CN110360133B - Gas turbine compressor through-flow structure - Google Patents
Gas turbine compressor through-flow structure Download PDFInfo
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- CN110360133B CN110360133B CN201910552631.7A CN201910552631A CN110360133B CN 110360133 B CN110360133 B CN 110360133B CN 201910552631 A CN201910552631 A CN 201910552631A CN 110360133 B CN110360133 B CN 110360133B
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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
- F04D17/12—Multi-stage 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
- F04D29/06—Lubrication
- F04D29/063—Lubrication specially 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
- 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
- F04D29/286—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
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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
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/662—Balancing of rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of gas compressors of small and medium-sized gas turbines, and particularly relates to a gas compressor through-flow structure of a gas turbine, which comprises primary branch channels, wherein the number of the primary branch channels is eight equal parts, annular channels are arranged at the junction of the primary branch channels, secondary branch bent channels are uniformly arranged at gaps among the primary branch channels, and the annular channels are in confluent butt joint with the air inlet ends of the secondary branch bent channels. The invention carries out through-flow layout through the reverse layout of the first-stage branch channel and the second-stage branch curved channel and through the curved channel structure of the bypass, so that reverse air intake can be carried out between two stages, the axial force of the centrifugal impeller is counteracted in a back-to-back mode, and the 8 branches are mutually connected in series, converged and communicated to form a complete annular channel, so that the air intake of the second-stage branch curved channel is uniform, and the total pressure of the air compressor is obviously improved.
Description
Technical Field
The invention belongs to the technical field of turbomachinery, and particularly relates to a compressor through-flow structure of a gas turbine.
Background
The three major core components of the gas turbine are a gas compressor, a combustion chamber and a turbine respectively, and for small-flow, medium-sized and micro gas turbines, the centrifugal gas compressor has obvious pneumatic and cost advantages. At present, the pressure ratio of a single-stage centrifugal compressor in China reaches more than 5, and the pressure ratio of a centrifugal compressor with a mature technology is between 1.5 and 4, which shows that the two-stage centrifugal compressor can completely reach the optimal circulating supercharging ratio of 8 to 11 medium and small gas turbines, and an axial flow compressor with the same pressure ratio usually needs more than 13 stages of supercharging, so that the production cost is greatly increased, and the size optimization of the whole machine is not facilitated. The small-sized aviation represented by the WZ8 turboshaft engine in China adopts the two-stage centrifugal compressors connected in series, and the layout has remarkable size advantage, greatly shortens the axial size and is suitable for small-sized aircrafts such as helicopters. However, the high pressure ratio brought by the double-centrifugal equidirectional layout also causes a large axial force, and the requirement on a thrust bearing or a balance inventory is high. In the GTCP85 auxiliary power device, a double suction centrifugal compressor + single-stage centrifugal compressor layout is used, wherein the double suction centrifugal compressor can well offset its own axial force, but the axial force of the high-pressure compressor still needs to be balanced additionally.
However, the centrifugal impeller in the reverse layout needs to require a special air inlet volute for the second-stage air compressor, which brings inconvenience to the structure, increases the size and weight of the whole air compressor, is not favorable for the uniformity of air flow at the outlet of the whole air compressor, causes uneven pressure ratio, great total pressure loss of the air compressor, extremely poor air inlet effect of the impeller of the second-stage air compressor, causes the performance of the whole air compressor to be low, reduces the efficiency, cannot improve the efficiency of the air compressor, and will affect the overall efficiency of the air compressor.
Disclosure of Invention
The invention provides a through-flow structure of a gas compressor of a gas turbine, aiming at improving the total pressure of a two-stage back-to-back type gas compressor, enhancing the uniformity of gas flow and reducing the structure to lighten the weight.
