CN116446964A - Turbine exhaust volute with inlet pre-rotation guide vane and turbine assembly - Google Patents

Turbine exhaust volute with inlet pre-rotation guide vane and turbine assembly Download PDF

Info

Publication number
CN116446964A
CN116446964A CN202310545875.9A CN202310545875A CN116446964A CN 116446964 A CN116446964 A CN 116446964A CN 202310545875 A CN202310545875 A CN 202310545875A CN 116446964 A CN116446964 A CN 116446964A
Authority
CN
China
Prior art keywords
volute
inlet
turbine
outlet
flow
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
Application number
CN202310545875.9A
Other languages
Chinese (zh)
Inventor
李茂义
杨旭
何家祥
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Qinghang Aerospace Beijing Technology Co ltd
Original Assignee
Qinghang Aerospace Beijing Technology Co ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Qinghang Aerospace Beijing Technology Co ltd filed Critical Qinghang Aerospace Beijing Technology Co ltd
Priority to CN202310545875.9A priority Critical patent/CN116446964A/en
Publication of CN116446964A publication Critical patent/CN116446964A/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

The invention provides a turbine exhaust volute with an inlet pre-rotation guide vane and a turbine assembly, wherein the turbine exhaust volute with the inlet pre-rotation guide vane comprises the following components: the diffusion section is provided with a diffusion inlet and a diffusion outlet, the diffusion inlet is connected with the turbine outlet, and the flow area of the diffusion inlet towards the diffusion outlet is gradually increased; the guide vane is arranged at the diffusion inlet; the flow guiding volute is provided with a flow guiding volute inlet and a flow guiding volute outlet, the flow guiding volute inlet is connected with the diffusion outlet, and the flow guiding volute outlet is communicated with the external space. The beneficial effects of the invention are as follows: the turbine outlet air flows through the guide vane to enable the air flow to generate larger circumferential speed division, the air flow enters the diffusion section with a larger circumferential included angle with the axial direction and is decelerated and pressurized, and then the air flow is smoothly, uniformly and without separation discharged into the atmosphere through the guide volute, so that the problems of flow blockage and large loss and the problem of excitation frequency to the turbine vane caused by uneven flow field at the inlet of the exhaust volute are solved.

