CN1070721A - Compressor range stabilization - Google Patents
Compressor range stabilization Download PDFInfo
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- CN1070721A CN1070721A CN 91109578 CN91109578A CN1070721A CN 1070721 A CN1070721 A CN 1070721A CN 91109578 CN91109578 CN 91109578 CN 91109578 A CN91109578 A CN 91109578A CN 1070721 A CN1070721 A CN 1070721A
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Abstract
A kind of centrifugal compressor comprises the device that is used for the operating mode regional stability.It has a ventilation chamber, make the pressure between impeller and gas-entered passageway obtain equilibrium, gas-entered passageway has an air inlet ring, and it makes the air-flow in the gas-entered passageway influenced by this way becomes possibility, promptly both realize the stable of operating mode zone, and do not had obvious loss in efficiency.By the remodeling of air inlet ring, can make compressor adapt to special user's needs.
Description
The present invention relates to a kind of range stabilization of centrifugal compressor.This centrifugal compressor comprises a gas-entered passageway, impeller and one go out the gas area, impeller is arranged on gas-entered passageway and goes out between the gas area, and the rotation by impeller is transported to out the gas area with medium from gas-entered passageway, impeller changes with the sidewall shape around it along its axis its gabarit shape from the inlet diameter to the outlet diameter, this range stabilization comprises a ventilation chamber that extends to contoured wall from gas-entered passageway, this ventilation chamber communicates with main air flow in the gas-entered passageway by a connection opening, and communicates with main air flow by the connection opening at a profile inwall place between impeller leading edge and impeller trailing edge.
The development trend of current supercharged engine is to the high pressure development, even also be like this when low speed.And when utilizing existing common compressor, the operating mode zone of motor can be very near surge line, and moves in the noise range, and part surpasses surge line.
In order to improve the control apparatus of this class motor, the characteristic that compressor had should have wide working zone and wide high efficient area.
For satisfying above-mentioned requirements with existing equipment, adopting operating mode regional stability (RS) level in the gas-entered passageway of compressor is very effective feasible method.
The range stabilization of this ventilation chamber form is early known.Their air-flow angles of attack on acting on impeller are to turn round in the incorrect zone.
This range stabilization allows compressor to be able to stable operation in this critical operating point zone, and this is to compensate this disturbance by the surge volume that utilizes annular space to realize.If disturbance is obvious, between the circular groove and the cyclic space circulation takes place.In the surge line zone, impeller is subjected to having the air-flow effect of the more and more littler angle of attack, and the pressure in this out rotor is also rising.Air-flow group is sent back to compressor inlet as a result.The air-flow ratio piston compressor that sucks at impeller leading edge place see off generally more than.Cause the improvement of this operating point angle of attack, surge line then is offset to small flow.Impeller leading edge air-flow reaches the velocity of sound can cause choking limit.But at this moment, because the decline of pressure, and air sends into impeller via by-pass line, and choking limit will be offset to the right.The effect of this two aspect of range stabilization is exactly to exceed the operation area more or less.The desirable angle of attack and adjustment thereof are without any effect.
Utilization is connected in the bypass line compensatory pressure of different axial region and the technology by the bypass line balance pressure is known, specifically can be referring to DE-PS1428077.This technology (is seen K ü hnle, Kopp ﹠amp owing to the explanation of the outline article of HDHenssler further develops; Kausch, VGB Kraftwerkstechnik special issue 1977 the 57th phases No. 3).
The prior art of the up-to-date device of relevant operating mode regional stability is seen EP-A348674, EP-B229519 and GB-OS2220447.EP-B229519 and GB-OS2220447 disclose a kind of bypass line that directly imports the leading edge back side from gas inlet.Fluid by ventilation chamber is regulated to the pressure reduction of ventilation chamber with impeller leading edge front one opening, and this opening is called opening 1 hereinafter.Or use the pressure reduction of a opening to regulate from ventilation chamber to leaf, this opening is called opening 2 hereinafter.
