CN115263808B - Intermediate casing of integrated double-rotor aircraft engine - Google Patents
Intermediate casing of integrated double-rotor aircraft engine Download PDFInfo
- Publication number
- CN115263808B CN115263808B CN202211186533.4A CN202211186533A CN115263808B CN 115263808 B CN115263808 B CN 115263808B CN 202211186533 A CN202211186533 A CN 202211186533A CN 115263808 B CN115263808 B CN 115263808B
- Authority
- CN
- China
- Prior art keywords
- casing
- rectifier
- compressor
- case
- section
- 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.)
- Active
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
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
-
- 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
- F04D29/601—Mounting; Assembling; Disassembling specially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an intermediate casing of an integrated dual-rotor aero-engine, which belongs to the technical field of an aero-engine casing structure and at least partially solves the technical problems that the structural rigidity is reduced and the number of parts for assembling the whole engine is increased in the installation of the intermediate casing in the prior art. The rectifier installing structure is suitable for installing a rectifier at a fan outlet position, a ring groove which is adaptive to the size of the rectifier is arranged on the inner wall of a front-section outer casing of the intermediate casing, an outward-turned hanging buckle is arranged on one side, close to the ring groove, of the inner wall of the front-section outer casing, and a caulking groove is axially formed in the other side of the ring groove; one side of rectifier be provided with hang the couple of detaining shape looks adaptation, the opposite side embedding the caulking groove just carries out the overlap joint through the mode of tang to pass through the mode of rivet in circumference with intermediary's machine casket carries out circumference fixed, realizes the reduction of whole machine casket weight.
Description
Technical Field
The invention belongs to the technical field of aero-engine casing structures, and particularly relates to an intermediate casing of an integrated dual-rotor aero-engine.
Background
The intermediary machine casket is main load-bearing frame and the assembly benchmark of birotor aeroengine, and the axial load of engine and installation benchmark all act on and arrange in the intermediary machine casket, and the installation form is: the front end of the intermediate casing is connected with the fan casing and the first fulcrum bearing seat through a mounting edge structure form and is used for mounting and fixing components such as a fan outlet rectifier component, a fulcrum bearing, a multifunctional shaft and the like; the rear end of the intermediary casing is connected with the transition section casing, the compressor casing and the like through a mounting edge and is used for mounting and fixing the compressor adjustable blade driving mechanism and the zero-level adjustable blade; the intermediary machine casket is inside to link to each other with second fulcrum bearing frame through the installation limit for fixed fulcrum bearing and transmission bevel gear.
Although the installation mode in the prior art meets the functional requirement of the intermediate bearing frame, the problems are that the connection structure of the engine becomes complicated and the structural rigidity is reduced, so that the number of the assembly parts of the whole machine is increased and the weight of the whole machine is increased.
Disclosure of Invention
In view of the above, the present invention provides an intermediary casing of an integrated dual-rotor aircraft engine, which at least partially solves the technical problems of reduced structural rigidity and a large number of parts for assembling the whole engine in the intermediary casing installation in the prior art.
The intermediate casing of the integrated double-rotor aero-engine is provided, wherein an annular groove which is adaptive to the size of a rectifier is formed in the inner wall of a front-section outer casing of the intermediate casing, an outward-turned hanging buckle is arranged on one side, close to the annular groove, of the inner wall of the front-section outer casing, and an embedding groove is axially formed in the other side of the annular groove; one side of rectifier be provided with hang the couple of detaining shape looks adaptation, the opposite side embedding the caulking groove just carries out the overlap joint through the mode of tang to pass through the mode of rivet in circumference with intermediary receiver carries out circumference and fixes.
