CN111255747A - Integrated diffuser connecting structure for centrifugal compressor - Google Patents
Integrated diffuser connecting structure for centrifugal compressor Download PDFInfo
- Publication number
- CN111255747A CN111255747A CN202010079126.8A CN202010079126A CN111255747A CN 111255747 A CN111255747 A CN 111255747A CN 202010079126 A CN202010079126 A CN 202010079126A CN 111255747 A CN111255747 A CN 111255747A
- Authority
- CN
- China
- Prior art keywords
- diffuser
- hole
- main body
- centrifugal compressor
- integrated
- 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
- F04D29/40—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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
Abstract
The invention discloses an integrated diffuser connecting structure for a centrifugal compressor, which comprises a diffuser main body, wherein the middle of the diffuser main body is of a through hole structure, one end of the diffuser main body is of a front cover structure, a connecting lug with a hole is arranged on the front cover structure, an air flow channel is arranged on the inner side of the through hole of the diffuser main body, an air inlet is arranged on the inner side of the through hole of the diffuser main body, an air outlet is arranged on the end surface of the diffuser main body, and an air flow channel is a streamline type with an expanded flow path, so that the kinetic energy of high-speed air flow can be converted into static pressure to the maximum extent, the air flow separation on the wall surface of the diffuser is avoided, the total pressure loss is reduced. The other end of the diffuser is connected with the shaft sleeve, the shaft sleeve is connected with the combustion chamber, the manufacturing time is effectively shortened, the assembling time is reduced, the performance loss caused by the assembling problem is reduced, and meanwhile, the pneumatic part of the assembly is subjected to pneumatic optimization, so that the efficiency of the whole machine is improved.
Description
Technical Field
The invention belongs to a core structure of a static part of a turbojet engine, and particularly relates to an integrated diffuser connecting structure for a centrifugal compressor.
Background
In the existing small-sized aero engine, the flow rate of the inlet air of the combustion chamber is very high, generally 150-220m/s, from the combustion angle, the high-speed air is an important means for ensuring that the aviation kerosene can not realize stable and sufficient combustion in the compact structure of the small-sized aero engine, and reducing the speed of the inlet air of the combustion chamber is an important means for improving the combustion efficiency, the combustion stability and the engine efficiency. The diffuser in the compressor mainly plays a role in diffusing high-speed air at the outlet of the centrifugal pressure turbine and changing the speed direction of the high-speed air from the radial direction to the axial direction. The diffuser converts the kinetic energy in the gas flow into static pressure energy, reduces the velocity of the gas flow entering the combustion chamber and provides for the full combustion of the fuel in the combustion chamber. The small-sized turbojet engine has a complex structure and high requirement on assembly precision, and the capacity of the small-sized turbojet engine is limited; the current diffuser airflow channel structure does not comprise a radial-axial steering section, is subject to process constraint as a diffuser manufactured in the prior art, and is difficult to obtain a complex curved surface, so that airflow can generate a more serious separation phenomenon in the diffuser, and the total pressure loss is more. Meanwhile, the diffuser and the front cover of the engine are connected through a plurality of bolts, and the assembly is complex.
Disclosure of Invention
The invention aims to provide an integrated diffuser connecting structure for a centrifugal compressor, which overcomes the defects of the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
an integrated diffuser connecting structure for a centrifugal compressor comprises a diffuser main body, wherein the middle of the diffuser main body is of a through hole structure, one end of the diffuser main body is of a front cover structure, and a connecting lug with a hole is arranged on the front cover structure; an air inlet is arranged on the inner side of the through hole of the diffuser body, an air outlet communicated with the air inlet through an air flow channel is arranged on the end face of the other end of the diffuser body, the air flow channel of the air inlet and the air outlet is arranged along the pipe wall of the diffuser body, and the diameter of the air flow channel is of a gradually expanding structure from the air inlet to the air outlet.
Furthermore, a plurality of air inlets are uniformly arranged on the inner side of the diffuser body at intervals, and each air inlet is connected with one air flow channel.
Furthermore, 20 air inlets are uniformly arranged on the inner side of the diffuser body at intervals.
Furthermore, the cross section of the airflow channel is of a special-shaped curved surface structure.
Furthermore, an annular groove is circumferentially arranged on the outer side of the diffuser body, and a grid support is arranged in the annular groove.
Furthermore, the grid supports are composed of a surface center grid structure and are distributed at intervals along the circumference of the outer side of the diffuser body.
Furthermore, the other end of the diffuser body is provided with a shaft sleeve connecting hole, and a shaft sleeve is fixed in the shaft sleeve connecting hole.
Furthermore, a combustion chamber is fixed on the outer side of the shaft sleeve.