Its shortcoming is that the flowing state of ventilation chamber is not contacted directly with the flowing state of the gas inlet of impeller leading edge front.Like this, have only groove to be used as the basic control point of adjusting.Wide groove perhaps can obviously be offset choking limit, and can obviously lower efficiency in the optimum condition district.Therefore, this structure is subjected to the restriction of permissible decrease in efficiency.
These disadvantageous performances are avoided in EP-A348674 like this, and promptly its inlet/outlet both is almost perpendicular to main air flow.By-pass line just can directly not be subjected to gas shock like this.This has just produced the bypass flow that the pressure reduction by the by-pass line import and export forms.
The shortcoming of this structure is that the by-pass line two ends all are positioned at the impeller front.The pressure reduction that this means by-pass line is under any circumstance all very little, and is just effective when therefore this structure only produces very large pressure gradient in the impeller front.
Yet desirable is stable should the beginning as early as possible, because stability characteristic (quality) just can expand to big discharge capacity zone like this.For the nominal situation point that drives motor, this means in low-speed range has higher efficient or running deposit in a big way (at the deposit of higher speed scope).
Another shortcoming of existing apparatus is that this operating mode stabilizer must adapt with type of compressor.The difference of compressor impeller structure, the position of the variation of profile and disturbance or surge region and intensity cause the clearly technical regulation that can't provide a design conditions stabilizer so far.So far can not predict to have reached an operating mode region of stability whether fully reliably, and measure in the given compressor, especially the degree of stability in the centrifugal compressor with its.According to present technology status, wish very much just can meet the demands with the parameter of very few number.
These shortcomings have caused the proposition of task of the present invention, and a kind of range stabilization of centrifugal compressor promptly is provided, and it can widen its working zone, and don't loss efficient.
Be conceived to the range stabilization that this specification begins the sort of type of part narration, this task is by be provided with an air inlet ring in the gas-entered passageway of existing range stabilization, its restriction main air flow and topped ventilation chamber, main air flow solves greater than a distance relatively.
According to above-mentioned feature, fluid is by playing the ventilation chamber of by-pass line effect in entry zone, and perpendicular to main air flow, additional eddy current and the relevant shortcoming at described opening all reduces to minimum like this in inwall place reality.Because the effect of air inlet ring, this zone are contacted directly with the flowing state of the main air flow of impeller front more consumingly.The other end of ventilation chamber or circular chamber enters impeller at the back of impeller leading edge opening.This just means that range stabilization moves under High Pressure Difference, the variation in pressure between so just ventilation chamber being imported and exported produce than according to the structure sensitivity of EP-OS348674 the effect of Duoing.The control effect is also more remarkable.By with being communicated with of impeller air-flow, in this structure, might adopt big pressure reduction.Because stable running state the invention enables in the optimum operation scope, the ventilation chamber pressure difference might be zero by structural adjustment, and in this working area, ventilation chamber cuts little ice like this, also without any loss in efficiency.
According to above-mentioned research, owing to adopt this structure, by optimizing inlet channel, the present invention also can make the compression function be applicable to new operating conditions.For this purpose, this structure is provided with an air inlet ring, and it influences the pressure difference of ventilation chamber by the variation of inlet flow state.Consequently to concrete application, range stabilization might be optimized in single letter, i.e. the size of air inlet ring internal diameter can be adjusted the flowing state of ventilation chamber.Along with air inlet ring internal diameter diminishes gradually, the flowing state of vent chamber just adapts with the flowing state or the hydrodynamic pressure of impeller leading edge front more nearly.
The feature of solution of the present invention also includes:
Replaceable and the adjustment of air inlet ring;
The air inlet diameter is 0.64 to 1.2 times of impeller trailing edge diameter, and optimum range is between 0.7 to 0.9;
The circular groove of direct fluid impeller had the angle of attack between 20 ° to 30 ° of the radial direction;
The width of circular groove is 0.55 to 0.7 times of impeller trailing edge width;
Has another circular groove at least, 1/4th of the suitable impeller trailing edge of its width width;
The determined axial position of distance of the circular groove of counting from the trailing edge of impeller is 0.15 to 0.3 times of impeller trailing edge diameter;
The position of inlet channel is the distance in distance impeller rear end, and this distance is 0.36 to 0.6 times of impeller trailing edge diameter;
The width of inlet channel is 1 to 1.1 with the ratio of the width of circular groove;
The ratio of the radially area of the cross-section area of ventilation chamber and circular groove is between 3.5 to 4.5;
The internal diameter of ventilation chamber is about 0.8 times of impeller trailing edge diameter;
The width of circular groove is 0.03 to 0.05 times of impeller trailing edge diameter.
The area of circular groove and impeller trailing edge diameter square ratio be between 0.106 to 0.151 times of hub ratio, this hub ratio is impeller inlet diameter and its trailing edge diameter ratio;
The volume of ventilation chamber is between three cubed 0.06 to 0.23 times of the impeller trailing edge diameter;
The end face of the gusset of support profiles ring is a rounding.
The further advantage and the measure of solution of the present invention will be set forth in the dependent claims.
Advantages and features of the invention, the description to embodiment can more be expressly understood in conjunction with the drawings.
Wherein:
Fig. 1 is the partial cross section figure with centrifugal compressor of range stabilization;
Fig. 2 is the partial cross section figure with centrifugal compressor of another kind of range stabilization;
Fig. 3 is the partial cross section figure with centrifugal compressor of the another kind of range stabilization of having made improved shape on the structure;
Fig. 4 is another partial cross section figure of another embodiment;
Fig. 5 is the partial cross section figure with embodiment of another kind of circular groove.
Fig. 6 is the partial cross section figure with embodiment of improved air inlet ring.
Fig. 1 is a kind of centrifugal compressor of representing with partial cross section figure, and it comprises the compressor housing 1 with impeller 49, and impeller is carried compressed gas medium from the left side of Fig. 1 to the right.Main air flow enters impeller 49 from gas-entered passageway 11, and flows into Diffuser 44 parts from trailing edge 46, is provided with the air inlet ring 10 that part is made of conical profile in the gas-entered passageway 11.
Be provided with a by-pass line with venting cavity 31 on inner walls, this venting cavity links to each other with gas-entered passageway via inlet channel 22, and communicates with main air flow via a circular groove 38 in the impeller contour area.Inlet channel 22 has stopped induction part, and its whole A/F 24 is arranged on the place ahead of impeller leading edge 2.The degree of depth of groove is radially extended, through air inlet ring 10 internal diameter 16, and be connected gusset 32 from the internal diameter 16 of gas-entered passageway 11 to shell inner surface and cut off.
Contour loop internal diameter 28 is equivalent to impeller diameter, leaves necessary rotary gap.The external diameter of contour loop 30 can greater than, be less than or equal to diameter 16.In the embodiment shown in fig. 1, its diameter group 16 is little.Contour loop remains on the concentric position of housing by gusset 32.This gusset is whole the casting on compressor housing 1, or in housing, mill out.Compressor housing 1 and air inlet ring 10 also can be made by single-piece.
Connecting tendon 32 also can be made one with contour loop 26 in another embodiment.In addition, contour loop 26 also can form an assembling part with connecting gusset 32 and another one outer shroud 27.Made of plastic when these parts, this group of device parts have special advantage.
But the leading edge of circular groove 38 also the side circle to become radius be the fillet of 0-4 millimeter.This fillet radius has reduced the development of the noise of sharp edge generation.Equate in above-mentioned two leading edge place fillet radius.
On the section 42 between circular groove 38 and the Diffuser section 44, another circular groove 138 can be set.This embodiment is illustrated among Fig. 5.The width of this circular groove 138 is significantly less than the width 36 of circular groove 38.