The invention has the technical beneficial effects that:
the integral molding of the rectifier case and the front section of the intermediary machine simplifies the installation difficulty of the rectifier, reduces the use of a plurality of groups of flange assemblies on the butt joint surface in the prior art, greatly reduces the specification and the number of the connecting pieces of the whole engine on the whole, and reduces the structural weight of the whole engine. The arrangement of the structure enables the process route to adopt investment precision casting and machining processes, the arrangement of the hanging buckle, the hook and the caulking groove thereof axially fixes the rectifier, the circumferential limiting of the rectifier case is carried out through the rivet, and the fixation of the rectifier and the intermediary case is integrally realized.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of a prior art assembly;
FIG. 2 is a schematic view of the integral molding of the present invention;
FIG. 3 is an enlarged partial view of the rectifier case installation;
wherein: 1. an intermediary case; 2. a first fulcrum bearing block; 3. a rectifier; 4. a rectifier case; 5. a transition section casing; 6. a primary casing of the compressor; 7. zero-order adjustable guide vanes; 8. a zero-level inner ring front-section casing of the compressor; 9. a second fulcrum bearing seat; 10. a first fulcrum bearing; 11. a second fulcrum bearing; 50. a ring groove; 51. caulking grooves; 52. hanging and buckling; 310. a characteristic cylindrical surface; 311. hooking; 401. a first mounting edge; 103. a second mounting edge; 501. a third mounting edge; 104. a fourth mounting edge; 105. a shunt ring; 601. a fifth mounting edge; 700. a sixth mounting edge; 801. a seventh mounting edge; 106. an eighth mounting edge; 902. a ninth mounting edge; 107. a tenth mounting edge; 201. an eleventh mounting edge; 102. a twelfth mounting edge; 109. a thirteenth mounting edge; 118. a fourteenth mounting edge; 117. a fifteenth mounting edge; 800. a front projecting section; 900. a rear protruding section.
Detailed Description
The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure in the specification. It is to be understood that the described embodiments are merely illustrative of some, and not restrictive, of the embodiments of the disclosure. The disclosure may be embodied or carried out in various other specific embodiments, and various modifications and changes may be made in the details within the description without departing from the spirit of the disclosure. It should be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without inventive step, are intended to be within the scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to or other than one or more of the aspects set forth herein.
The structure in the prior art is as follows: as shown in fig. 1, a rectifier casing 4 (a rectifier 3 is arranged at a position of a fan outlet, and is installed through the rectifier casing 4), an intermediate casing 1, and a transition section casing 5 are sequentially arranged along an incoming flow direction, with a placement direction of fig. 1 as a reference, a first fulcrum bearing seat 2 and a second fulcrum bearing seat 9 are respectively arranged at the lower left and the lower right, and a first fulcrum bearing 10 and a second fulcrum bearing 11 are respectively arranged in the first fulcrum bearing seat 2 and the second fulcrum bearing seat 9. The transition section casing 5 is internally provided with a compressor which comprises a compressor first-stage casing 6 and a compressor zero-stage inner ring front-stage casing 8, and a zero-stage adjustable guide vane 7 is arranged in the middle of the compressor first-stage casing 6 and the compressor zero-stage inner ring front-stage casing.
When the rectifier 3 is installed, the first installation edge 401 of the fan casing and the sixteenth installation edge 401 of the outlet rectifier 3 are fixed with the second installation edge 103 on the intermediate casing 1;
when the transition section casing 5 is assembled on the intermediate casing 1, the transition section casing 5 is fixed with the fourth mounting edge 104 of the intermediate casing 1 through the third mounting edge 501 of the transition section casing 5;
when the first-stage casing 6 of the compressor and the zero-level adjustable guide vane 7 are assembled on the intermediate casing 1, the first-stage casing 6 of the compressor is fixed with the sixth mounting edge 700 of the intermediate casing 1 through the fifth mounting edge 601 of the first-stage casing 6 of the compressor, and the inner side of the zero-level adjustable guide vane 7 is connected with the eighth mounting edge 106 of the intermediate casing 1 through the seventh mounting edge 801 of the front-stage casing 8 of the zero-level inner ring of the compressor;
when the intermediate casing 1 is assembled, the second fulcrum bearing 11 is assembled on the second fulcrum bearing seat 9, and then connected to the tenth mounting edge 107 of the intermediate casing 1 through the ninth mounting edge 902 of the second fulcrum bearing seat 9.
As shown in fig. 1, the first bracket bearing is mounted on the intermediate casing 1 in the same manner as the second fulcrum bearing 11, and the eleventh mounting edge 201 of the first fulcrum bearing seat 2 and the twelfth mounting edge 102 of the front extension section 800 of the intermediate casing 1 are mounted by a flange assembly.
The traditional mode is to set up a plurality of installation edges with intermediary machine casket 1, has satisfied the functional requirement of assembling spare parts such as first fulcrum bearing frame 2, fan outlet rectifier 3. The installation edge connection can be seen, the whole rigidity of the intermediate bearing frame is reduced, the number and the specification of the connecting pieces are increased, and the assembly workload is increased.
The core of the scheme is that the traditional mode is improved, and accessories required by installation are simplified, so that the weight of the whole structure is reduced. As shown in fig. 2, the intermediate casing 1 of the integrated dual-rotor aircraft engine is used for installing the rectifier 3 at the fan outlet position, specifically, an annular groove 50 which is adaptive to the size of the rectifier 3 is arranged on the inner wall of the front-section outer casing of the intermediate casing 1, an outward-turned hanging buckle 52 is arranged on one side of the inner wall of the front-section outer casing of the intermediate casing 1, which is close to the annular groove 50, and a caulking groove 51 is axially arranged on the other side of the annular groove 50;
one side of the rectifier 3 is provided with a hook 311 matched with the shape of the hanging buckle 52, and the other side of the rectifier is embedded into the embedding groove 51 and is overlapped in a spigot manner, and is circumferentially fixed with the intermediary case 1 in a rivet or pin manner.
According to the scheme, the conventional intermediate casing 1 and the rectifier casing 4 are integrally formed to serve as the intermediate casing 1, the rectifier 3 is installed through the arrangement of the annular groove 50, as shown in fig. 3, the rectifier 3 is axially fixed or limited through the matching of the hanging buckle 52 and the embedding groove 51, and the mode is convenient for secondary replacement of the rectifier casing 4. After the rectifier 3 is assembled on the ring groove 50, the rectifier casing 4 is radially limited or fixed in the circumferential direction in a rivet mode, so that the use of a plurality of flange assemblies is avoided on the whole, and the condition that the stress concentration on the mounting surface causes the fracture of the mounting surface is avoided.
In actual installation, as shown in fig. 2, the rectifier 3 at the outlet of the fan has a characteristic cylindrical surface 310, the characteristic cylindrical surface 310 is matched with the caulking groove 51 formed on the intermediate casing 1, and the hook 311 on the rectifier 3 is matched with the hook 52 on the intermediate casing 1 to realize the axial installation of the rectifier 3.
As a specific embodiment provided in the present disclosure, the mounting method further includes mounting the first fulcrum bearing seat 2, the first fulcrum bearing seat 2 is used for mounting the first fulcrum bearing 10, the front section of the intermediate casing 1 is provided with a front protruding section 800, the front protruding section 800 and the first fulcrum bearing seat 2 are formed in an integrated manner, specifically, the first fulcrum bearing seat 2 includes a thirteenth mounting edge 109, as shown in fig. 2, an edge of the first fulcrum bearing seat 2, which is close to the intermediate casing 1, serves as the thirteenth mounting edge 109, and the front protruding section 800 and the thirteenth mounting edge 109 are formed in an integrated manner. The use of pins, steel wires, thread inserts and flange components in the traditional mode is avoided, and the weight of the whole structure is reduced.
As a specific embodiment provided by the present disclosure, the mounting of the second fulcrum bearing seat 9 is further included, the second fulcrum bearing seat 9 is used for mounting the second fulcrum bearing 11, the rear section of the intermediate casing 1 is provided with a rear extending section 900, the rear extending section 900 and the second fulcrum bearing seat 9 are formed in an integrated manner, specifically, the second fulcrum bearing seat 9 includes a fourteenth mounting edge 118, as shown in fig. 2, an edge of the second fulcrum bearing seat 9, which is close to the casing, is used as the fourteenth mounting edge 118, and the rear extending section 900 and the fourteenth mounting edge 118 are formed in an integrated manner. The use of pins, steel wires, threaded sleeves and flange assemblies in the traditional mode is avoided, the weight of the whole structure is reduced, the complexity of the force bearing scheme of the intermediate casing 1 is simplified, the specification and the number of connecting pieces are reduced, the installation of the labyrinth seal seat is simplified, the labyrinth seal seat is installed at the butt joint position of the tenth installation edge 107 and the ninth installation edge 902 in the traditional mode, and the performance of labyrinth seal is reduced by more parts.
