CN112377268B - Integrated diffuser for additive manufacturing - Google Patents
Integrated diffuser for additive manufacturing Download PDFInfo
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- CN112377268B CN112377268B CN202011271202.1A CN202011271202A CN112377268B CN 112377268 B CN112377268 B CN 112377268B CN 202011271202 A CN202011271202 A CN 202011271202A CN 112377268 B CN112377268 B CN 112377268B
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- blade
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
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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
- F04D29/66—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
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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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
- F04D29/66—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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an integrated diffuser manufactured by additive manufacturing, wherein a plurality of integrated special-shaped blades are connected with the outer circumference of a web plate, a cover plate is connected with the outer circumference of the integrated special-shaped blades, the integrated diffuser is manufactured by adopting the additive manufacturing process, the processing procedure is simple, meanwhile, the blades and the front end surface of the cover plate are not under insufficient compression, the risk of vibration cracks of the blades is reduced, and the safety of the diffuser is improved. In addition, the high-pressure airflow output by the front centrifugal impeller flows in the continuous airflow channel formed by the two special-shaped blades of the integrated special-shaped blade, so that the airflow loss is low, and the total pressure loss of the blade is low.
Description
Technical Field
The invention relates to the technical field of diffusers of aero-engines, in particular to an integrated diffuser manufactured by materials in an additive mode.
Background
For the diffuser structure of the aircraft engine, an air flow channel of the diffuser is in a diffusion shape and is used for converting kinetic energy of high-speed air flow after accelerating and pressurizing of a centrifugal impeller into pressure energy, simultaneously converting the direction of the air flow from radial direction to axial direction, and conveying the air flow to a combustion chamber of the engine to be mixed with fuel oil and be combusted. The most common types of existing diffuser designs are three: the diffuser comprises a pipe diffuser, a vane diffuser and a conformal channel diffuser, wherein the pipe diffuser is formed by independent diffusion pipes; the conformal channel type diffuser is mainly characterized in that a plurality of three-position main channels in conformal design are periodically arranged in the circumferential direction, and the rear section in each main channel is provided with a splitter blade; the vane diffuser is composed of a front cover, radial vanes, axial vanes and a web, as shown in fig. 1, the radial vanes are used for guiding airflow to flow in a radial direction, the axial vanes are used for guiding airflow to flow in an axial direction, and a part of the axial vanes also need to function as splitter vanes.
At present, a blade type diffuser is usually designed in a split mode, the total pressure loss of blades is large, the number of required parts is large, machining procedures are multiple, assembling is complex, and due to errors caused by traditional split machining and manufacturing, the situation that insufficient compression is prone to occurring on the front end faces of diffuser blades and cover plates is caused, so that the problem that vibration cracks occur on the blades is caused. In addition, the traditional multi-part combined type and split type blade cannot realize self-supporting in the additive manufacturing process, so that the structural top material is easy to collapse, and the production and manufacturing difficulty is high.
Disclosure of Invention
The invention provides an integrated diffuser manufactured by an additive, which aims to solve the technical problem that the blades are easy to have vibration cracks due to insufficient compression on the front end surfaces of the blades and a cover plate of the existing blade diffuser caused by adopting a split design.
According to one aspect of the invention, the integrated diffuser manufactured through additive manufacturing comprises a web plate, a plurality of integrated special-shaped blades and a cover plate which are sequentially connected from inside to outside, wherein the cover plate, the integrated special-shaped blades and the web plate are manufactured through the additive manufacturing process, the integrated special-shaped blades are uniformly arranged along the circumferential direction, and an airflow channel is formed between every two adjacent integrated special-shaped blades so as to convert high-speed airflow kinetic energy after acceleration and pressurization of a centrifugal impeller into pressure energy and convert the airflow direction from the radial direction to the axial direction.
Further, the ratio of the radial outlet radius to the radial inlet radius of the integrated special-shaped blade is 1-1.1.
Further, the ratio of the radial outlet radius to the radial inlet radius of the integrated profiled blade is 1.08.
Further, the integrated special-shaped blade comprises a radial section, a turning transition section and an axial section which are connected in sequence, wherein the radial section is used for guiding airflow to flow along the radial direction, the turning transition section is used for guiding airflow to change from the radial flow to the axial flow, and the axial section is used for guiding airflow to flow along the axial direction.
