CN110360133A - A kind of through-flow structure of gas turbine compressor - Google Patents

A kind of through-flow structure of gas turbine compressor Download PDF

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Publication number
CN110360133A
CN110360133A CN201910552631.7A CN201910552631A CN110360133A CN 110360133 A CN110360133 A CN 110360133A CN 201910552631 A CN201910552631 A CN 201910552631A CN 110360133 A CN110360133 A CN 110360133A
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China
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level
angle
branch
flow
gas turbine
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CN201910552631.7A
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CN110360133B (en
Inventor
房骏翌
齐永春
马贺
孟亮
鲍丛
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Liaoning Fuan Gas Turbine Co Ltd
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Liaoning Fuan Gas Turbine Co Ltd
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08Centrifugal pumps
    • F04D17/10Centrifugal pumps for compressing or evacuating
    • F04D17/12Multi-stage pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/06Lubrication
    • F04D29/063Lubrication specially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/26Rotors specially for elastic fluids
    • F04D29/28Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/286Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/42Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44Fluid-guiding means, e.g. diffusers
    • F04D29/441Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/66Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/662Balancing of rotors

Abstract

The invention belongs to the compressor technical fields of middle-size and small-size gas turbine, more particularly to a kind of through-flow structure of gas turbine compressor, including, level-one branched bottom, the quantity of level-one branched bottom is eight equal parts, the meet of level-one branched bottom is equipped with circular passage, and the gap between level-one branched bottom is uniformly equipped with second level branch bend, and circular passage is converged with the inlet end of second level branch bend docks.The present invention passes through reciprocal transformation's level-one branched bottom and second level branch bend, through-flow layout is carried out by the elbow structure of bypass, make to can be reversed air inlet between two-stage, back-to-back mode is to offset the axial force of centrifugal impeller, series connection is mutually carried out by respective 8 branches converges connection formation complete annular channel, make the air inlet uniformity of second level branch bend, improve the stagnation pressure of compressor significantly, the configuration of the present invention is simple, the through-flow structural volume of compressor is small, lightweight construction, pressure ratio is uniform, air inlet excellent.

Description

A kind of through-flow structure of gas turbine compressor
Technical field
The invention belongs to turbomachinery technical fields, and in particular to a kind of through-flow structure of gas turbine compressor.
Background technique
The big core component of the three of gas turbine is respectively compressor, combustion chamber and turbine, and for the middle-size and small-size of small flow And miniature gas turbine, there is significant pneumatic and cost advantage using centrifugal compressor.Country's one-stage centrifugal compressor at present Pressure ratio reaches 5 or more, and between 1.5-4, this shows complete using two-stage centrifugal compressor the centrifugal compressor pressure ratio of technology maturation It can achieve the medium and small gas turbine optimum cycle pressure ratio of 8-11 entirely, and the axial flow compressor of same pressure ratio then generally requires 13 Grade or more pressurization, this will cause the significant increase of production cost, also be unfavorable for the optimization of package size.The whirlpool the WZ8 axis in China is sent out Motivation is that the small-sized boat hair of representative uses concatenated two stage centrifugal compressor, and this layout has significant size advantage, Axial dimension greatly is shortened, is suitable for the small-sized aerial crafts such as helicopter.But its really layout bring is high in the same direction for double centrifugations Pressure ratio also results in very big axial force, and making an inventory thrust bearing or balance, it is very high to require.And in GTCP85 auxiliary power unit Middle to have used double-suction centrifugal pump compressor+one-stage centrifugal compressor layout, wherein double-suction centrifugal pump compressor can compensate well for certainly The axial force of body, but there is still a need for additional counters for the axial force of its high-pressure compressor.
But the centrifugal impeller of reciprocal transformation needs that second level compressor is required to install special air inlet volute, this is in structure On bring inconvenience, increase the size of compressor, weight increase, and be unfavorable for compressor outlet air-flow it is equal Even property, causes pressure ratio uneven, and the pitot loss of compressor is very big, and the air inlet effect of the impeller of two-stage compressor is very poor, causes The performance of compressor is lower, efficiency decline, can not be to the improved efficiency of compressor, it will influences the overall effect of gas engine Rate.
Summary of the invention
The present invention provides a kind of through-flow structure of gas turbine compressor, it is therefore an objective to by the total of two-stage opposite type compressor Pressure improves, airflow homogeneity enhancing and diminution structure make weight saving.
To achieve the purpose of the present invention, the present invention provides a kind of through-flow structure of gas turbine compressor, including, level-one Branched bottom, the quantity of level-one branched bottom are eight equal parts, and the meet of level-one branched bottom is equipped with circular passage, level-one branch The gap of interchannel is uniformly equipped with second level branch bend, and circular passage is converged with the inlet end of second level branch bend docks; Level-one branched bottom includes one stage impeller outlet diameter D1, level-one diffuser intake diameter D2, level-one diffuser exit diameter D3、 Level-one diffuser exit angle α1, level-one circle angle of contingence α21, level-one branch boundaries diameter D4, level-one branch boundaries channel starting point C1, one Edge point C is faced in grade branch boundaries channel2, level-one channel width b1, level-one axis of great circle D5, level-one sector shrink channel α23, level-one fan Shape shrinks angle α22;Second level branch bend includes the minimum air inlet diameter D of second level6, second level highest air inlet diameter D7, second level diffuser Angle of outlet α4, second level circle angle of contingence α31, second level branch boundaries channel starting point C3, second level branch boundaries channel face edge point C4, second level it is logical Road width b4
Further, the level-one branched bottom is with the uniform cross-distribution of second level branch bend and in inlet end connection.
Further, the level-one circle angle of contingence α21Angle be equal to level-one diffuser exit angle α1Angle.
Further, the second level circle angle of contingence α31Angle be equal to second level diffuser exit angle α4Angle.
Further, the level-one branch boundaries diameter D4Less than or equal to level-one diffuser exit diameter D31.02 times.
Further, the level-one channel width b1Equal to level-one branch boundaries diameter D4Multiplied by the sin(level-one circle angle of contingence α21+ 22.5).
Further, the level-one sector shrinks channel α23Covering of the fan angle be 10 °.
Further, the level-one sector shrinks angle α22Channel α is shunk for level-one sector23Center line with it is corresponding circle Centerlines, level-one sector shrink angle α22∈ (0,6 °).
Further, the level-one branched bottom is equal with each throat opening area of bend of second level branch bend.
Further, the second level highest air inlet diameter D7Less than or equal to level-one axis of great circle D50.8 times.
The beneficial effects of the present invention are: the level-one branch, bend reciprocal transformation that the present invention is bypassed by two stage centrifugal compressor Channel and second level branch bend carry out through-flow layout by the elbow structure of bypass, make to can be reversed air inlet between two-stage, back to For the mode of back to offset the axial force of centrifugal impeller, balance is good, reduces the demand to thrust bearing or balancing frame, increases long-term The stability of operation can be such that the service life of thrust bearing or balancing frame greatly extends, and this structure guarantees two-stage centrifugal Impeller reciprocal transformation can offset each other axial thrust, and the requirement to thrust bearing can be greatly reduced, to reduce cost, and have There is better mechanical property;The level-one branched bottom and second level branch bend of reciprocal transformation, by respective 8 branches mutually into Row series connection, the circular rectors principle design such as reference, level-one branched bottom converge connection as unbroken loop before the bend import of second level branch Shape channel is docked with second level branch bend inlet end, makes the air inlet uniformity of second level branch bend, air inflow is balanced, knot of the present invention Structure is simple, reduces the through-flow structural volume of compressor, and the bend air inlet of second level branch does not depend on spiral case, can mitigate the weight of structure Amount, the available maximum pressure recovery coefficient of balanced air inlet, pressure ratio is uniform, and air inlet excellent, pitot loss is small, improves Overall performance.
Detailed description of the invention
Fig. 1 is schematic view of the front view of the invention;
Fig. 2 is right side view of the invention;
Fig. 3 is the front partial schematic sectional view of level-one branched bottom of the invention;
Fig. 4 is the rear portion partial schematic sectional view of level-one branched bottom of the invention;
Fig. 5 is the schematic diagram of through-flow meridian plane of the invention;
Fig. 6 is left view schematic diagram of the invention.
Specific embodiment
Hereinafter, will the invention will be further described in conjunction with attached drawing:
In figure: 1 level-one branched bottom, 11 circular passages, 2 second level branch bends.
In conjunction with shown in Fig. 1, Fig. 2, Fig. 3, Fig. 4 and Fig. 5, a kind of gas turbine compressor disclosed in this invention is logical Flow structure, including, level-one branched bottom 1, the quantity of level-one branched bottom 1 is eight and is uniformly distributed, the remittance of level-one branched bottom 1 Circular passage 11 is equipped at conjunction, the gap between level-one branched bottom 1 is uniformly equipped with second level branch bend 2, circular passage 11 Converge with the inlet end of second level branch bend 2 and docks;Level-one branched bottom 1 includes one stage impeller outlet diameter D1, level-one diffusion Device inlet diameter D2, level-one diffuser exit diameter D3, level-one diffuser exit angle α1, level-one circle angle of contingence α21, level-one branch side Boundary diameter D4, level-one branch boundaries channel starting point C1, level-one branch boundaries channel face edge point C2, level-one channel width b1, level-one it is big Circular diameter D5, level-one sector shrink channel α23, level-one sector shrink angle α22;Second level branch bend 2 includes the minimum air inlet of second level Diameter D6, second level highest air inlet diameter D7, second level diffuser exit angle α4, second level circle angle of contingence α31, second level branch boundaries channel rise Point C3, second level branch boundaries channel face edge point C4, secondary passage width b4;Level-one branched bottom 1 and second level branch bend 2 are uniform Cross-distribution and in inlet end connection, level-one circle angle of contingence α21Angle be equal to level-one diffuser exit angle α1Angle, two Grade circle angle of contingence α31Angle be equal to second level diffuser exit angle α4Angle, level-one branch boundaries diameter D4Less than or equal to one Grade diffuser exit diameter D31.02 times, level-one channel width b1Equal to level-one branch boundaries diameter D4Multiplied by sin(level-one circle Angle of contingence α21+ 22.5), level-one sector shrinks channel α23Covering of the fan angle be 10 °, level-one sector shrink angle α22For level-one fan Shape shrinks channel α23Center line and corresponding circle center wire clamp angle, level-one sector shrinks angle α22∈ (0,6 °), level-one branch are logical Road is equal with each throat opening area of bend of second level branch bend, second level highest air inlet diameter D7It is straight less than or equal to level-one great circle Diameter D50.8 times.
Embodiment one:
The centrifugal compressor of reciprocal transformation is connected by multiple level-one branched bottoms 1 with second level branch bend 2, first order pressure Mechanism of qi diffuser exit connects 8 level-one branched bottoms 1, and the circular rectors principle design such as channel reference forms sky at diffuser rear Gap, so that second level branch bend 2 passes through, it is logical that level-one branched bottom 1 is merged into as complete annular before 2 import of second level branch bend Road.
Second level blower outlet bend equally uses 8 second level branch bends 2 to draw, channel design method and the first phase Together, gap (interleaved) of the channel across first order bend branch, then completes to converge in collection chamber, into next list Member.The reversed air inlet of two-stage centrifugal impeller, back-to-back part is to offset axial force.The present invention allows to the curved of level-one branched bottom 1 Road part is adjusted, and bend is changed to heat exchanger channel, to introduce cascade EDFA system between two stage compressor, is improved Compressor efficiency.
Embodiment two:
Two-stage centrifugal compressor is using reversed layout back-to-back, and referring to shown in Fig. 2, Fig. 3, Fig. 4 and Fig. 5, one stage impeller outlet is straight Diameter D1Width, the level-one diffuser intake diameter D in the section in the channel at place2The width and level-one diffuser in the section in the channel at place Outlet diameter D3The width in the section in the channel at place is equal;Diffuser inside circular passage 11 forms level-one diffuser exit angle α1;Diffuser forms second level diffuser exit angle α at the second level4
It is level-one diffuser exit angle α according to first order compressor diffuser outlet blade angle1To determine first order bend boundary Angle with place circle tangent line is level-one circle angle of contingence α21, it is desirable that α211.The level-one branch boundaries of branched bottom inlet diameter are straight Diameter D4With level-one diffuser exit diameter D3Comparison be D4≤1.02D3.Take D4Locate any point as first branched bottom side Boundary's starting point, the point are level-one branch boundaries channel starting point C1, 8 equal part of circumference array takes adjacent edge as level-one branch side later Boundary faces in channel edge point C2Starting point, it is desirable that C2With C1In parallel, it can determine level-one channel width b at this time1=D4× sin(α21+ 22.5).
First order compressor bend extends radially to level-one axis of great circle D5Place, subsequently into racetrack portion, racetrack portion Deflection takes place, meet before bend latter half to second level compressor impeller import shrinks channel to be fan-shaped, and sector is received The angle level-one sector in contracting channel shrinks channel α23=10 °, channel centerline is level-one fan with the angle that corresponding circle center line is formed Shape shrinks angle α22, level-one sector contraction angle α22∈ (0,6 °), can be according to centrifugal compressor revolving speed and section of diameter at Air-flow peripheral speed determines α22Value, but should not exceed 6 °, branched bottom meet answers rounded corner R2, R2∈ (1,5).
One stage impeller outlet diameter D before impeller outlet to 180 ° of bend imports1The width in the section in the channel at place, level-one Diffuser intake diameter D2Width, the level-one diffuser exit diameter D in the section in the channel at place3The width in the section in the channel at place, Level-one branch boundaries diameter D4The width in the section in the channel at place can be set according to compressor design conditions, before 180 ° of bends Level-one branch boundaries diameter D afterwards4The width and level-one axis of great circle D in the section in the channel at place5The width in the section in the channel at place It is equal, wherein level-one axis of great circle D5The width in the section in the channel at place is the width in the fan-shaped section for shrinking channel after bend. It is exported to before sector channel converges import from 180 ° of bends, level-one axis of great circle D5The width and second level in the section in the channel at place are most Low air inlet diameter D6(D should be can satisfy between the width in the section in the channel at place5Its cross-sectional passage width × D at place5= D6Place Its cross-sectional passage width × D6), this ensure that through-flow throat opening area, keeps the amount of air inlet balanced.
The racetrack portion design of the second level branch bend 2 of two-stage compressor is identical as the first order, can determine second level circle respectively Angle of contingence α31, second level branch boundaries channel starting point C3, second level branch boundaries channel face edge point C4, secondary passage width b4Etc. second levels Compressor bend converges after 180 ° of bend pipes with collection chamber or spiral case etc., is then discharged out compressor.It can be by 180 ° of bends most The second level highest air inlet diameter D of high point7≤0.8D5It is designed, and width should be less than the gap of level-one bend branch herein.Eight Structure that equal part air inlet is through-flow avoids traditional dependence air inlet volute air inlet, simplifies whole structure, be effectively guaranteed into The uniformity of gas, in the back-to-back design of the two-stage centrifugal compressor designed by equivalent, both ends air inlet it is uniform and steady It is completely counterbalanced by the axial force of opposite direction, the service life of axial lubricating device can be increased, ensure that shaft Steady efficient operation, while the generation of surge phenomenon is avoided, promote arriving for the overall pressure tatio of compressor, more reasonable structure Design reduces outer dimension, also there is corresponding mitigation to weight, ensure that the present invention can open on middle-size and small-size gas turbine To great significant effect, traditional technical barrier is captured, high substantial effect is brought.
The bend reciprocal transformation level-one branched bottom 1 and second level branch bend that the present invention is bypassed by two stage centrifugal compressor 2, through-flow layout is carried out by the elbow structure of bypass, makes to can be reversed air inlet between two-stage, back-to-back mode with offset from The axial force of lobus cardiacus wheel, balance is good, reduces the demand to thrust bearing or balancing frame, increases long-term running stability, can So that the service life of thrust bearing or balancing frame greatly extends, this structure guarantees that two-stage centrifugal impeller reciprocal transformation can be mutual Axial thrust is offseted, the requirement to thrust bearing can be greatly reduced, to reduce cost, and there is better mechanical property Energy;The level-one branched bottom 1 and second level branch bend 2 of reciprocal transformation, are mutually connected by respective 8 branches, reference Etc. the design of circular rectors principle, level-one branched bottom 1 converge connection before 2 import of second level branch bend as complete annular channel, with The docking of 2 inlet end of second level branch bend makes the air inlet uniformity of second level branch bend 2, and air inflow is balanced, the configuration of the present invention is simple, Reduce the through-flow structural volume of compressor, 2 air inlet of second level branch bend does not depend on spiral case, can mitigate the weight of structure, balanced The available maximum pressure recovery coefficient of air inlet, pressure ratio is uniform, and air inlet excellent, pitot loss is small, improve complete machine Energy.
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, Er Qie In the case where without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter From the point of view of which point, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power Benefit requires rather than above description limits, it is intended that all by what is fallen within the meaning and scope of the equivalent elements of the claims Variation is included within the present invention, and any reference signs in the claims should not be construed as limiting the involved claims.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should It considers the specification as a whole, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art The other embodiments being understood that.

Claims (10)

1. a kind of through-flow structure of gas turbine compressor, it is characterised in that: including level-one branched bottom, level-one branch leads to The quantity in road is eight equal parts, and the meet of level-one branched bottom is equipped with circular passage, and the gap between level-one branched bottom is uniform Be equipped with second level branch bend, circular passage is converged with the inlet end of second level branch bend docks;Level-one branched bottom includes one Grade impeller outlet diameter D1, level-one diffuser intake diameter D2, level-one diffuser exit diameter D3, level-one diffuser exit angle α1、 Level-one justifies angle of contingence α21, level-one branch boundaries diameter D4, level-one branch boundaries channel starting point C1, level-one branch boundaries channel face side Point C2, level-one channel width b1, level-one axis of great circle D5, level-one sector shrink channel α23, level-one sector shrink angle α22;Second level Branch's bend includes the minimum air inlet diameter D of second level6, second level highest air inlet diameter D7, second level diffuser exit angle α4, second level circle cut Line angle α31, second level branch boundaries channel starting point C3, second level branch boundaries channel face edge point C4, secondary passage width b4
2. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: a fraction Subchannel is with the uniform cross-distribution of second level branch bend and in inlet end connection.
3. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: the level-one circle Angle of contingence α21Angle be equal to level-one diffuser exit angle α1Angle.
4. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: the second level circle Angle of contingence α31Angle be equal to second level diffuser exit angle α4Angle.
5. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: a fraction Branch boundary diameter D4Less than or equal to level-one diffuser exit diameter D31.02 times.
6. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: the level-one is logical Road width b1Equal to level-one branch boundaries diameter D4Multiplied by sin(level-one circle angle of contingence α21+ 22.5).
7. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: the level-one fan Shape shrinks channel α23Covering of the fan angle be 10 °.
8. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: the level-one fan Shape shrinks angle α22Channel α is shunk for level-one sector23Center line and corresponding circle center wire clamp angle, level-one sector shrinks angle α22∈ (0,6 °).
9. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: a fraction Subchannel is equal with each throat opening area of bend of second level branch bend.
10. a kind of through-flow structure of gas turbine compressor according to claim 1, it is characterised in that: the second level Highest air inlet diameter D7Less than or equal to level-one axis of great circle D50.8 times.
CN201910552631.7A 2019-06-25 2019-06-25 Gas turbine compressor through-flow structure Active CN110360133B (en)

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4679990A (en) * 1984-12-28 1987-07-14 Matsushita Electric Industrial Co., Ltd. Electric blower
CN2174569Y (en) * 1993-09-29 1994-08-17 李顺朴 Shell recoil gas turbine
CN1601114A (en) * 2003-09-26 2005-03-30 M·米勒电气有限责任公司 Side channel compressor with annular casing
CN104612983A (en) * 2015-01-29 2015-05-13 湖南天雁机械有限责任公司 Uniaxial tandem type two-stage compressor
CN205592195U (en) * 2016-04-29 2016-09-21 常州兰翔机械有限责任公司 Tubular diffuser for compressor
CN106895012A (en) * 2017-05-05 2017-06-27 大连依勒斯涡轮增压技术有限公司 A kind of compact two-step supercharging compressor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4679990A (en) * 1984-12-28 1987-07-14 Matsushita Electric Industrial Co., Ltd. Electric blower
CN2174569Y (en) * 1993-09-29 1994-08-17 李顺朴 Shell recoil gas turbine
CN1601114A (en) * 2003-09-26 2005-03-30 M·米勒电气有限责任公司 Side channel compressor with annular casing
CN104612983A (en) * 2015-01-29 2015-05-13 湖南天雁机械有限责任公司 Uniaxial tandem type two-stage compressor
CN205592195U (en) * 2016-04-29 2016-09-21 常州兰翔机械有限责任公司 Tubular diffuser for compressor
CN106895012A (en) * 2017-05-05 2017-06-27 大连依勒斯涡轮增压技术有限公司 A kind of compact two-step supercharging compressor

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