Operating mode zone stable is to be based upon by by air inlet ring 10, and compressor housing 1 and contour loop 26 formed ventilation chamber 31 realize isostasies, and by by on circular groove 22 and 38 formed connection opening 33 and 45 realizations and the basis that main air flow is communicated with.
The air inlet ring defines ventilation chamber by air inlet lateral section 15.Because the effect of taper circular groove 10 makes main air flow quicken towards impeller leading edge direction.
Air inlet ring attached jet causes the variation of flowing state, also influences flowing state in the ventilation chamber 31 by circular groove 22.By the size and the corresponding flow condition of decision circular groove 22 and 38, can determine the pressure at connection opening 33 and 45 places.In addition, the stable also necessary and type of compressor in operating mode zone, the position of circular groove on the impeller profile, its width and oblique position, and ventilation chamber volume, the position of the inlet channel of the contour shape of import and definite speed line feature adapts.When pressure difference was confirmed as zero in the design conditions zone, ventilation chamber was inoperative, and the characteristic of centrifugal compressor is unaffected in this zone, just inefficent loss.
If pressure is with respect to the ideal situation generation deviation of this setting, they will obtain balance by ventilation chamber so.This has just caused the steady working condition zone to the skew of the left side of optimum condition, and range of flow is to the right of optimum condition skew.The variation of two aspects makes the working zone obtain enlarging.
Because the operation mode of range stabilization depends on the flox condition of gas-entered passageway basically, just can be optimized easily by changing import ring 10.And the import ring that installs with a pin 12 and suitable structure is easy to change.
Except that the assembling of center, fixedly the connection gusset 32 of contour loop 26 also works to stablize axial flow.
In large-scale compressor, especially in the compressor of big hub ratio, quite wide connection gusset has caused a wake flow of sounding.Especially from opening 31 to opening 45 flow, produce a kind of high and noise spectrum of ringing.In this case, just can significantly improve by the connection gusset (Fig. 2) that shortens in the ventilation chamber, making has longer distance to leave air-flow for to eliminate the wake flow that connects gusset.
For fear of these shortcomings, the structure that Fig. 2 provides is preferably.Connect gusset and no longer contact, and plate is a rounding in Diffuser one side originally with groove.
Fig. 3 represents another kind of structure of the present invention.Opposite with Fig. 1, the circular groove 38 here is not to put in ventilation chamber 31 far away, and connection gusset 32 is circular towards the opening of circular groove 38.Become the ideal structure of an angle of attack 43 to compare with circular groove shown in Figure 1, in order to be convenient to assembling in produced in series, the degree of depth of groove is less.By inserting contour loop 26 mount pin 13 is fixed in the hole in the shell, rotates in order to preventing.The import that enters ventilation chamber is tilted as the front at opening 45 places.Towards the cross section 42, formed a radial engagement face, this helps the assembling of contour loop.Pin 13 prevents to rotate.
In the embodiment of Fig. 3, air inlet ring 10 is contained in the gas-entered passageway at Fig. 1, and fixing with pin 12.Another kind of modification is a structure shown in Figure 4.Inserting member 110 directly uses bolton on housing, and has determined the external diameter of ventilation chamber 31.This new structure is for making compressor be fit to user's needs.
Fig. 5 represents another kind of embodiment.Here ventilation chamber almost reaches the impeller trailing edge.In order to adjust the steady working condition district better, three circular grooves 22,45 and 38 are provided in this case.
Among the embodiment 4 shown in Figure 6, import diameter of section 16 is less than the contour loop diameter.This embodiment has the advantage that bigger acceleration can be arranged at gas-entered passageway, and the pressure reduction ratio in opening 33 zones and the ventilation chamber makes moderate progress.
As mentioned above, the operation mode in steady working condition zone depends on the flowing state in circular groove 22 and 38 places and the ventilation chamber 31 itself substantially.Flow condition at the connection opening place obviously is subjected to the circular groove influence.
By adjusting whole system, can obtain needed characteristic.And, more focus on and keep level of efficiency according to situation of the present invention.From this viewpoint, adjust range stabilization to remove choking limit, the result can offer the best.With regard to surge line, the working zone of certain specification compressor changes by hub ratio or compressor profile to be adjusted, and owing to compressor for certain specification, what adopt is the venting gas appliance of same specification, and therefore the size of this operating point stabilizer (RS) can adapt to discharge area or impeller easily.
Substantially to consider during adjustment following some:
1) adjustment of ventilation chamber 31 area sizes;
2), further adjust the flowing state of described vent chamber by the ventilation chamber in the topped more or less suction port of air inlet ring;
3) area of the circular groove above the impeller 38 and position;
4) angle of the angle of attack 43 of the circular groove above the impeller 38.
Provide the structure characteristic of these parameters of optimization below.
The width 36 of circular groove 38 is 0.55 to 0.7 times of impeller trailing edge width 50.
The circular groove width that forms is not more than 1/4th of impeller trailing edge width 50.
The axial dimension that is limited by the distance 56 between circular groove 38 and impeller 49 rear ends is 0.15 to 0.3 times of impeller trailing edge diameter 48.
The axial position of air inlet duct 22 is that described distance 58 is 0.3 to 0.6 times of impeller trailing edge diameter at distance impeller trailing edge distance 58 places.
The width 24 of inlet channel 22 is 1 to 1.1 times of circular groove 38 width 36.
The internal diameter 30 of ventilation chamber 31 is approximately 0.8 times of impeller trailing edge diameter 48.
The width 36 of circular groove 38 is 0.03 to 0.05 times of impeller trailing edge diameter 48.
The area of circular groove 38 and impeller trailing edge diameter 48 square ratio be 0.106 to 0.151 times of hub ratio.Hub ratio is to be determined by impeller inlet diameter 34 and the ratio of its outlet diameter 48, for example between 0.64 to 0.74.
The volume of ventilation chamber 31 is three cubed 0.06 and 0.23 times of impeller trailing edge diameter 48.
These narrow proportions clearly show that when design has the centrifugal compressor of range stabilization these parameters must strictly be noted.Given adjustment range shows that this scope is several must to keep specified value.The instruction that obtains from specific embodiment makes us can obtain a kind of range stabilization of centrifugal compressor, and it can not lower efficiency and can broaden the scope of work.
Claims (15)
1, a kind of range stabilization of centrifugal compressor, this centrifugal compressor comprises a gas-entered passageway (11), an impeller (49) and one go out gas area (46,44), impeller (49) is arranged on gas-entered passageway (11) and goes out gas area (46,44) between, and the rotation by impeller is transported to out gas area (46 with medium from gas-entered passageway (11), 44), (34) change with the sidewall shape around it to its gabarit shape of outlet diameter (48) impeller along its axis from inlet diameter, this range stabilization comprises a ventilation chamber (31) that extends to contoured wall (47) from gas-entered passageway (11), this ventilation chamber communicates with main air flow (33) in the gas-entered passageway (11) by a connection opening (33), and the connection opening of locating by a profile inwall (11) that is positioned between impeller leading edge (2) and the impeller trailing edge (46) (45) communicates with main air flow, it is characterized in that: in gas-entered passageway (11), be provided with an air inlet ring (10), its restriction main air flow and topped ventilation chamber (31), main air flow is greater than a distance (15) relatively.
2, according to the range stabilization of the described centrifugal compressor of claim 1, it is characterized in that the replaceable and adjustment of air inlet ring (10).
According to the range stabilization of claim 1 or 2 described centrifugal compressors, it is characterized in that 3, air inlet diameter (16) is 0.64 to 1.2 times of impeller trailing edge diameter (48), optimum range is between 0.7 to 0.9.
According to the range stabilization of the described centrifugal compressor of claim 1 to 3, it is characterized in that 4, the circular groove (38) of direct fluid impeller (49) is had the angle of attack (43) between 20 ° to 30 ° of the radial direction.
According to the range stabilization of the described centrifugal compressor of claim 1 to 4, it is characterized in that 5, the width (36) of circular groove (38) is 0.55 to 0.7 times of impeller trailing edge width (50).
6, according to the range stabilization of the described centrifugal compressor of at least one claim in the claim 1 to 5, it is characterized in that having another circular groove (138) at least, 1/4th of the suitable impeller trailing edge of its width width (50).
7, according to the range stabilization of the described centrifugal compressor of at least one claim in the claim 1 to 6, the determined axial position of distance (56) that it is characterized in that the circular groove (38) counted from the trailing edge of impeller (49) is 0.15 to 0.3 times of impeller trailing edge diameter (48).
According to the range stabilization of the described centrifugal compressor of claim 1 to 7, it is characterized in that 8, the position of inlet channel (22) is to locate in the distance (58) of distance impeller rear end, this distance is 0.36 to 0.6 times of impeller trailing edge diameter (48).
According to the range stabilization of the described centrifugal compressor of claim 1 to 8, it is characterized in that 9, the ratio of the width of the width of inlet channel (22) and circular groove (38) is 1 to 1.1.
According to the range stabilization of the described centrifugal compressor of claim 1 to 9, it is characterized in that 10, the ratio of the radially area of the cross-section area of ventilation chamber and circular groove (38) is between 3.5 to 4.5.
According to the range stabilization of the described centrifugal compressor of claim 1 to 10, it is characterized in that 11, the internal diameter (30) of ventilation chamber (31) is about 0.8 times of impeller trailing edge diameter (48).
According to the range stabilization of the described centrifugal compressor of claim 1 to 11, it is characterized in that 12, the width (36) of circular groove (38) is 0.03 to 0.05 times of impeller trailing edge diameter (48).
13, according to the range stabilization of the described centrifugal compressor of claim 1 to 12, it is characterized in that, the area of circular groove (38) and impeller trailing edge diameter square ratio be between 0.106 to 0.151 times of hub ratio, this hub ratio is impeller inlet (34) diameter and its trailing edge (48) diameter ratio.
According to the range stabilization of the described centrifugal compressor of claim 1 to 13, it is characterized in that 14, the volume of ventilation chamber (31) is between three cubed 0.06 to 0.23 times of the impeller trailing edge diameter (48).
According to the range stabilization of the described centrifugal compressor of claim 1 to 14, it is characterized in that 15, the end face of the gusset of support profiles ring (26) is a rounding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 91109578 CN1070721A (en) | 1991-09-19 | 1991-09-19 | Compressor range stabilization |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 91109578 CN1070721A (en) | 1991-09-19 | 1991-09-19 | Compressor range stabilization |
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| Publication Number | Publication Date |
|---|---|
| CN1070721A true CN1070721A (en) | 1993-04-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 91109578 Pending CN1070721A (en) | 1991-09-19 | 1991-09-19 | Compressor range stabilization |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101027491B (en) * | 2004-06-07 | 2010-12-08 | 霍尼韦尔国际公司 | Compressor apparatus with recirculation and method therefore |
| CN102221016A (en) * | 2010-04-19 | 2011-10-19 | 通用汽车环球科技运作有限责任公司 | Compressor gas flow deflector and compressor incorporating the same |
| CN101520054B (en) * | 2008-02-27 | 2011-12-21 | 三菱重工业株式会社 | Centrifugal compressor |
| CN102705266B (en) * | 2007-09-28 | 2015-03-25 | 三菱重工业株式会社 | Compressor device |
| CN106574631A (en) * | 2014-07-03 | 2017-04-19 | 三菱重工发动机和增压器株式会社 | Compressor cover, centrifugal compressor, and supercharger, and compressor cover manufacturing method |
| CN106968989A (en) * | 2013-02-22 | 2017-07-21 | 三菱重工业株式会社 | Centrifugal compressor |
| CN109707665A (en) * | 2017-10-26 | 2019-05-03 | 韩华压缩机株式会社 | With the double shrouded wheel for voluntarily recycling treated casing |
| CN110185632A (en) * | 2019-04-18 | 2019-08-30 | 西安热工研究院有限公司 | The overcritical working medium semi-open type centrifugal compressed device and method of changeable flow |
| CN110185631A (en) * | 2019-04-18 | 2019-08-30 | 西安热工研究院有限公司 | The symmetrical overcritical working medium closed centrifugal compressor set of partial admission and method |
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- 1991-09-19 CN CN 91109578 patent/CN1070721A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101027491B (en) * | 2004-06-07 | 2010-12-08 | 霍尼韦尔国际公司 | Compressor apparatus with recirculation and method therefore |
| CN102705266B (en) * | 2007-09-28 | 2015-03-25 | 三菱重工业株式会社 | Compressor device |
| CN101520054B (en) * | 2008-02-27 | 2011-12-21 | 三菱重工业株式会社 | Centrifugal compressor |
| CN102221016A (en) * | 2010-04-19 | 2011-10-19 | 通用汽车环球科技运作有限责任公司 | Compressor gas flow deflector and compressor incorporating the same |
| US8882444B2 (en) | 2010-04-19 | 2014-11-11 | GM Global Technology Operations LLC | Compressor gas flow deflector and compressor incorporating the same |
| CN102221016B (en) * | 2010-04-19 | 2015-01-28 | 通用汽车环球科技运作有限责任公司 | Compressor gas flow deflector and compressor incorporating the same |
| US10167877B2 (en) | 2013-02-22 | 2019-01-01 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressor |
| CN106968989A (en) * | 2013-02-22 | 2017-07-21 | 三菱重工业株式会社 | Centrifugal compressor |
| CN106574631A (en) * | 2014-07-03 | 2017-04-19 | 三菱重工发动机和增压器株式会社 | Compressor cover, centrifugal compressor, and supercharger, and compressor cover manufacturing method |
| US10436218B2 (en) | 2014-07-03 | 2019-10-08 | Mitsubishi Heavy Industries Engine & Turbocharger , Ltd. | Compressor cover, centrifugal compressor, and turbocharger, and compressor cover manufacturing method |
| CN106574631B (en) * | 2014-07-03 | 2019-10-18 | 三菱重工发动机和增压器株式会社 | The manufacturing method of compression case, centrifugal compressor and booster and compression case |
| CN109707665A (en) * | 2017-10-26 | 2019-05-03 | 韩华压缩机株式会社 | With the double shrouded wheel for voluntarily recycling treated casing |
| CN109707665B (en) * | 2017-10-26 | 2022-04-29 | 韩华压缩机株式会社 | Closed impeller with self-recirculating casing treatment |
| CN110185632A (en) * | 2019-04-18 | 2019-08-30 | 西安热工研究院有限公司 | The overcritical working medium semi-open type centrifugal compressed device and method of changeable flow |
| CN110185631A (en) * | 2019-04-18 | 2019-08-30 | 西安热工研究院有限公司 | The symmetrical overcritical working medium closed centrifugal compressor set of partial admission and method |
| CN110185632B (en) * | 2019-04-18 | 2024-05-17 | 西安热工研究院有限公司 | Variable-flow supercritical working medium semi-open centrifugal compression device and method |
| CN110185631B (en) * | 2019-04-18 | 2024-05-28 | 西安热工研究院有限公司 | Symmetrical local air inlet supercritical working medium closed centrifugal compressor unit and method |
| CN113417890A (en) * | 2021-07-26 | 2021-09-21 | 中国船舶重工集团公司第七0三研究所 | Grooved ring type processing casing structure of gas compressor of ship gas turbine |
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