Description

Turbine exhaust volute with inlet pre-rotation guide vane and turbine assembly
Technical Field
The invention relates to the technical field of turbines, in particular to a turbine exhaust volute with an inlet pre-rotation guide vane and a turbine assembly.
Background
When the turbine adopts the rear axle to output power, the working fuel gas needs to be discharged from the axial rotation radial direction or from the axial rotation radial direction to the axial direction again through the exhaust volute. The outlet direction of the turbine is generally close to the axial direction, the size of the exhaust volute is compact, the turning angle of the airflow in the exhaust volute is large, the turning radius is small, the flow blockage is serious, the loss is excessive, and the output power of the engine is greatly reduced. Especially when the exhaust gas direction after the turbine deviates more from the axial direction, the flow loss of the conventional exhaust volute is further increased. In addition, the traditional exhaust volute is difficult to lead airflow after the turbine to be uniform in the circumferential direction, so that airflow parameters at the inlet of the volute are not uniform in the circumferential direction, extra excitation frequency is generated for turbine blades, and the blades are easy to generate resonance danger.
The pressure loss in the exhaust volute is reduced, so that the pressure behind the turbine can be reduced, the enthalpy drop of the turbine is increased, and the performance of the engine is improved. Besides the small pressure loss, the exhaust device also improves the speed field uniformity of the inlet of the exhaust volute as much as possible, and avoids the danger of resonance of turbine blades.
The existing common exhaust volute is divided into three types, namely a elbow pipe type, a full volute type and a box type, wherein in the elbow pipe type scheme, air flow is a low-speed vortex area below a central shaft, and blockage and vortex loss can be caused; and a high velocity zone above the central axis and generally at a much greater velocity than below the central axis, which results in non-uniform circumferential flow at the inlet of the volute. The flow characteristics of the full volute approach are similar to those of the elbow volute, except that the axial length is short and the radial length is long. The box volute comprises a ring diffuser and a gas collecting chamber. The volute has the advantages that the structure is compact, and the airflow at the inlet of the volute is relatively uniform; the disadvantage is that the swirl flow at the outlet of the annular diffuser below the central axis is severe, which can cause flow blockage and large flow losses.
Disclosure of Invention
In view of the above, the present invention provides a turbine exhaust volute with inlet pre-rotation vanes and a turbine assembly, so as to achieve the purposes of reducing flow loss and blockage and improving the circumferential uniformity of the inlet flow field of the turbine exhaust volute.
The embodiment of the specification provides the following technical scheme: a turbine exhaust volute with inlet pre-rotation vanes, comprising: the diffusion section is provided with a diffusion inlet and a diffusion outlet, the diffusion inlet is connected with the turbine outlet, and the flow area of the diffusion inlet towards the diffusion outlet is gradually increased; the guide vane is arranged at the diffusion inlet; the flow guiding volute is provided with a flow guiding volute inlet and a flow guiding volute outlet, the flow guiding volute inlet is connected with the diffusion outlet, and the flow guiding volute outlet is communicated with the external space.
Further, the cross section area of the diversion volute is gradually increased along the direction from the diversion volute inlet to the diversion volute outlet, and at least one diversion volute outlet is arranged.
Further, the ratio of the sum of the sectional areas of the flow guiding volute outlets to the sectional area of the turbine outlet is 1.1 to 3.
Further, the guide vane is a single vane or a serial vane.
Further, the outlet airflow direction of the guide vane has an included angle with the axial direction of the guide vane.
Further, the turbine exhaust volute with the inlet pre-rotation guide vane further comprises exhaust pipes, each flow guiding volute outlet is correspondingly connected with one exhaust pipe, the exhaust pipe inlet is connected with the flow guiding volute outlet, and the exhaust pipe outlet is connected with the external space.
Further, the outlet cross-sectional area of the exhaust pipe is greater than or equal to the inlet cross-sectional area of the exhaust pipe.
Further, when the number of exhaust pipes is even, the plurality of exhaust pipe outlets are axisymmetrically distributed relative to the axis of the turbine exhaust volute with the inlet pre-rotation guide vane.
The invention also provides a turbine assembly, which comprises the turbine exhaust volute with the inlet pre-rotation guide vane.
Further, the turbine assembly includes a turbine, an outlet of which is connected to a diffuser inlet of the turbine exhaust volute with inlet pre-rotation vanes.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least: the turbine outlet air flows through the guide vane to enable the air flow to generate larger circumferential speed division, the air flow enters the diffusion section with a larger circumferential included angle with the axial direction and is decelerated and pressurized, and then the air flow is smoothly, uniformly and nondeparatally discharged into the atmosphere through the guide volute, so that the problems of flow blockage and large loss and the problem of turbine blade exciting force caused by uneven circumferential air flow at the inlet of the exhaust volute are solved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic three-dimensional structure of an embodiment of the present invention;
FIG. 2 is a schematic diagram of the front view of FIG. 1;
FIG. 3 is a schematic view of a single-bladed version of a guide vane;
FIG. 4 is a schematic view of a guide vane structure in the form of a tandem vane;
FIG. 5 is a schematic view of a diffuser according to an embodiment of the present invention;
FIG. 6 is a schematic view of a flow directing scroll in an embodiment of the invention;
fig. 7 is a schematic view of the structure of an exhaust pipe in the embodiment of the present invention.
Reference numerals in the drawings: 10. a diffuser section; 11. a guide vane mounting portion; 12. a diversion volute connection part; 20. a guide vane; 30. a flow guiding volute; 31. a diversion volute inlet; 32. a diversion volute outlet; 40. an exhaust pipe; 41. an exhaust pipe inlet; 42. and an exhaust pipe outlet.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
As shown in fig. 1 to 7, an embodiment of the present invention provides a turbine exhaust volute with inlet pre-rotation vanes, comprising a diffuser 10, a guide vane 20, a guide volute 30, and an exhaust pipe 40. The diffusion section 10 is provided with a diffusion inlet and a diffusion outlet, the diffusion inlet is connected with the turbine outlet, and the flow area of the diffusion inlet towards the diffusion outlet is gradually increased; the guide vane 20 is arranged at the diffuser inlet to turn the axial airflow at the turbine outlet, and a certain circumferential speed division is generated at the guide vane outlet, so that the airflow in the guide volute is smooth and uniform; the flow guiding volute 30 is provided with a flow guiding volute inlet and a flow guiding volute outlet, the flow guiding volute inlet is connected with the diffusion outlet, the flow guiding volute outlet is communicated with the exhaust pipe 40, and the exhaust pipe 40 is communicated with the external space.
The turbine outlet airflow passes through the guide vane 20 to generate larger circumferential velocity, the airflow enters the diffuser section 10 at a larger circumferential included angle with the axial direction and is decelerated and pressurized, then the airflow is smoothly, uniformly and without separation led into the exhaust pipe 40 through the guide volute 30, and finally the airflow is discharged into the atmosphere through the exhaust pipe 40, so that the problems of flow blockage and large loss of the exhaust volute are solved, the circumferential uniformity of the inlet flow field of the turbine exhaust volute is realized, the excitation frequency of uneven flow to the turbine blade is eliminated, and the resonance risk of the turbine blade is eliminated.
In the embodiment of the invention, the cross-sectional area of the flow guiding volute 30 gradually increases along the direction from the inlet of the flow guiding volute to the outlet of the flow guiding volute, and the flow guiding volute has at least one outlet.
The flow guiding scroll 30 is for guiding the air flow of the diffuser 10 to the exhaust pipe 40 smoothly, uniformly, and without separation. The cross-sectional area of the flow guiding volute 30 increases gradually along the air flow direction, and the flow guiding volute 30 may have one outlet, two outlets or a plurality of outlets according to the actual use requirements. The flow directing scroll 30 in the present embodiment has two outlets.
The exhaust pipe 40 is for exhausting the exhaust gas to the atmosphere without circumferential velocity division, thereby eliminating axial moment generated by the exhaust gas.
Preferably, the ratio of the sum of the sectional areas of the outlets of the diversion spiral case to the sectional area of the outlet of the turbine is 1.1 to 3, so that the air flow is smoothly led out and the speed and the pressure are reduced and increased.
As shown in fig. 3 and 4, the guide vane 20 is configured to generate a certain circumferential velocity of the axial airflow entering the guide volute 30, so that the guide volute 30 can smoothly guide the airflow. The guide vane 20 may be a single vane or a tandem vane. The condition of small airflow rotation angle is achieved by a single blade; for large airflow angle comparisons, tandem vanes are used. The serial blades can effectively inhibit flow separation of the suction surfaces of the blades, and reduce flow loss. Two-dimensional primitive blade profiles for single blade and tandem blade are shown in figures 3 and 4, respectively. The three-dimensional blade is formed by stacking two-dimensional primitive blade profiles with different blade heights from blade root to blade tip according to a certain rule. The three-dimensional blade in the embodiment is formed by stacking two-dimensional primitive blade profiles of three sections of blade root, blade middle and blade tip along the tail edge line.
The outlet airflow direction of the guide vane 20 has a circumferential angle with the axial direction of the guide vane 20.
The outlet of the guide vane 20 is connected with a diffuser section 10, so as to reduce the speed of the air flow coming out of the guide vane 20, and reduce the friction loss of the air flow in the guide volute 30. The diffuser 10 is shown in fig. 5. The diffuser 10 is an axisymmetric annular passage, and the flow area gradually increases along the airflow direction, so that the airflow gradually decelerates and diffuses. The front part of the diffuser section 10 is provided with guide vanes 20, and the outlet is connected with a guide volute 30.
Fig. 5 shows a diffuser 10 provided with a guide vane mounting portion 11 at one end of the diffuser 10. At the other end of the diffuser section 10 is a flow directing volute connection 12.
Fig. 6 shows that the flow guiding volute 30 is provided with a flow guiding volute inlet 31 and a flow guiding volute outlet 32, the flow guiding volute inlet 31 is connected with the diffuser outlet, and the flow guiding volute outlet 32 is connected with the exhaust pipe 40. The cross-sectional area of the flow-directing scroll 30 increases gradually in the flow direction and the ratio of the sum of the cross-sectional areas of the flow-directing scroll outlets 32 to the turbine outlet cross-sectional area is 1.1 to 3.
As shown in fig. 1 and 7, each of the flow-guiding scroll outlets 32 is connected to one exhaust pipe 40, and the exhaust pipe inlet 41 is connected to the flow-guiding scroll outlet 32, and the exhaust pipe outlet 42 is connected to the external space.
The exhaust duct 40 functions to direct the flow of air at the flow directing volute outlet 32 in the direction of desired discharge. The absence of a circumferential velocity division in the exhaust pipe outlet 42 flow eliminates axial torque caused by exhaust. The circumferential velocity of the exhaust pipe outlet 42 airflow generates a certain axial moment. The exhaust direction of the exhaust pipe outlet 42 may be arranged as desired.
Preferably, when the number of exhaust pipes 40 is even, the plurality of exhaust pipe outlets 42 are distributed axisymmetrically with respect to the axis of the turbine exhaust volute with inlet pre-rotation vanes. The axisymmetric arrangement of the outlet direction can offset radial force and moment.
The cross-sectional area of the exhaust pipe outlet 42 is greater than or equal to the cross-sectional area of the exhaust pipe inlet 41. The exhaust pipe 40 is designed into a diffusion channel structure, so that the speed and the pressure can be effectively reduced, and the shaft power of the turbine can be improved.
The invention also provides a turbine assembly, which comprises the turbine exhaust volute with the inlet pre-rotation guide vane.
Further, the turbine assembly includes a turbine, an outlet of which is connected to a diffuser inlet of the turbine exhaust volute with inlet pre-rotation vanes. The absolute airflow at the turbine outlet can have a larger circumferential airflow angle with the axial direction, so that the load of the guide vane of the exhaust volute is reduced, the separation flow is lightened, and meanwhile, the reverse force of the turbine is improved, so that the pneumatic performance of the exhaust volute is improved, and the pneumatic performance of the turbine is improved.
The beneficial effects of the invention are as follows:
the flow guiding volute 30 has smooth airflow, no obvious vortex flow, small flow blockage, large flow and high turbine power.
The flow loss is small, and the pneumatic efficiency is high. Because the turbine exhaust volute with the inlet pre-rotation guide vane has almost no obvious vortex flow and separation flow, the flow loss is smaller than that of the existing volute, and the aerodynamic efficiency is high. In addition, the flow loss of the exhaust volute is small, so that the power reserve of the turbine is large, and the working range of the turbine is wide.
The turbine exhaust volute with the inlet pre-rotation guide vane has even inlet airflow, no extra exciting force to the turbine blade, and reduces the resonance risk of the turbine blade. The turbine exhaust volute with the inlet pre-rotation guide vane is characterized in that the flow guiding volute 30 continuously and uniformly guides the air flow into the exhaust pipe, the air flow uniformly flows in the circumferential direction, and a low-speed area and a vortex area are not existed.
The absolute airflow at the turbine outlet can be accepted to have larger circumferential speed, the difficulty of turbine design is reduced, and the pneumatic efficiency of the turbine is facilitated. The turbine exhaust volute with the inlet pre-rotation guide vane is used, so that the turbine design is not limited by the requirement of outlet axial air outlet, and the absolute speed of the outlet can have larger circumferential speed division. On the one hand, the bending angle of the guide vane 20 can be reduced, the load and flow separation of the guide vane 20 can be reduced, and on the other hand, the turbine reaction force can be increased, and especially the flow of the root of the movable vane can be improved, so that the aerodynamic efficiency of the turbine is improved.
The foregoing description of the embodiments of the invention is not intended to limit the scope of the invention, so that the substitution of equivalent elements or equivalent variations and modifications within the scope of the invention shall fall within the scope of the patent. In addition, the technical characteristics and technical scheme, technical characteristics and technical scheme can be freely combined for use.

Claims (10)

1. A turbine exhaust volute with inlet pre-rotation vanes, comprising:
the diffusion section (10) is provided with a diffusion inlet and a diffusion outlet, the diffusion inlet is connected with the turbine outlet, and the flow area of the diffusion inlet towards the diffusion outlet is gradually increased;
a guide vane (20) disposed at the diffuser inlet;
the flow guiding volute (30) is provided with a flow guiding volute inlet and a flow guiding volute outlet, the flow guiding volute inlet is connected with the diffusion outlet, and the flow guiding volute outlet is communicated with an external space.
2. The turbine exhaust volute with inlet pre-rotation vanes of claim 1, wherein the flow directing volute (30) has a gradually increasing cross-sectional area along the flow directing volute inlet to the flow directing volute outlet, and wherein the flow directing volute outlet is at least one.
3. The turbine exhaust volute with inlet pre-rotation vanes of claim 2 wherein the ratio of the sum of the cross-sectional areas of the flow directing volute outlets to the cross-sectional area of the turbine outlets is 1.1 to 3.
4. Turbine exhaust volute with inlet pre-rotation vanes according to claim 1, characterized in that the guide vanes (20) are single or tandem vanes.
5. The turbine exhaust volute with inlet pre-rotation vanes of claim 4, wherein the outlet airflow direction of the guide vanes (20) is angled with respect to the axial direction of the guide vanes (20).
6. The turbine exhaust volute with inlet pre-rotation vanes of claim 2, further comprising exhaust pipes (40), each of the flow guiding volute outlets being connected to one exhaust pipe (40) in correspondence, and an exhaust pipe inlet (41) being connected to the flow guiding volute outlet, and an exhaust pipe outlet (42) being connected to the external space.
7. The turbine exhaust volute with inlet pre-rotation vanes of claim 6, wherein the exhaust pipe outlet (42) cross-sectional area is greater than or equal to the exhaust pipe inlet (41) cross-sectional area.
8. The turbine exhaust volute with inlet pre-rotation vanes of claim 6, wherein the plurality of exhaust pipe outlets (42) are axisymmetrically distributed with respect to the axis of the turbine exhaust volute with inlet pre-rotation vanes when the number of exhaust pipes (40) is even.
9. A turbine assembly comprising a turbine exhaust volute with inlet pre-rotation vanes, characterized in that the turbine exhaust volute with inlet pre-rotation vanes is the turbine exhaust volute with inlet pre-rotation vanes of any one of claims 1 to 8.
10. The turbine assembly of claim 9, wherein the turbine assembly includes a turbine, an outlet of the turbine being connected to a diffuser inlet of the turbine exhaust volute with inlet pre-rotation vanes.
CN202310545875.9A 2023-05-15 2023-05-15 Turbine exhaust volute with inlet pre-rotation guide vane and turbine assembly Pending CN116446964A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310545875.9A CN116446964A (en) 2023-05-15 2023-05-15 Turbine exhaust volute with inlet pre-rotation guide vane and turbine assembly

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310545875.9A CN116446964A (en) 2023-05-15 2023-05-15 Turbine exhaust volute with inlet pre-rotation guide vane and turbine assembly

Publications (1)

Publication Number Publication Date
CN116446964A true CN116446964A (en) 2023-07-18

Family

ID=87132131

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310545875.9A Pending CN116446964A (en) 2023-05-15 2023-05-15 Turbine exhaust volute with inlet pre-rotation guide vane and turbine assembly

Country Status (1)

Country Link
CN (1) CN116446964A (en)

Similar Documents

Publication Publication Date Title
CN1214191C (en) Dewwirler system for centrifugal compressor
US7575412B2 (en) Anti-stall casing treatment for turbo compressors
US4530639A (en) Dual-entry centrifugal compressor
GB2124303A (en) Axial-flow ventilation fan
US10422345B2 (en) Centrifugal compressor curved diffusing passage portion
US20130115067A1 (en) Impeller
KR20140099206A (en) Axial turbine with meridionally divided turbine housing
KR20140099200A (en) Axial turbine with sector-divided turbine housing
EP3832144B1 (en) Diffuser pipe with radially-outward exit
CN109252900B (en) Combined type turbine
WO2020242788A1 (en) Mixed-flow compressor configuration for a refrigeration system
CN110418896B (en) Return stage and radial turbine fluid energy machine
JP3557389B2 (en) Multistage centrifugal compressor
CN116446964A (en) Turbine exhaust volute with inlet pre-rotation guide vane and turbine assembly
CN215444436U (en) High-circulation and low-pressure-loss radial and axial integrated diffuser
CN106662119B (en) Improved scroll for a turbomachine, turbomachine comprising said scroll and method of operation
CN115038878A (en) Outflow region of a compressor, compressor having an outflow region of said type and turbocharger having a compressor
CN112922861B (en) Compact low-rotation-speed centrifugal compressor
JP7123029B2 (en) centrifugal compressor
CN217381021U (en) Pneumatic component, dust collector and compressor comprising axial diffuser
RU2452876C1 (en) Radial-flow compressor stage
EP1682779B1 (en) Radial compressor impeller
US11131210B2 (en) Compressor for gas turbine engine with variable vaneless gap
CN211778224U (en) Two-section diffuser
US20230175524A1 (en) Compressor housing and centrifugal compressor

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination