbomachine, method for manufacturing a seal arrangement and turbomachine | |
| US20190249682A1 (en) | Modular turbo compressor shaft | |
| CN103161855A (en) | Composite disc rotor | |
| JP2007132348A (en) | Device conveying steam to turbine and double-flow steam turbine having the device | |
| CN111577462A (en) | Engine air inlet frame | |
| CN111664123A (en) | Stator structure and machining and assembling method thereof | |
| CN115030778A (en) | Connection structure and connection method of turbine disc and blades of aircraft engine | |
| CN114352414A (en) | Aeroengine air inlet casing structure | |
| CN104471212A (en) | First stage compressor disk configured for balancing the compressor rotor assembly | |
| JP2015520336A (en) | Exhaust gas turbocharger | |
| JP2006200363A (en) | Hermetic compressor | |
| US20190136705A1 (en) | Sealing assembly for a fluid kinetic machine, method for producing a sealing assembly as well as fluid kinetic machine | |
| JPH10299681A (en) | Fluid machine | |
| CN111561481A (en) | Stator cartridge receiver structure | |
| CN101131092A (en) | Methods and apparatus for fabricating a rotor for a steam turbine | |
| US8944752B2 (en) | Compressor rectifier architecture |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200818 |