Further, the height of an inlet blade of the radial section is 13-15 mm, the oblique length of the blade is about 18-20 mm, the maximum height of a blade outlet of the axial section is about 12-14 mm, the axial length is about 18-20 mm, and the total axial length of the integrated special-shaped blade is about 45-50 mm.
Further, the height of an inlet blade of the radial section is 15mm, and the inclined length of the blade is 19 mm; the maximum height of the blade outlet of the axial section is 13mm, and the axial length is 19 mm; the total axial length of the integrated special-shaped blade is 48 mm.
Furthermore, the outer peripheral surface of apron evenly is provided with a plurality of pairs of bolt hole for connect main engine casket and air inlet cover.
Furthermore, a plurality of bolt holes are formed in the front mounting surface of the cover plate and used for connecting the centrifugal impeller cover of the engine.
Further, the angle between the integrated special-shaped blade and the laser deposition heightening direction is smaller than 45 degrees.
The invention has the following effects:
according to the additive manufacturing integrated diffuser, the plurality of integrated special-shaped blades are connected with the outer circumference of the web, the cover plate is connected with the outer circumference of the plurality of integrated special-shaped blades, the integrated diffuser is integrally manufactured by adopting an additive manufacturing process, the processing procedure is simple, meanwhile, the situation that the blades and the front end face of the cover plate are not pressed sufficiently is avoided, the risk of vibration cracks of the blades is reduced, and the safety of the diffuser is improved. In addition, the high-pressure airflow output by the front centrifugal impeller flows in the continuous airflow channel formed by the two special-shaped blades of the integrated special-shaped blade, so that the airflow loss is low, and the total pressure loss of the blade is low.
In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification. In the drawings:
fig. 1 is a schematic structural view of a conventional vane diffuser.
Fig. 2 is a schematic view showing the overall structure of the integral diffuser of the preferred embodiment of the present invention.
Fig. 3 is a schematic cross-sectional view of an integrated diffuser according to a preferred embodiment of the present invention.
Fig. 4 is a partial structural schematic view of an integrated diffuser according to a preferred embodiment of the present invention.
Fig. 5 is a schematic view of the integrated diffuser with the cover plate removed according to the preferred embodiment of the present invention.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
As shown in fig. 2 to 5, a preferred embodiment of the present invention provides an additive manufactured integral diffuser, which includes a web, an integral profiled blade, and a cover plate connected in sequence from inside to outside, wherein the cover plate, the integral profiled blade, and the web are integrally manufactured by an additive manufacturing process. Specifically, a plurality of the integral type abnormal shape blade sets up along the even interval of circumference to be connected with the outer circumference of web, the apron then is connected with the outer circumference of a plurality of integral type abnormal shape blade. A continuous airflow channel is formed between two adjacent integrated special-shaped blades so as to convert kinetic energy of high-speed airflow after accelerated pressurization of the centrifugal impeller into pressure energy and convert the airflow direction from the radial direction to the axial direction. In one embodiment of the invention, the fan blade comprises a total of 19 integrated special-shaped blades uniformly arranged along the circumferential direction, and an airflow channel is formed between every two adjacent integrated special-shaped blades to form a total of 18 airflow channels. Of course, in other embodiments of the invention, the specific number of integral profiled blades may be adjusted as desired. In addition, the inlet area of an airflow channel formed between two adjacent integrated special-shaped blades is matched with the outlet airflow parameters of the front centrifugal impeller, and the outlet area meets the overall aerodynamic requirement and is matched with the inlet airflow parameters of the combustion chamber.
It can be understood that in the additive manufacturing integral diffuser of the embodiment, the plurality of integral type special-shaped blades are connected with the outer circumference of the web, the cover plate is connected with the outer circumference of the plurality of integral type special-shaped blades, the integral type additive manufacturing process is adopted, the machining process is simple, meanwhile, the situation that the compression is insufficient does not exist between the blades and the front end face of the cover plate any more, the risk that the vibration cracks occur on the blades is reduced, and the safety of the diffuser is improved. In addition, the high-pressure airflow output by the front centrifugal impeller flows in a continuous airflow channel formed by the two special-shaped blades of the integrated special-shaped blade, so that the airflow loss is low, and the total pressure loss of the blade is low.
