CN108035891A - Single stage centrifugal high pressure ratio compressor - Google Patents
Single stage centrifugal high pressure ratio compressor Download PDFInfo
- Publication number
- CN108035891A CN108035891A CN201810032428.2A CN201810032428A CN108035891A CN 108035891 A CN108035891 A CN 108035891A CN 201810032428 A CN201810032428 A CN 201810032428A CN 108035891 A CN108035891 A CN 108035891A
- Authority
- CN
- China
- Prior art keywords
- compressor
- pressure ratio
- air
- impeller
- stage centrifugal
- 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
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
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
-
- 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
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
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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
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
本发明涉及单级离心式高压比压气机。包括进气室、压气机定子和转子三部分，压气机定子包括由进气口外壳和进气口护罩组成的波状外形进气通道、进气口支架及扩压器组成；压气机转子由转子轴、径向轴承、套筒、推力轴承及叶片组成，转子轴由径向轴承和推力轴承支撑，径向轴承在靠近叶轮侧设置有密封，推力轴承两侧均设置有密封；叶片为半开后弯式结构，由导流片Ⅰ、导流片Ⅱ和一个叶轮组合而成。本发明单级离心式高压比压气机结构简单，压气比相较传统压气机进一步提高。
The invention relates to a single-stage centrifugal high-pressure ratio compressor. It consists of three parts: the air intake chamber, the compressor stator and the rotor. The compressor stator consists of a corrugated air intake channel composed of the air intake shell and the air intake shield, the air intake bracket and the diffuser; the compressor rotor is composed of Composed of rotor shaft, radial bearing, sleeve, thrust bearing and blades, the rotor shaft is supported by the radial bearing and the thrust bearing, the radial bearing is provided with a seal on the side close to the impeller, and both sides of the thrust bearing are provided with seals; the blade is half Open back curved structure, composed of deflector Ⅰ, deflector Ⅱ and an impeller. The single-stage centrifugal high-pressure ratio air compressor of the invention has a simple structure, and the air-compression ratio is further improved compared with the traditional air compressor.
Description
Technical field
The present invention relates to a kind of centrifugal air compressor, is exclusively used in producing in small size gas turbine more particularly to one kind
The compressor of gases at high pressure.
Background technology
The composition of gas turbine is divided into compressor, combustion chamber and turbine three parts.The compressor of gas turbine is big at present
All use multiatage axial flow structure type.Single-stage pressure ratio is relatively low, it is necessary to plural serial stage uses, so as to cause blade more, assembler
The shortcomings of work amount is big, and axial dimension is long.Centrifugal air compressor press pressure ratio is high, and simple in structure, rotor axial is apart from short.Mesh
Before, the high pressure ratio of domestic single-stage radial compressor is 4 or so, it is also necessary to improves the pressure ratio of air compressor to further improve
The overall efficiency of gas engine.
The content of the invention
The present invention provides a kind of single stage centrifugal high pressure ratio compressor, to improve the pressure ratio of air compressor, so that into one
Step improves the overall efficiency of gas engine.
The present invention is that technical solution is used by solving its technical problem：A kind of single stage centrifugal high pressure ratio is provided to calm the anger
Machine, including inlet plenum, compressor stator and rotor three parts.The compressor stator is included by air inlet shell and air inlet
Contoured inlet channel, air inlet stent and the diffuser composition of shield composition；The compressor rotor is by armature spindle, footpath
Formed to bearing, sleeve, thrust bearing and blade, armature spindle is supported by journal bearing and thrust bearing, and journal bearing is close
Impeller side is provided with sealing, and thrust bearing both sides are both provided with sealing；The blade is half-open swept-back structure, by flow deflector
Ith, flow deflector II and an impeller are composed.
As a preferred embodiment of the present invention, the flow deflector is made of stainless steel material, and impeller is closed using titanium
Golden material is made.
As a preferred embodiment of the present invention, corrosion-resistance treatment is carried out to the flow deflector.
Having the beneficial effect that acquired by the present invention：
By setting the combination of three-stage blade to increase axial length so that overall runner axial length is than same type blade more
It is long；
Three-stage blade includes flow deflector I, flow deflector II and impeller, and flow deflector can force air-flow to be transferred, to reduce leaf
Take turns the influence of the entrance air-flow angle of attack；
Blade uses backward bent vane so that impeller air stream outlet angle is larger, and diffuser efficiency thereafter is high, and air-flow passes through diffusion
Kinetic energy can be more converted into pressure energy after device；
Blade uses semi-open type blade, and intensity is high, it is allowed to peripheral speed it is high, thus single pressure ratio is high.
Above-mentioned advantage advantageously reduces flow passage resistance force of waterproof, can effectively improve pressure ratio.
Brief description of the drawings
Fig. 1 is the structure diagram of the present invention.
1st, inlet plenum, 2, air inlet shell, 3, air inlet shield, 4, journal bearing, 5, armature spindle, 6, journal bearing it is close
Envelope, 7, sleeve, 8, air inlet stent, 9, diffuser, 10, flow deflector I, 11, flow deflector II, 12, impeller, 13, thrust bearing it is close
Envelope I, 14, thrust bearing sealing II, 15, thrust bearing.
Embodiment
Below in conjunction with attached drawing and specific embodiment, the present invention is further illustrated.
It is as shown in Figure 1 the structure diagram of the present invention.Including inlet plenum 1, compressor stator and rotor three parts, calm the anger
Machine stator includes contoured inlet channel, air inlet stent 8 and the diffusion being made of air inlet shell 2 and air inlet shield 3
Device 9 forms；Compressor rotor is made of armature spindle 5, journal bearing 4, sleeve 7, thrust bearing 15 and blade, and armature spindle 5 is by footpath
Supported to bearing 4 and thrust bearing 15, sleeve 7 is connected with armature spindle 5, and journal bearing 4 is being provided with sealing close to impeller side, pushes away
15 both sides of power bearing are provided with sealing I and II.
Blade is made of two stainless steel diversion pieces and a titanium alloy impeller 12（Diameter phi 575mm, overall length
245mm）, flow deflector increases its corrosion resistance afterwards after further treatment.Blade is divided into three sections and uses different materials, so both
Easy to manufacture, and reduce cost.
Blade uses half-open backward bent vane, and the pressure ratio of overall air compressor machine can reach 6.3:1, greatly improve the effect of combustion engine
Rate.Using backward bent vane, in the case where the parameters such as rotating speed, flow are all identical, the exhausted degree speed that swept-back produces is smaller, and
Flow losses and speed square are inversely proportional, thus when fluid passes through blade, swept-back energy loss is smaller；In addition antecurvature formula
The dynamic pressure of generation is bigger than static pressure, and compressor should produce higher static pressure to overcome resistance to convey gas, if dynamic pressure is high, it is also necessary to
Static pressure is converted in spiral case, in the transfer must be with larger energy loss；The more antecurvature formula of runner of backward bent vane
It is longer, and swept-back even more further lengthening in length that three segments combined blade constructions of the invention are more general, so that
The diffusion of runner is smaller, fluid by when local losses it is smaller.
When compressor works, air enters from inlet plenum 1（Import：Pressure 1.013bar, 15 DEG C of temperature, air velocity
16m/s）, by the contoured inlet channel being made of air inlet shell 2 and air inlet shield 3, then by flow deflector I
10th, flow deflector II 11 and impeller 12, compressor rotate at a high speed（Rotating speed 18000r/min）The energy transmission of generation is to air, increase
Impeller 12 is left after the pressure and rotating speed of air stream, then air stream pressure after efficient diffuser 9 further increases, by speed
The energy of degree is converted into the pressure of static state（Outlet：Pressure 6.330bar, 272 DEG C of temperature, 93 m/s of air velocity）, it is then, high
Pressure air low speed is flowed into fuel chamber.
Claims (3)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810032428.2A CN108035891A (en) | 2018-01-12 | 2018-01-12 | Single stage centrifugal high pressure ratio compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810032428.2A CN108035891A (en) | 2018-01-12 | 2018-01-12 | Single stage centrifugal high pressure ratio compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108035891A true CN108035891A (en) | 2018-05-15 |
Family
ID=62096489
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810032428.2A Pending CN108035891A (en) | 2018-01-12 | 2018-01-12 | Single stage centrifugal high pressure ratio compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108035891A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114941630A (en) * | 2022-05-31 | 2022-08-26 | 江苏金通灵氢能机械科技有限公司 | Single-stage high-speed hydrogen fuel cell centrifugal compressor |
| CN116517881A (en) * | 2023-04-11 | 2023-08-01 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A compressor intake chamber structure with a bearing chamber |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0575763A1 (en) * | 1992-06-20 | 1993-12-29 | Robert Bosch Gmbh | Rotor for a radial fan |
| CN2769561Y (en) * | 2004-12-29 | 2006-04-05 | 中国船舶重工集团公司第七一一研究所 | Single-stage high-speed centrifugal compressor |
| US20100215508A1 (en) * | 2009-02-25 | 2010-08-26 | Behzad Hagshenas | Axially Segmented Impeller |
| CN102400960A (en) * | 2011-12-20 | 2012-04-04 | 中国船舶重工集团公司第七�三研究所 | Centrifugal oxygen-enriched air compressor and application thereof |
| CN104533816A (en) * | 2014-11-12 | 2015-04-22 | 中国科学院工程热物理研究所 | Radial diffuser testing device and testing method of centrifugal compressor |
| CN104895841A (en) * | 2015-04-30 | 2015-09-09 | 中国科学院工程热物理研究所 | Rectifier, runner structure, combined gas compressor and aviation gas turbine engine |
| CN105026689A (en) * | 2013-03-14 | 2015-11-04 | 埃利奥特公司 | Vane arrangement having alternating vanes with different trailing edge profile |
| CN105275874A (en) * | 2015-11-27 | 2016-01-27 | 中国航空动力机械研究所 | Single-stage centrifugal compressor |
| CN207892856U (en) * | 2018-01-12 | 2018-09-21 | 大连派思透平动力科技有限公司 | A kind of single stage centrifugal high pressure ratio compressor |
-
2018
- 2018-01-12 CN CN201810032428.2A patent/CN108035891A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0575763A1 (en) * | 1992-06-20 | 1993-12-29 | Robert Bosch Gmbh | Rotor for a radial fan |
| CN2769561Y (en) * | 2004-12-29 | 2006-04-05 | 中国船舶重工集团公司第七一一研究所 | Single-stage high-speed centrifugal compressor |
| US20100215508A1 (en) * | 2009-02-25 | 2010-08-26 | Behzad Hagshenas | Axially Segmented Impeller |
| CN102400960A (en) * | 2011-12-20 | 2012-04-04 | 中国船舶重工集团公司第七�三研究所 | Centrifugal oxygen-enriched air compressor and application thereof |
| CN105026689A (en) * | 2013-03-14 | 2015-11-04 | 埃利奥特公司 | Vane arrangement having alternating vanes with different trailing edge profile |
| CN104533816A (en) * | 2014-11-12 | 2015-04-22 | 中国科学院工程热物理研究所 | Radial diffuser testing device and testing method of centrifugal compressor |
| CN104895841A (en) * | 2015-04-30 | 2015-09-09 | 中国科学院工程热物理研究所 | Rectifier, runner structure, combined gas compressor and aviation gas turbine engine |
| CN105275874A (en) * | 2015-11-27 | 2016-01-27 | 中国航空动力机械研究所 | Single-stage centrifugal compressor |
| CN207892856U (en) * | 2018-01-12 | 2018-09-21 | 大连派思透平动力科技有限公司 | A kind of single stage centrifugal high pressure ratio compressor |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114941630A (en) * | 2022-05-31 | 2022-08-26 | 江苏金通灵氢能机械科技有限公司 | Single-stage high-speed hydrogen fuel cell centrifugal compressor |
| CN116517881A (en) * | 2023-04-11 | 2023-08-01 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A compressor intake chamber structure with a bearing chamber |
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Legal Events
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 116610 No. 73, Zhenpeng industrial city, Dalian Economic and Technological Development Zone, Liaoning Province Applicant after: Dalian oppner Turbine Power Technology Co.,Ltd. Address before: 116610 No. 73, Zhenpeng industrial city, Dalian Economic and Technological Development Zone, Liaoning Province Applicant before: DALIAN ENERGAS TURBINE POWER TECHNOLOGY Co.,Ltd. |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180515 |