In order to realize the aim of the invention, the invention provides a through-flow structure of a gas compressor of a gas turbine, which comprises a primary branch channel, wherein the number of the primary branch channel is eight equal parts, an annular channel is arranged at the junction of the primary branch channel, secondary branch bent channels are uniformly arranged at gaps among the primary branch channels, and the annular channel is in confluent butt joint with the air inlet ends of the secondary branch bent channels; the first-stage branch channel comprises a first-stage impeller outlet diameter D1Diameter D of inlet of first-stage diffuser2Diameter D of outlet of first-stage diffuser3First stage diffuser exit angle α1First order tangent angle α21First order branch boundary diameter D4First-order branch boundary channel starting point C1First-level branch boundary channel edge point C2Primary channel width b1First order major diameter D5First stage fan-shaped converging channel α23First stage fan-shaped convergent angle α22(ii) a The second branch curve comprises a second stageMinimum inlet diameter D6Second highest inlet diameter D7Second stage diffuser exit angle α4Second-order tangent angle α31Second-level branch boundary channel starting point C3Second-level branch boundary channel edge point C4Second level channel width b4。
Furthermore, the primary branch channel and the secondary branch bent channel are uniformly distributed in a crossed manner and communicated at the air inlet end.
Further, the primary circle tangent angle α21Is equal to the first stage diffuser exit angle α1The angle of (c).
Further, the secondary circle tangent angle α31Is equal to the secondary diffuser exit angle α4The angle of (c).
Further, the primary branch boundary diameter D4Less than or equal to the outlet diameter D of the first-stage diffuser31.02 times of the total weight of the powder.
Further, the primary channel width b1Equal to the first-order branch boundary diameter D4Multiplied by sin (first order circle tangent angle α21+22.5°）。
Further, the primary fan-shaped converging channel α23The included angle of the fan surface is 10 degrees.
Further, the first-stage fan-shaped contraction included angle α22Is a one-stage fan-shaped contraction passage α23The center line of (A) and the center line of the corresponding circle form an included angle, and the first-stage fan-shaped contraction included angle α22∈（0，6°）。
Furthermore, the areas of the throats of the curves of the first-stage branch channel and the second-stage branch channel are equal.
Further, the second highest intake diameter D7Less than or equal to the first-order major diameter D50.8 times of the total weight of the powder.
The invention has the beneficial effects that: according to the invention, the first-stage branch channel and the second-stage branch channel are reversely distributed on the curved channel of the bypass of the two-stage centrifugal compressor, and through-flow distribution is carried out on the curved channel structure of the bypass, so that reverse air intake can be carried out between two stages, the axial force of the centrifugal impeller is counteracted in a back-to-back manner, the balance is good, the requirement on the thrust bearing or the balance disc is reduced, the long-term running stability is increased, the service life of the thrust bearing or the balance disc is greatly prolonged, the structure ensures that the axial thrust can be counteracted by the reverse distribution of the two-stage centrifugal impeller, the requirement on the thrust bearing can be greatly reduced, the cost is reduced, and better mechanical property; the invention has the advantages that the structure is simple, the flow structure volume of the compressor is reduced, the air inlet of the secondary branch curve channel does not depend on a volute, the weight of the structure can be reduced, the balanced air inlet can obtain the maximum pressure recovery coefficient, the pressure ratio is uniform, the air inlet effect is excellent, the total pressure loss is small, and the performance of the whole machine is improved.
Drawings
FIG. 1 is a schematic front view of the present invention;
FIG. 2 is a schematic right-side view of the present invention;
FIG. 3 is a partial cross-sectional view of the front of the primary branching channel of the present invention;
FIG. 4 is a partial cross-sectional view of the rear portion of the primary branch passage of the present invention;
FIG. 5 is a schematic view of a through-flow meridian plane of the present invention;
fig. 6 is a schematic left side view of the present invention.
Detailed Description
The invention will be further explained below with reference to the accompanying drawings:
in the figure: 1 first-stage branch channel, 11 annular channel and 2 second-stage branch curved channel.
Referring to fig. 1, fig. 2, fig. 3, fig. 4, and fig. 5, the gas compressor flow structure of a gas turbine according to the present invention includes a first-stage branch passage 1, eight first-stage branch passages 1 are uniformly distributed, a ring passage 11 is disposed at a junction of the first-stage branch passages 1, and gaps between the first-stage branch passages 1 are all filled with a gasThe second-stage branch bend 2 is uniformly arranged, and the annular channel 11 is converged and butted with the air inlet end of the second-stage branch bend 2; the first-stage branch channel 1 comprises a first-stage impeller outlet diameter D1Diameter D of inlet of first-stage diffuser2Diameter D of outlet of first-stage diffuser3First stage diffuser exit angle α1First order tangent angle α21First order branch boundary diameter D4First-order branch boundary channel starting point C1First-level branch boundary channel edge point C2Primary channel width b1First order major diameter D5First stage fan-shaped converging channel α23First stage fan-shaped convergent angle α22(ii) a The second-stage branch bend 2 comprises a second-stage lowest air inlet diameter D6Second highest inlet diameter D7Second stage diffuser exit angle α4Second-order tangent angle α31Second-level branch boundary channel starting point C3Second-level branch boundary channel edge point C4Second level channel width b4The first-stage branch passage 1 and the second-stage branch curve 2 are uniformly distributed in a crossed manner and communicated at the air inlet end, and the first-stage circular tangent angle α21Is equal to the first stage diffuser exit angle α1Angle of (d), second order circle tangent angle α31Is equal to the secondary diffuser exit angle α4Angle of (D), first order branch boundary diameter D4Less than or equal to the outlet diameter D of the first-stage diffuser31.02 times of the primary channel width b1Equal to the first-order branch boundary diameter D4Multiplied by sin (first order circle tangent angle α21+22.5 deg., one-stage fan-shaped converging channel α23Has a sector included angle of 10 degrees and a first-stage sector contraction included angle α22Is a one-stage fan-shaped contraction passage α23The center line of (A) and the center line of the corresponding circle form an included angle, and the first-stage fan-shaped contraction included angle α22∈ (0, 6 degree), the throat areas of the first branch channel and the second branch channel are equal, the highest inlet diameter D of the second branch channel7Less than or equal to the first-order major diameter D50.8 times of the total weight of the powder.
The first embodiment is as follows:
the centrifugal compressor with the reverse layout is connected with a secondary branch bend 2 in series through a plurality of primary branch channels 1, 8 primary branch channels 1 are connected to the outlet of a diffuser of the primary compressor, the channels are designed according to the principle of equal annular quantity, a gap is formed behind the diffuser for the secondary branch bend 2 to pass through, and the primary branch channels 1 are converged into a complete annular channel before the inlet of the secondary branch bend 2.
The outlet curve of the second-stage compressor is also led out by 8 second-stage branch curves 2, the design mode of the channel is the same as that of the first-stage compressor, the channel passes through the gaps (staggered) between the branches of the first-stage curve, and then the channel is converged in the gas collecting chamber and enters the next unit. The two-stage centrifugal impeller reversely intakes air and locally offsets the axial force back to back. The invention allows the curve part of the first-stage branch channel 1 to be adjusted, and changes the curve into a heat exchanger channel, thereby introducing an interstage cooling system between two stages of gas compressors and improving the overall efficiency of the gas compressors.
Example two:
the two-stage centrifugal compressor adopts a reverse back-to-back layout, and the outlet diameter D of the one-stage impeller is shown in reference to fig. 2, 3, 4 and 51The width of the cross section of the channel and the inlet diameter D of the first-stage diffuser2The width of the cross section of the channel and the outlet diameter D of the first-stage diffuser3Where the cross-sectional width of the passage is equal and the diffuser inside the annular passage 11 forms a first stage diffuser exit angle α1The diffuser forms a second-stage diffuser exit angle α at the second stage4；
The first stage compressor diffuser blade exit angle being the first stage diffuser exit angle α1To determine the included angle between the boundary of the first-stage curve and the tangent of the circle as the first-stage circle tangent angle α21Demand α21=α1. First order branch boundary diameter D of branch channel inlet diameter4And the outlet diameter D of the first-stage diffuser3Comparison of (D)4≤1.02D3. Get D4Any point is used as the starting point of the boundary of the first branch channel, and the point is the starting point C of the boundary of the first branch channel1The circumferential array 8 is divided equally, and then the adjacent edge is taken as the adjacent edge point C of the first-level branch boundary channel2Starting point of (2), requirement C2And C1Parallel, in which case the primary channel width b can be determined1=D4×sin（α21+22.5°）。
The first-stage compressor bend radially extends to a first-stage large circular diameter D5Then enters a curve part, the curve part begins to deflect, the rear half part of the curve is connected to the front junction of the inlet of the second-stage compressor impeller and is a fan-shaped contraction channel, and the corner first-stage fan-shaped contraction channel α of the fan-shaped contraction channel23=10 degrees, and the included angle formed by the central line of the channel and the central line of the corresponding circle is a first-stage fan-shaped contraction included angle α22First order fan pinch angle α22∈ (0, 6), α may be determined based on the centrifugal compressor speed and the peripheral speed of the air flow at the diametric section22Taking value, but not more than 6 degrees, and rounding R at the junction of the branch channels2，R2∈（1,5）。
The diameter D of the outlet of the first-stage impeller from the outlet of the impeller to the inlet of the 180-degree bend1The width of the cross section of the channel and the inlet diameter D of the first-stage diffuser2The width of the cross section of the channel and the outlet diameter D of the first-stage diffuser3The width of the cross section of the channel and the diameter D of the boundary of the primary branch4The width of the cross section of the channel can be set according to the design condition of the compressor, and the boundary diameter D of the first-stage branch before and after the 180-degree bend4The width of the cross section of the channel and the primary large diameter D5The cross-section of the channel is equal, wherein the diameter D of the large circle is one step5The width of the cross section of the channel is the width of the cross section of the fan-shaped contraction channel after the bend. The diameter D of the first-stage large circle is from the outlet of the 180-degree bend to the front of the merging inlet of the fan-shaped channel5The width of the cross section of the passage and the second lowest air inlet diameter D6Should satisfy (D) between the widths of the cross sections of the channels5Its cross-sectional channel width × D5= D6Its cross-sectional channel width × D6) Thus, the throat area of through flow is ensured, and the air inlet quantity is balanced.
The design of the curve part of the secondary branch curve 2 of the secondary compressor is the same as that of the first stage, and the secondary circle tangent angle α can be respectively determined31Second-level branch boundary channel starting point C3Second order branch boundary channelRoad edge point C4Second level channel width b4And the secondary compressor curved channel is merged with a gas collecting chamber or a volute after being bent at 180 degrees, and then the gas compressor is discharged. The second-level highest air inlet diameter D of the highest point of the 180-degree bend can be adjusted7≤0.8D5The design is made and here the width should be smaller than the gap of the first order curve branch. The eight-equal-part air inlet through-flow structure avoids the traditional dependence on air inlet of an air inlet volute, simplifies the whole structure, effectively ensures the uniformity of air inlet, ensures that the air inlet at two ends is uniform and stable to completely offset the axial force in the opposite direction through the back-to-back design of the two-stage centrifugal compressors with the same amount, can prolong the service life of an axial lubricating device, ensures the stable and efficient operation of a rotating shaft, simultaneously avoids the occurrence of surge phenomenon, promotes the total pressure ratio of the compressors, reduces the appearance size through the reasonable structural design, correspondingly lightens the weight, ensures that the invention can achieve the great and remarkable effect on small and medium-sized gas turbines, overcomes the traditional technical barrier and brings extremely high and substantial effects.
According to the invention, the first-stage branch channel 1 and the second-stage branch channel 2 are reversely distributed on the curved channel of the bypass of the two-stage centrifugal compressor, and through-flow distribution is carried out on the curved channel structure of the bypass, so that reverse air inlet can be carried out between two stages, the axial force of the centrifugal impeller is counteracted in a back-to-back mode, the balance is good, the requirement on the thrust bearing or the balance disc is reduced, the long-term running stability is increased, the service life of the thrust bearing or the balance disc is greatly prolonged, the structure ensures that the axial thrust can be counteracted by the reverse distribution of the two-stage centrifugal impeller, the requirement on the thrust bearing can be greatly reduced, the cost is reduced, and better mechanical property; the reverse layout primary branch channel 1 and the secondary branch bend 2 are mutually connected in series through respective 8 branches, and are designed according to the principle of equal circulation, the primary branch channel 1 is converged and communicated in front of an inlet of the secondary branch bend 2 to form a complete annular channel and is butted with an air inlet end of the secondary branch bend 2, so that the air inlet of the secondary branch bend 2 is uniform, and the air inlet amount is balanced.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein, and any reference signs in the claims are not intended to be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. A through-flow structure of a gas compressor of a gas turbine is characterized in that: the device comprises primary branch channels, wherein the number of the primary branch channels is eight equal parts, annular channels are arranged at the junction of the primary branch channels, secondary branch bent channels are uniformly arranged at gaps among the primary branch channels, and the annular channels are in confluent butt joint with the air inlet ends of the secondary branch bent channels; the first-stage branch channel comprises a first-stage impeller outlet diameter D1Diameter D of inlet of first-stage diffuser2Diameter D of outlet of first-stage diffuser3First stage diffuser exit angle α1First order tangent angle α21First order branch boundary diameter D4First-order branch boundary channel starting point C1First-level branch boundary channel edge point C2Primary channel width b1First order major diameter D5First-stage fan-shaped contraction passageα23First stage fan-shaped convergent angle α22(ii) a The second-stage branch curve comprises a second-stage lowest air inlet diameter D6Second highest inlet diameter D7Second stage diffuser exit angle α4Second-order tangent angle α31Second-level branch boundary channel starting point C3Second-level branch boundary channel edge point C4Second level channel width b4。
2. The compressor through-flow structure of a gas turbine according to claim 1, characterized in that: the first-stage branch channel and the second-stage branch bent channel are uniformly distributed in a crossed manner and communicated at the air inlet end.
3. The compressor flow structure of the gas turbine as claimed in claim 1, wherein the first-stage circular tangent angle α21Is equal to the first stage diffuser exit angle α1The angle of (c).
4. The compressor flow structure of a gas turbine as claimed in claim 1, wherein the secondary circle tangent angle α31Is equal to the secondary diffuser exit angle α4The angle of (c).
5. The compressor through-flow structure of a gas turbine according to claim 1, characterized in that: the primary branch boundary diameter D4Less than or equal to the outlet diameter D of the first-stage diffuser31.02 times of the total weight of the powder.
6. The compressor through-flow structure of a gas turbine according to claim 1, characterized in that: width b of the primary channel1Equal to the first-order branch boundary diameter D4Multiplied by sin (first order circle tangent angle α21+22.5°）。
7. The compressor through-flow structure of the gas turbine as claimed in claim 1, wherein the first stage fan-shaped contraction passage α23The included angle of the fan surface is 10 degrees.
8. The compressor flow structure of the gas turbine as claimed in claim 1, wherein the primary fan-shaped contraction included angle α22Is a one-stage fan-shaped contraction passage α23The center line of (A) and the center line of the corresponding circle form an included angle, and the first-stage fan-shaped contraction included angle α22∈（0，6°）。
9. The compressor through-flow structure of a gas turbine according to claim 1, characterized in that: the first-stage branch channel and the second-stage branch channel are equal in throat area of the curve.
10. The compressor through-flow structure of a gas turbine according to claim 1, characterized in that: the second highest air inlet diameter D7Less than or equal to the first-order major diameter D50.8 times of the total weight of the powder.
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| 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 |
-
2019
- 2019-06-25 CN CN201910552631.7A patent/CN110360133B/en active Active
Patent Citations (6)
| 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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