Furthermore, the combustion chamber is an evaporation tube type combustion chamber, and 12 evaporation tubes are arranged in the combustion chamber.
Furthermore, a rear bearing seat and a front bearing seat which are fixedly arranged with the supporting piece are arranged in the shaft sleeve.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention relates to an integrated diffuser connecting structure for a centrifugal compressor, which comprises a diffuser main body, wherein the middle of the diffuser main body is of a through hole structure, one end of the diffuser main body is of a front cover structure, the front cover structure is provided with a connecting lug with a hole, an air flow channel is arranged on the inner side of the through hole of the diffuser main body, an air inlet is arranged on the inner side of the through hole of the diffuser main body, an air outlet is arranged on the end surface of the diffuser main body, and an air flow channel is a streamline type with a flow path expansion, so that the kinetic energy of high-speed air flow can be converted into static pressure to the maximum extent, the air flow separation on the wall surface of the diffuser is avoided, the total pressure loss.
Furthermore, a plurality of air inlets are uniformly arranged on the inner side of the diffuser body at intervals, each air inlet is connected with one air flow channel, so that the resistance of air flow in the channels can be effectively reduced, the pressure loss is reduced, and the efficiency of the diffuser is improved.
Furthermore, the shaft sleeve and the combustion chamber are integrated, so that the processing and manufacturing cost, the manufacturing and assembling time and the assembling difficulty are reduced, and the productivity is greatly improved.
Furthermore, an annular groove is formed in the circumferential direction of the outer side of the diffuser body, a grid support is arranged in the annular groove and consists of a surface center grid structure and is distributed at intervals along the circumferential direction of the outer side of the diffuser body, the weight of the integrated diffuser is effectively reduced, and the grid support is used as a support to avoid the problem that collapse cannot be formed in the additive manufacturing process.
Drawings
FIG. 1 is a schematic view of the structure of the present invention
FIG. 2 is a schematic view of the diffuser body structure of the present invention.
Fig. 3 is a front view of the present invention.
Fig. 4 is a rear view of the present invention.
FIG. 5 is a curved view of the inner flow passage of the present invention.
In the figure: 1. diffuser body, 2, grid support; 3. a front cover structure; 4. connecting lugs; 5. an air inlet; 6. and an air outlet.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings:
as shown in fig. 1 to 5, an integrated diffuser connecting structure for a centrifugal compressor comprises a diffuser main body 1, wherein the middle of the diffuser main body 1 is of a through hole structure, one end of the diffuser main body 1 is provided with a front cover structure 3, the front cover structure 3 is provided with a connecting lug 4 with a hole for being fixedly connected with a casing, and the integrated diffuser can be assembled on the casing through a bolt; the inner side of the through hole of the diffuser main body 1 is provided with an air inlet hole 5, the end face of the other end of the diffuser main body 1 is provided with an air outlet hole 6 communicated with the air inlet hole through an air flow channel, the air flow channel of the air inlet hole 5 and the air outlet hole 6 is arranged along the pipe wall of the diffuser main body 1, and the pipe diameter of the air flow channel is of a gradually expanding structure from the air inlet hole 5 to the air outlet hole 6, so that a better diffusion effect is obtained, the air flow speed is reduced, the air flow separation is. The diffuser main body 1 is provided with a mounting groove at one end of the air outlet, and the air outlet 6 is arranged on the wall of the mounting groove.
The other end of the diffuser body 1 is provided with a shaft sleeve connecting hole, a shaft sleeve 8 is fixed in the shaft sleeve connecting hole, a combustion chamber 7 is fixed on the outer side of the shaft sleeve 8, and the shaft sleeve 8 and the combustion chamber 7 are integrally formed.
The combustion chamber 7 is an evaporation tube type combustion chamber, and 12 evaporation tubes are arranged in the combustion chamber 7.
A rear bearing seat 81 and a front bearing seat 82 are arranged in the shaft sleeve 8 and are used for being fixedly installed with a supporting piece.
A plurality of air inlets 5 are uniformly arranged at intervals on the inner side of the diffuser body 1, and each air inlet 5 is connected with an airflow channel.
This application is equipped with 20 inlet ports 5 at diffuser main part 1 inboard even interval.
The cross section of the airflow channel is of a special-shaped curved surface structure. Diffuser main part 1 outside circumference is equipped with the ring channel, is equipped with grid support 2 in the ring channel, and grid support 2 comprises face center grid structure, along diffuser main part 1 outside circumference interval distribution, adopts ring channel structural design, has effectively reduced the weight of diffuser, improves heat-sinking capability simultaneously. The integrated diffuser is formed by additive manufacturing, and the grid support 2 is used as a support, so that the problem that collapse cannot be formed in the additive manufacturing process is solved. A plurality of air inlets are uniformly arranged on the inner side of the diffuser body at intervals, each air inlet is connected with an airflow channel, the resistance of airflow in the channels can be effectively reduced, the pressure loss is reduced, and the efficiency of the diffuser is improved. The shaft sleeve and the combustion chamber are integrated, so that the processing and manufacturing cost, the manufacturing and assembling time and the assembling difficulty are reduced, and the productivity is greatly improved.
The foregoing detailed description has been presented in conjunction with specific embodiments of the invention, but is not intended to limit the invention thereto. Many changes, modifications, and variations can be made to the embodiments without departing from the spirit and scope of the invention, which is defined by the claims and their equivalents.
Claims (10)
1. An integrated diffuser connecting structure for a centrifugal compressor is characterized by comprising a diffuser main body (1), wherein the middle of the diffuser main body (1) is of a through hole structure, one end of the diffuser main body (1) is provided with a front cover structure (3), and the front cover structure (3) is provided with a connecting lug (4) with a hole; an air inlet hole (5) is formed in the inner side of a through hole of the diffuser main body (1), an air outlet hole (6) communicated with the air inlet hole through an air flow channel is formed in the end face of the other end of the diffuser main body (1), the air flow channel of the air inlet hole (5) and the air outlet hole (6) is arranged along the pipe wall of the diffuser main body (1), and the pipe diameter of the air flow channel is of a gradually expanding structure from the air inlet hole (5) to the air outlet hole (6.
2. The integrated diffuser connecting structure for the centrifugal compressor as claimed in claim 1, wherein a plurality of air inlet holes (5) are uniformly arranged at intervals inside the diffuser body (1), and each air inlet hole (5) is connected with one air flow passage.
3. The integrated diffuser connection structure for the centrifugal compressor as claimed in claim 1, wherein 20 air inlet holes (5) are uniformly spaced inside the diffuser body (1).
4. The integrated diffuser connection structure for a centrifugal compressor as recited in claim 1, wherein the cross-section of the flow passage is a profiled curved surface structure.
5. The integrated diffuser connecting structure for the centrifugal compressor according to claim 1, wherein an annular groove is circumferentially formed on the outer side of the diffuser body (1), and a grid support (2) is arranged in the annular groove.
6. An integrated diffuser connection structure for a centrifugal compressor according to claim 5, characterized in that the lattice supports (2) are formed of a face-centered lattice structure, spaced circumferentially around the outside of the diffuser body (1).
7. The integrated diffuser connecting structure for the centrifugal compressor as claimed in claim 1, wherein a bushing connecting hole is formed at the other end of the diffuser body (1), and a bushing (8) is fixed in the bushing connecting hole.
8. The integrated diffuser connecting structure for the centrifugal compressor as recited in claim 7, wherein the combustion chamber (7) is fixed to an outer side of the sleeve (8), and the sleeve (8) and the combustion chamber (7) are integrally formed.
9. The integrated diffuser connection structure for the centrifugal compressor as recited in claim 8, wherein the combustion chamber (7) is an evaporator tube type combustion chamber, and 12 evaporator tubes are provided in the combustion chamber (7).
10. The integrated diffuser connection structure for a centrifugal compressor according to claim 7, wherein a rear bearing seat (81) and a front bearing seat (82) for fixed mounting with a support member are provided in the sleeve (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010079126.8A CN111255747A (en) | 2020-02-03 | 2020-02-03 | Integrated diffuser connecting structure for centrifugal compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010079126.8A CN111255747A (en) | 2020-02-03 | 2020-02-03 | Integrated diffuser connecting structure for centrifugal compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111255747A true CN111255747A (en) | 2020-06-09 |
Family
ID=70923905
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010079126.8A Pending CN111255747A (en) | 2020-02-03 | 2020-02-03 | Integrated diffuser connecting structure for centrifugal compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111255747A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113932249A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Combustion chamber and pre-diffuser |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH467943A (en) * | 1967-08-04 | 1969-01-31 | United Aircraft Canada | Centrifugal compressor |
| US6280139B1 (en) * | 1999-10-18 | 2001-08-28 | Pratt & Whitney Canada Corp. | Radial split diffuser |