As the embodiment provided in the present application, the installation with the transition section casing 5 is further included, the intermediate casing 1 and the transition section casing 5 are integrally formed, and in the prior art, the actuator cylinder installation seat is installed at a position corresponding to the zero-level adjustable guide vane 7. The actuator cylinder mounting seat needs to be monitored and measured during working, and the influence on the measurement of driving precision and feedback precision caused by vibration in the traditional mode during the working of an engine is avoided in an integrated forming mode.
As a specific implementation mode provided by the scheme, the installation with the compressor is further included, the compressor includes a compressor first-stage casing 6, a compressor zero-stage inner ring front-stage casing 8 and a zero-stage adjustable guide vane 7, specifically:
the intermediate casing 1 is integrally formed with the compressor first-stage casing 6 and the compressor zero-stage inner ring front-section casing 8 respectively to simplify the installation difficulty of the zero-stage adjustable guide vane 7, for example, the intermediate casing 1 is internally provided with the splitter ring 105 in an integrated manner, and the compressor first-stage casing 6 is integrally formed with the splitter ring 105. The installation of the zero-level adjustable guide vane 7 is simplified, the condition that the installation difficulty of the zero-level adjustable guide vane 7 is high due to the installation of a flange assembly is avoided, the inner wall surface of the intermediate casing 1 is relatively smooth due to the structure, and the influence of the protruded installation parts on the zero-level adjustable guide vane 7 is avoided. In practice, the zero-order adjustable blade is mounted on the fifteenth mounting edge 117 of the intermediate casing 1.
The above is only a specific embodiment of the present disclosure, but the scope of the present disclosure 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 disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (6)
1. An intermediary case of an integrated double-rotor aircraft engine is suitable for mounting a rectifier at the position of a fan outlet and is characterized in that,
an annular groove with the size adaptive to that of the rectifier is formed in the inner wall of the front-section outer casing of the intermediary casing, an outward-turning hanging buckle is arranged on one side, close to the annular groove, of the inner wall of the front-section outer casing, and an embedded groove is axially formed in the other side of the annular groove; one side of the rectifier is provided with a hook matched with the hanging buckle in shape, the other side of the rectifier is embedded into the caulking groove and is overlapped in a spigot mode, and the rectifier is circumferentially fixed with the intermediary case in a rivet mode.
2. The intermediate case according to claim 1, further comprising a mounting to the first fulcrum bearing seat, wherein the front section of the intermediate case is provided with a front extension, and wherein the front extension is integrally formed with the first fulcrum bearing seat.
3. The intermediate case according to claim 2, further comprising a mounting to the second fulcrum bearing seat, wherein the rear section of the intermediate case is provided with a rear extension section, and wherein the rear extension section is integrally formed with the second fulcrum bearing seat.
4. The intermediate case according to claim 3, further comprising an attachment to a compressor comprising a compressor primary case, a compressor zero stage inner ring forward case, and zero stage adjustable guide vanes,
the intermediate casing is integrally formed with the compressor first-stage casing and the compressor zero-stage inner ring front-section casing respectively, so that the installation difficulty of the zero-stage adjustable guide vane is simplified.
5. The intermediate casing according to claim 4, wherein a splitter ring is integrally formed in the intermediate casing, and the compressor primary casing is integrally formed with the splitter ring.
6. The intermediate case according to claim 5, further comprising a transition piece case, wherein the intermediate case is integrally formed with the transition piece case and has a ram mount mounted therein at a location corresponding to the zero stage adjustable vane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211186533.4A CN115263808B (en) | 2022-09-28 | 2022-09-28 | Intermediate casing of integrated double-rotor aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211186533.4A CN115263808B (en) | 2022-09-28 | 2022-09-28 | Intermediate casing of integrated double-rotor aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115263808A CN115263808A (en) | 2022-11-01 |
| CN115263808B true CN115263808B (en) | 2023-02-21 |
Family
ID=83757914
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211186533.4A Active CN115263808B (en) | 2022-09-28 | 2022-09-28 | Intermediate casing of integrated double-rotor aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115263808B (en) |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4200846B2 (en) * | 2003-07-04 | 2008-12-24 | 株式会社Ｉｈｉ | Shroud segment |
| US9238977B2 (en) * | 2012-11-21 | 2016-01-19 | General Electric Company | Turbine shroud mounting and sealing arrangement |
| US9297312B2 (en) * | 2012-12-29 | 2016-03-29 | United Technologies Corporation | Circumferentially retained fairing |
| WO2014105512A1 (en) * | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Mechanical linkage for segmented heat shield |
| JP6233578B2 (en) * | 2013-12-05 | 2017-11-22 | 株式会社Ihi | Turbine |
| JP6614407B2 (en) * | 2015-06-10 | 2019-12-04 | 株式会社Ｉｈｉ | Turbine |
| US10514004B2 (en) * | 2015-12-14 | 2019-12-24 | Rohr, Inc. | Cascade assembly for a thrust reverser of an aircraft nacelle |
| CN206513408U (en) * | 2017-01-23 | 2017-09-22 | 中国航发沈阳发动机研究所 | A kind of low-pressure turbine guide vane location structure and the engine with it |
| CN211116275U (en) * | 2019-12-06 | 2020-07-28 | 中国航发商用航空发动机有限责任公司 | Engine nacelle structure and aeroengine |
| CN212337380U (en) * | 2020-05-27 | 2021-01-12 | 中国航发商用航空发动机有限责任公司 | Turbine cartridge receiver limit structure |
| CN114876877B (en) * | 2022-05-12 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | Stationary blade angle adjusting device suitable for multi-duct fan |
-
2022
- 2022-09-28 CN CN202211186533.4A patent/CN115263808B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN115263808A (en) | 2022-11-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110196167B (en) | Core machine test rear casing | |
| CN101509398B (en) | Platform and vane for an impeller wheel of a turbomachine, impeller wheel and compressor or turbomachine comprising such an impeller wheel | |
| US8511983B2 (en) | LPC exit guide vane and assembly | |
| CA2600818C (en) | Exhaust duct and tail cone attachment of aircraft engines | |
| JP2002061600A (en) | Platform guide vane having corresponding shape | |
| US8579583B2 (en) | Strut for an intermediate turbine housing, intermediate turbine housing, and method for producing an intermediate turbine housing | |
| US20130333350A1 (en) | Airfoil including adhesively bonded shroud | |
| EP3489463B1 (en) | Composite fan platform lug reinforcement | |
| CA2852180A1 (en) | Composite housing with a metallic fixing flange for the compressor of an axial turbomachine | |
| CN103080563A (en) | Flow straightener device for turbomachine | |
| US8469662B2 (en) | Guide vane architecture | |
| CN115263808B (en) | Intermediate casing of integrated double-rotor aircraft engine | |
| CN108691810B (en) | Turbine engine containment assembly and method of making same | |
| US8662819B2 (en) | Apparatus and method for preventing cracking of turbine engine cases | |
| US6881032B2 (en) | Exit stator mounting | |
| EP3001014A1 (en) | Improved nacelle inlet and engine fan housing assembly and method for making same | |
| US20100150711A1 (en) | Apparatus and method for preventing cracking of turbine engine cases | |
| CN110725721B (en) | Composite outlet guide vane with metal fasteners for a turbomachine | |
| CA2803706C (en) | Fan and boost joint | |
| US9664069B2 (en) | Panels of a fan of a gas turbine | |
| CN110273714B (en) | Collar support assembly for an airfoil | |
| US20240117747A1 (en) | Stator vane assembly for an aircraft turbine engine compressor | |
| EP4086437A1 (en) | Vane system with continuous support ring | |
| US11035238B2 (en) | Airfoil including adhesively bonded shroud | |
| CN116291884A (en) | Novel oil supply and heat insulation structure for integrated high-strength bearing cavity |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |