CN104389800A - Mixed flow air compressor of aero-engine - Google Patents
Mixed flow air compressor of aero-engine Download PDFInfo
- Publication number
- CN104389800A CN104389800A CN201410545599.7A CN201410545599A CN104389800A CN 104389800 A CN104389800 A CN 104389800A CN 201410545599 A CN201410545599 A CN 201410545599A CN 104389800 A CN104389800 A CN 104389800A
- Authority
- CN
- China
- Prior art keywords
- mixed flow
- blade
- flow
- circulation groove
- flow air
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 claims abstract description 31
- 239000000411 inducer Substances 0.000 claims description 7
- 230000004308 accommodation Effects 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims description 3
- 230000006835 compression Effects 0.000 abstract description 11
- 238000007906 compression Methods 0.000 abstract description 11
- 230000008901 benefit Effects 0.000 abstract description 7
- 238000010304 firing Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000000565 sealant Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
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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
- F04D25/00—Pumping installations or systems
- F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
- F04D25/163—Combinations of two or more pumps ; Producing two or more separate gas flows driven by a common gearing arrangement
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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
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
Abstract
The invention discloses a mixed flow air compressor of an aero-engine. The mixed flow air compressor comprises a low-pressure mixed flow air compression assembly, a high-pressure mixed flow air compression assembly, diffusers and rectifying devices, wherein the first diffuser, the first rectifying device, the high-pressure mixed flow air compression assembly, the second diffuser and the second rectifying device are sequentially arranged behind the low-pressure mixed flow air compression assembly; the low-pressure mixed flow air compression assembly comprises a machine case, a flowing groove sealing piece and a tapered impeller; the tapered impeller is arranged in the machine case in a sealed manner by the flowing groove sealing piece; a flowing groove and a mixed flow blade are arranged on the outer surface of the tapered impeller; the air inlet end of the mixed flow blade is provided with an air guide wheel opposite to a flowing inlet angle; the air outlet end of the mixed flow blade is provided with a flow splitting blade for preventing vortex; the structures of the low-pressure mixed flow air compression assembly and the high-pressure mixed flow air compression assembly are the same. The mixed flow air compressor has high-grade compression ratio and high compression efficiency and can be connected in a plurality of grades to be used; the mixed flow air compressor has the advantages of greater surge margin, simple structure, small size and weight, small windward area, great mass flow in unit area and the like.
Description
Technical field
The present invention relates to technical field of engines, refer in particular to a kind of aeroengine mixed-flow compressor.
Background technique
Existing Axial Flow Compressor pressure ratio is low, average level pressure ratio wretched insufficiency 1.37, for reach design pressure ratio needed for progression many, weight and size large, surge margin is low, anti-surge structure and control system complicated;
Centrifugal compressor level pressure ratio is high, can reach 4 even higher, and surge margin is large, but flow losses are large, and wind-exposuring area is large, and weight is also larger.
Summary of the invention
For the defect that prior art exists, the object of the invention is to propose a kind of aeroengine mixed-flow compressor.
Technological scheme of the present invention is:
A kind of aeroengine mixed-flow compressor, comprise low pressure mixed flow to calm the anger assembly, high pressure mixed flow is calmed the anger assembly, Diffuser and rectifier, described low pressure mixed flow is calmed the anger after assembly and is set gradually the first Diffuser, first rectifier, high pressure mixed flow is calmed the anger assembly, second Diffuser and the second rectifier, described low pressure mixed flow assembly comprises casing, circulation groove Sealing, and pyramidal lobe wheel composition, described cone impeller is arranged on casing inside by the sealing of circulation groove Sealing, the outer surface of described cone impeller is provided with circulation groove and mixed flow blade, the inlet end of mixed flow blade is provided with the inducer of flowing inlet angle relatively, there are the splitterr vanes of anti-eddy current the outlet side of mixed flow blade, described low pressure mixed flow assembly is identical with high pressure mixed flow modular construction.
As the preferred technical solution of the present invention, described circulation groove Sealing is the taper sheath mated with cone impeller, described cone impeller overcoat has circulation groove Sealing, the outer wall of described circulation groove Sealing is provided with many untouchable labyrinth seal groove A, the cone space of an accommodation cone impeller is provided with in described casing, the inwall of described cone space is provided with many untouchable labyrinth seal groove B coordinated with circulation groove Sealing, and circulation groove Sealing and cone impeller are fixed as an entirety.
As the preferred technical solution of the present invention, the outer surface of described cone impeller is provided with the mixed flow blade of the projection that a circle circumferentially distributes, equidistantly distribute between mixed flow blade, be circulation groove between adjacent mixed flow blade, mixed flow blade comprises sweepforward blade, diametrically blade and backward-swept blade.
As the preferred technical solution of the present invention, the conical surface of described cone impeller is 45 degree relative to the angle of inclination of its central shaft.
Advantageous Effects of the present invention is:
The respective advantage of combined axis flow air compressor of the present invention and centrifugal compressor, combination proposes mixed-flow compressor, the existing centrifugal radial motion of air-flow, there is again axial flow axial motion, existing level pressure ratio is high, and having again the advantage that flow losses are little and surge margin is large, is that aeroengine compression stage is few, pressure ratio is high, flow losses are few, and structure is simple, and dimensional weight is little, the advantages such as wind-exposuring area is little are the requisite core components of aeroengine.Particularly when main duct flow little (below 3kg/s), advantage is more obvious.
The present invention has that grade pressure ratio is high, and compression efficiency is high, can multistage string use, and surge margin is large, and structure is simple, the advantages such as dimensional weight is little, and wind-exposuring area is little, and the mass flow rate in unit area is larger.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is low pressure mixed-flow compressor ssembly drawing
Fig. 3 is the case structure schematic diagram of low pressure mixed-flow compressor
Fig. 4 is the structural representation of its circulation groove Sealing of low pressure mixed-flow compressor
Fig. 5 is the cut-away view of its cone impeller of low pressure mixed-flow compressor
Fig. 6 is the plan view of its cone impeller of low pressure mixed-flow compressor
Number in the figure represents:
1, low pressure mixed flow is calmed the anger assembly; 11, casing; 12, circulation groove Sealing; 13, cone impeller; 14, circulation groove; 15, mixed flow blade; 16, inducer; 17, splitterr vanes; 2, the first Diffuser; 3, the first rectifier; 4, high pressure mixed flow is calmed the anger assembly; 5, the second Diffuser; 6, the second rectifier.
The object of the invention realization, functional characteristics and advantage will in conjunction with the embodiments, are described further with reference to accompanying drawing.
Embodiment
Should be appreciated that specific embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
Referring to figs. 1 through Fig. 6, the invention provides a kind of aeroengine mixed-flow compressor, comprise calm the anger assembly 1, high pressure mixed flow of low pressure mixed flow to calm the anger assembly 4, Diffuser and rectifier, described low pressure mixed flow is calmed the anger after assembly 1 and is set gradually the first Diffuser 2, first rectifier 3, high pressure mixed flow calms the anger assembly 4, second Diffuser 5 and the second rectifier 6, described low pressure mixed flow assembly 1 comprises casing 11, circulation groove Sealing 12 and cone impeller 13 and forms, and the conical surface of cone impeller 13 is 45 degree relative to the angle of inclination of its central shaft.It is inner that described cone impeller 13 is arranged on casing 11 by circulation groove Sealing 12 sealing, described circulation groove Sealing 12 is the taper sheath mated with cone impeller 13, described cone impeller 13 overcoat has circulation groove Sealing 12, the outer wall of described circulation groove Sealing 12 is provided with many untouchable labyrinth seal groove A, the cone space of an accommodation cone impeller 13 is provided with in described casing 11, the inwall of described cone space is provided with many untouchable labyrinth seal groove B coordinated with circulation groove Sealing 12, and circulation groove Sealing 12 and disk of conical profile 13 are fixed together.The outer surface of described cone impeller 13 is provided with circulation groove 14 and mixed flow blade 15, and the outer surface of cone impeller 13 is provided with the mixed flow blade 15 of the projection that a circle circumferentially distributes, and equidistantly distributes between mixed flow blade 15, is circulation groove 14 between adjacent mixed flow blade 15.Mixed flow blade 15 comprises sweepforward blade, diameter propeller and backward-swept blade.The inlet end of mixed flow blade 15 is provided with the inducer 16 of flowing inlet angle relatively, and there are the splitterr vanes 17 of anti-eddy current the outlet side of mixed flow blade 15, and described low pressure mixed flow assembly is similar with high pressure mixed flow modular construction.
Cone impeller 13 has the inclination conical surface of inclination miter angle, and the conical surface is provided with circulation groove 14 and mixed flow blade 15, and mixed flow blade inlet end has the inducer 16 of corresponding relative flowing inlet angle, and there are the splitterr vanes 17 of anti-eddy current outlet side.During main duct ultra-low quantity of flow, adopt circulation groove Sealing sealant flow groove, circulation groove Sealing outer wall is provided with the non-contact labyrinth seal (i.e. raised line on the outer wall of above-mentioned circulation groove Sealing is or/and groove) of anti-backflow.
Working principle: height mixed-flow compressor, by each self-corresponding turbine drives, when air enters low pressure mixed-flow compressor inducer, import with suitable flow inlet angle, also make air-flow slow down in inducer supercharging simultaneously, when air-flow enters mixed flow disk of conical profile, air-flow is under the centrifugal action of mixed flow blade, throw away at a high speed impeller and compress supercharging simultaneously, when air-flow enters Diffuser, flow slowing down be the further increase of static pressure by kinetic transformation, when air-flow enters rectifier (being vaned Diffuser in fact), by the air-flow of spiral, be rectified into axial flow (also having part radial direction).When air-flow enters high pressure mixed-flow compressor, process is the same with low pressure compressor, and pressure improves further, then the diffusion that slows down enters firing chamber.Firing chamber high-temperature high-speed airflow out, through respective guider, drives respective turbine.
The foregoing is only the preferred embodiments of the present invention; not thereby the scope of the claims of the present invention is limited; every equivalent structure transformation utilizing description of the present invention to do; or directly or indirectly use the technical field being attached to other Related products, be all in like manner included in scope of patent protection of the present invention.
Claims (4)
1. an aeroengine mixed-flow compressor, it is characterized in that, comprise low pressure mixed flow to calm the anger assembly, high pressure mixed flow is calmed the anger assembly, Diffuser and rectifier, described low pressure mixed flow is calmed the anger after assembly and is set gradually the first Diffuser, first rectifier, high pressure mixed flow is calmed the anger assembly, second Diffuser and the second rectifier, described low pressure mixed flow assembly comprises casing, circulation groove Sealing, and pyramidal lobe wheel composition, described cone impeller is arranged on casing inside by the sealing of circulation groove Sealing, the outer surface of described cone impeller is provided with circulation groove and mixed flow blade, the inlet end of mixed flow blade is provided with the inducer of flowing inlet angle relatively, there are the splitterr vanes of anti-eddy current the outlet side of mixed flow blade, described low pressure mixed flow assembly is identical with high pressure mixed flow modular construction.
2. aeroengine mixed-flow compressor according to claim 1, it is characterized in that, described circulation groove Sealing is the taper sheath mated with cone impeller, described cone impeller overcoat has circulation groove Sealing, the outer wall of described circulation groove Sealing is provided with many untouchable labyrinth seal groove A, the cone space of an accommodation cone impeller is provided with in described casing, the inwall of described cone space is provided with many untouchable labyrinth seal groove B coordinated with circulation groove Sealing, and circulation groove Sealing and disk of conical profile are fixed as an entirety.
3. aeroengine mixed-flow compressor according to claim 2, it is characterized in that, the outer surface of described cone impeller is provided with the mixed flow blade of the projection that a circle circumferentially distributes, equidistantly distribute between mixed flow blade, be circulation groove between adjacent mixed flow blade, mixed flow blade comprises sweepforward blade, diametrically blade and backward-swept blade.
4. aeroengine mixed-flow compressor according to claim 3, is characterized in that, the conical surface of described cone impeller is 25--65 degree relative to the angle of inclination of its central shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410545599.7A CN104389800B (en) | 2014-10-15 | 2014-10-15 | Mixed flow air compressor of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410545599.7A CN104389800B (en) | 2014-10-15 | 2014-10-15 | Mixed flow air compressor of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104389800A true CN104389800A (en) | 2015-03-04 |
| CN104389800B CN104389800B (en) | 2017-04-12 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410545599.7A Active CN104389800B (en) | 2014-10-15 | 2014-10-15 | Mixed flow air compressor of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104389800B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105386998A (en) * | 2015-11-27 | 2016-03-09 | 中国航空动力机械研究所 | Returning device and double-stage combined air compressor with same |
| CN108252935A (en) * | 2016-12-29 | 2018-07-06 | 上海鼓风机厂有限公司 | Multistage culvert type axial flow compressor |
| WO2020097951A1 (en) * | 2018-11-15 | 2020-05-22 | 海明（江苏）环境科技有限公司 | Closed fan for ship |
| CN113217410A (en) * | 2021-06-17 | 2021-08-06 | 浙江理工大学 | Ternary blade centrifugal blower suitable for near space |
| CN113833679A (en) * | 2021-09-16 | 2021-12-24 | 势加透博洁净动力如皋有限公司 | Compressor capable of reducing air flow loss |
| CN113982988A (en) * | 2020-04-16 | 2022-01-28 | 李伟 | Centrifugal axial flow turbine and novel jet engine mode and operation method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08170598A (en) * | 1994-12-16 | 1996-07-02 | Toshiba Corp | Centrifugal compressor |
| JPH0949498A (en) * | 1995-06-01 | 1997-02-18 | Ishikawajima Harima Heavy Ind Co Ltd | Multistage compressor |
| CN1281953A (en) * | 1999-07-15 | 2001-01-31 | 株式会社日立制作所 | Turbomachine |
| JP2001248593A (en) * | 2000-03-03 | 2001-09-14 | Ishigaki Co Ltd | Mixed flow compressor with screw |
| JP2011226376A (en) * | 2010-04-20 | 2011-11-10 | Mitsubishi Heavy Ind Ltd | Turbo machine |
| EP2520763A2 (en) * | 2011-05-05 | 2012-11-07 | Rafael Advanced Defense Systems Ltd. | Impeller |
-
2014
- 2014-10-15 CN CN201410545599.7A patent/CN104389800B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08170598A (en) * | 1994-12-16 | 1996-07-02 | Toshiba Corp | Centrifugal compressor |
| JPH0949498A (en) * | 1995-06-01 | 1997-02-18 | Ishikawajima Harima Heavy Ind Co Ltd | Multistage compressor |
| CN1281953A (en) * | 1999-07-15 | 2001-01-31 | 株式会社日立制作所 | Turbomachine |
| JP2001248593A (en) * | 2000-03-03 | 2001-09-14 | Ishigaki Co Ltd | Mixed flow compressor with screw |
| JP2011226376A (en) * | 2010-04-20 | 2011-11-10 | Mitsubishi Heavy Ind Ltd | Turbo machine |
| EP2520763A2 (en) * | 2011-05-05 | 2012-11-07 | Rafael Advanced Defense Systems Ltd. | Impeller |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105386998A (en) * | 2015-11-27 | 2016-03-09 | 中国航空动力机械研究所 | Returning device and double-stage combined air compressor with same |
| CN108252935A (en) * | 2016-12-29 | 2018-07-06 | 上海鼓风机厂有限公司 | Multistage culvert type axial flow compressor |
| WO2020097951A1 (en) * | 2018-11-15 | 2020-05-22 | 海明（江苏）环境科技有限公司 | Closed fan for ship |
| CN113982988A (en) * | 2020-04-16 | 2022-01-28 | 李伟 | Centrifugal axial flow turbine and novel jet engine mode and operation method |
| CN113982988B (en) * | 2020-04-16 | 2023-04-25 | 李伟 | Centrifugal axial flow turbine and novel jet engine mode and operation method |
| CN113217410A (en) * | 2021-06-17 | 2021-08-06 | 浙江理工大学 | Ternary blade centrifugal blower suitable for near space |
| CN113833679A (en) * | 2021-09-16 | 2021-12-24 | 势加透博洁净动力如皋有限公司 | Compressor capable of reducing air flow loss |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104389800B (en) | 2017-04-12 |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| TR01 | Transfer of patent right |
Effective date of registration: 20191114 Address after: 215422 laozha West Street, Jinlang Town, Fuqiao Town, Taicang City, Suzhou City, Jiangsu Province Patentee after: Taicang Qiujing Plastic Mould Co., Ltd. Address before: 528099 Guangdong province Foshan city Chancheng District 1 room 811 source Patentee before: Chen Yuanjin |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20201105 Address after: Room 308, No.6 office building, No.1, Lugong Road, Port Development Zone, Fuqiao Town, Taicang City, Jiangsu Province, 215400 Patentee after: Suzhou Zhilue Intellectual Property Operation Co., Ltd Address before: 215422 laozha West Street, Jinlang Town, Fuqiao Town, Taicang City, Suzhou City, Jiangsu Province Patentee before: TAICANG QIUJING PLASTIC MOULD Co.,Ltd. |
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| TR01 | Transfer of patent right |