| US6589015B1 (en) * | 2002-05-08 | 2003-07-08 | Pratt & Whitney Canada Corp. | Discrete passage diffuser |
| US20090022586A1 (en) * | 2007-07-18 | 2009-01-22 | Honda Motor Co., Ltd. | Axial diffuser for a centrifugal compressor |
| US20170114794A1 (en) * | 2015-10-27 | 2017-04-27 | Pratt & Whitney Canada Corp. | Diffuser pipe with vortex generators |
| CN108590859A (en) * | 2018-04-24 | 2018-09-28 | 南方科技大学 | A kind of Micro Turbine Jet Engine of increasing material manufacturing |
| CN108661951A (en) * | 2017-03-27 | 2018-10-16 | 通用电气公司 | Diffuser-derotator for gas-turbine unit |
| CN109723576A (en) * | 2017-10-27 | 2019-05-07 | 北京精密机电控制设备研究所 | A kind of air turbo rocket novel high-pressure is than big flow turbo charging installation |
| CN209414261U (en) * | 2019-01-18 | 2019-09-20 | 温岭市博大塑业有限公司 | A kind of guide vane of long-life |
| US20190293087A1 (en) * | 2018-03-20 | 2019-09-26 | Honda Motor Co., Ltd. | Pipe diffuser of centrifugal compressor |
-
2020
- 2020-02-03 CN CN202010079126.8A patent/CN111255747A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH467943A (en) * | 1967-08-04 | 1969-01-31 | United Aircraft Canada | Centrifugal compressor |
| US6280139B1 (en) * | 1999-10-18 | 2001-08-28 | Pratt & Whitney Canada Corp. | Radial split diffuser |
| US6589015B1 (en) * | 2002-05-08 | 2003-07-08 | Pratt & Whitney Canada Corp. | Discrete passage diffuser |
| US20090022586A1 (en) * | 2007-07-18 | 2009-01-22 | Honda Motor Co., Ltd. | Axial diffuser for a centrifugal compressor |
| US20170114794A1 (en) * | 2015-10-27 | 2017-04-27 | Pratt & Whitney Canada Corp. | Diffuser pipe with vortex generators |
| CN108661951A (en) * | 2017-03-27 | 2018-10-16 | 通用电气公司 | Diffuser-derotator for gas-turbine unit |
| CN109723576A (en) * | 2017-10-27 | 2019-05-07 | 北京精密机电控制设备研究所 | A kind of air turbo rocket novel high-pressure is than big flow turbo charging installation |
| US20190293087A1 (en) * | 2018-03-20 | 2019-09-26 | Honda Motor Co., Ltd. | Pipe diffuser of centrifugal compressor |
| CN108590859A (en) * | 2018-04-24 | 2018-09-28 | 南方科技大学 | A kind of Micro Turbine Jet Engine of increasing material manufacturing |
| CN209414261U (en) * | 2019-01-18 | 2019-09-20 | 温岭市博大塑业有限公司 | A kind of guide vane of long-life |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113932249A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Combustion chamber and pre-diffuser |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203097955U (en) | Air guiding assembly of gas turbine engine | |
| US6280139B1 (en) | Radial split diffuser | |
| CN1854486B (en) | Double reverse turbine engine, and method for assembling the same | |
| CN106870201A (en) | For the exhaust nozzle of gas-turbine unit | |
| CN108425708B (en) | Combined vortex reducer structure | |
| CN112377268B (en) | Integrated diffuser for additive manufacturing | |
| CN104204423B (en) | For the exhaust diffuser of gas turbine | |
| CN110469540A (en) | A kind of counter-rotating compressor structure and the combined type suitable for counter-rotating compressor bleed air system subtract whirlpool device structure | |
| CN111622985A (en) | Diffuser integrating diffusion and rectification | |
| CN111255747A (en) | Integrated diffuser connecting structure for centrifugal compressor | |
| CN216044114U (en) | Intake manifold assembly of EGR distributor | |
| CN112628204B (en) | High-efficient low-noise multilayer collector and centrifugal fan | |
| CN214146013U (en) | High-pressure compressor rotor and vortex reducing device | |
| CN215444436U (en) | High-circulation and low-pressure-loss radial and axial integrated diffuser | |
| CN213980965U (en) | Tubular vortex reducer and vortex reducing pipe thereof | |
| CN210343859U (en) | Diffuser structure and centrifugal compressor | |
| CN205277627U (en) | Miniature turbofan engine divides division exhaust apparatus with rectifier | |
| CN110925792B (en) | Fuel oil main pipe with layered centrifugal nozzles | |
| CN113969806A (en) | High-power multistage axial flow turbine expander | |
| CN212868028U (en) | Diffuser integrating diffusion and rectification | |
| CN117145592B (en) | Prerotation system based on special-shaped throttling channel and design method thereof | |
| CN113530683A (en) | Turbine blade cooling system and aircraft engine | |
| CN219993992U (en) | Novel structure diffuser | |
| CN117365683A (en) | Combined vortex reducing structure of air system | |
| US20220120291A1 (en) | Damping device for damping shaft vibration |
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 |
Application publication date: 20200609 |
|
| RJ01 | Rejection of invention patent application after publication |