It can be understood that the ratio of the radial outlet radius r4 to the radial inlet radius r3 of the integrated profiled blade is 1-1.1, and preferably the ratio of the radial outlet radius r4 to the radial inlet radius r3 of the integrated profiled blade is 1.08. The blades of the existing blade type diffuser are designed in a split mode and comprise axial blades and radial blades, the ratio of the radius of a radial outlet to the radius of a radial inlet of the existing blade type diffuser is generally about 1.25-1.35, and therefore the existing blade type diffuser is large in size and cannot meet the requirement of the miniaturization design of an aeroengine. The ratio of the radial outlet radius to the radial inlet radius of the integrated special-shaped blade is 1-1.1, the equivalent radial height is very small and is far smaller than that of the existing blade-type diffuser, the overall size of the diffuser is greatly reduced, and the miniaturization and compact design of an aeroengine is facilitated.
It can be understood that the integral diffuser of the present invention adopts a small equivalent radial height design for miniaturization, which results in an increase in difficulty in the deceleration and diffusion of the diffuser. Therefore, the invention fuses a traditional two-dimensional section type extending radial blade and an axial blade into an integral special-shaped blade crossing the axial direction and the radial direction through pneumatic design, the integral special-shaped blade is formed by three sections of three-dimensional space curved surfaces, and is optimized through design by combining a genetic algorithm, the integral special-shaped blade specifically comprises a radial section, a turning transition section and an axial section which are sequentially connected, wherein the radial section is used for guiding airflow to flow along the radial direction, the turning transition section is used for guiding airflow to change from the radial flow to the axial flow, and the axial section is used for guiding airflow to flow along the axial direction. The blade profile curved surface parameters of the three sections are optimally designed based on a genetic algorithm, specifically, the height of an inlet blade of the radial section is 13-15 mm, the oblique length of the blade is about 18-20 mm, the maximum height of a blade outlet of the axial section is about 12-14 mm, the axial length is about 18-20 mm, and the total axial length of the integrated special-shaped blade is about 45-50 mm. Preferably, the inlet vane height of the radial section is about 15mm, and the inclined length of the vane is about 19 mm; the maximum height of the blade outlet of the axial section is about 13mm, and the axial length is about 19 mm; the total axial length of the integrated special-shaped blade is about 48 mm. According to the integrated special-shaped blade, the three-dimensional curved surface parameters of the integrated special-shaped blade are designed through the optimization algorithm, the speed reduction and the pressure expansion of the pneumatic performance of the airflow can be realized under the condition that the overall performance requirement is met, the structural characteristic that the splitter blade is not required to be arranged at the rear end of the airflow channel is realized, and the structural form is simpler. Compare in traditional configuration and need adopt five number of axles to mill each blade profile of processing one by one, on partial blade needs rethread bolted connection to the diffuser main part, the reduction of this scheme diffuser blade quantity and additive manufacturing integrated into one piece, the manufacturing of being more convenient for.
In addition, a plurality of pairs of bolt holes are uniformly formed in the outer circumferential surface of the cover plate and used for connecting the main casing and the air inlet outer cover. Generally, 16 (8 pairs) bolt holes are uniformly formed on the outer circumferential surface of the cover plate so as to be fixedly connected with the main casing and the air inlet housing through bolts.
In addition, a plurality of bolt holes are arranged on the front mounting surface (namely the surface close to the front centrifugal impeller) of the cover plate and used for connecting the centrifugal impeller cover of the engine.
In addition, two main oil passages, two starting oil passages, two ignition electric nozzles, two thermocouples and a lubricating pipeline of the engine, wherein 9 pipeline holes pass through the integrated special-shaped blades from the front part of the diffuser and then lead to the combustion chamber and the turbine part.
In addition, as optimization, when an integrated diffuser structure is designed, the process characteristics of additive manufacturing are also considered, so that the angle between the integrated special-shaped blades and the laser deposition heightening direction is designed to be smaller than 45 degrees, the integrated special-shaped blades can be indirectly used as a support structure in the additive manufacturing process to achieve a self-supporting effect to a certain extent, an air flow channel formed among the integrated special-shaped blades does not need to be added with an additional support structure, the support structure removing process at the channel position and the phenomena of pits, bulges and unevenness of the blade surface caused by the removal of the support structure are reduced in the post-processing process of the additive manufacturing, and therefore the surface smoothness of the blades and the flow channel is good, and the total pressure loss of air flow is reduced.
Therefore, the integrated diffuser is integrally machined and manufactured in an additive manufacturing mode, the problems that the number of parts is large and machining, manufacturing and assembling are complex in the traditional design scheme are solved, the problem of diffuser blade vibration caused by insufficient compression of the diffuser blade and the front end face of the cover plate due to traditional split machining is solved, and the vibration margin of the diffuser blade is improved.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The integrated diffuser is characterized by comprising a web plate, a plurality of integrated special-shaped blades and a cover plate which are sequentially connected from inside to outside, wherein the cover plate, the integrated special-shaped blades and the web plate are manufactured through an additive manufacturing process; the integrated special-shaped blade comprises a radial section, a turning transition section and an axial section which are sequentially connected, wherein the radial section is used for guiding airflow to flow along the radial direction, the turning transition section is used for guiding airflow to change from the radial flow to the axial flow, and the axial section is used for guiding the airflow to flow along the axial direction; the height of an inlet blade of the radial section is 13-15 mm, the oblique length of the blade is 18-20 mm, the maximum height of a blade outlet of the axial section is 12-14 mm, the axial length is 18-20 mm, and the total axial length of the integrated special-shaped blade is 45-50 mm.
2. The additive manufactured one-piece diffuser of claim 1,
the ratio of the radial outlet radius to the radial inlet radius of the integrated special-shaped blade is 1-1.1.
3. The additive manufactured integral diffuser of claim 2,
the ratio of the radial outlet radius to the radial inlet radius of the integrated special-shaped blade is 1.08.
4. The additive manufactured one-piece diffuser of claim 1,
the height of an inlet blade of the radial section is 15mm, and the oblique length of the blade is 19 mm; the maximum height of the outlet of the blade of the axial section is 13mm, and the axial length is 19 mm; the total axial length of the integrated special-shaped blade is 48 mm.
5. The additive manufactured one-piece diffuser of claim 1,
the peripheral face of apron evenly is provided with a plurality of pairs of bolt hole for connect main engine casket and air inlet cover.
6. The additive manufactured one-piece diffuser of claim 1,
and a plurality of bolt holes are formed in the front mounting surface of the cover plate and used for connecting the centrifugal impeller cover of the engine.
7. The additive manufactured one-piece diffuser of claim 1,
the angle between the integrated special-shaped blade and the laser deposition heightening direction is smaller than 45 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011271202.1A CN112377268B (en) | 2020-11-13 | 2020-11-13 | Integrated diffuser for additive manufacturing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011271202.1A CN112377268B (en) | 2020-11-13 | 2020-11-13 | Integrated diffuser for additive manufacturing |
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| Publication Number | Publication Date |
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| CN112377268A CN112377268A (en) | 2021-02-19 |
| CN112377268B true CN112377268B (en) | 2022-08-30 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113007137B (en) * | 2021-04-25 | 2022-12-02 | 中国航发湖南动力机械研究所 | Diffuser with containment and centrifugal compressor |
| FR3122452A1 (en) * | 2021-04-30 | 2022-11-04 | Safran Helicopter Engines | Turbomachine subassembly produced by additive manufacturing |
| CN113756951B (en) * | 2021-09-30 | 2022-07-12 | 大连理工大学 | Shape-preserving diffuser with radial diffuser and axial diffuser fused |
| CN113878129A (en) * | 2021-10-29 | 2022-01-04 | 成都先进金属材料产业技术研究院股份有限公司 | Method for manufacturing diffuser integral piece with integrated and lightweight structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2402717B (en) * | 2003-06-10 | 2006-05-10 | Rolls Royce Plc | A vane assembly for a gas turbine engine |
| FR2985792B1 (en) * | 2012-01-18 | 2014-02-07 | Snecma | ANGLE CORRELATION VIBRATION DAMPING RECTIFIER SECTOR FOR TURBOMACHINE COMPRESSOR |
| US10436068B2 (en) * | 2016-02-12 | 2019-10-08 | General Electric Company | Flowpath contouring |
| CN106089808B (en) * | 2016-07-28 | 2018-11-16 | 中南大学 | A kind of blade diffuser and its formative method with trailing edge structures before swallow-tail form |
| CN108386389B (en) * | 2018-02-08 | 2020-03-24 | 中国科学院工程热物理研究所 | Centrifugal compressor diffuser structure with blades, casing and hub fused |
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