CN113883087B - Meridian flow channel molded line of impeller, compressor and air cycle machine - Google Patents
Meridian flow channel molded line of impeller, compressor and air cycle machine Download PDFInfo
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- CN113883087B CN113883087B CN202111283018.3A CN202111283018A CN113883087B CN 113883087 B CN113883087 B CN 113883087B CN 202111283018 A CN202111283018 A CN 202111283018A CN 113883087 B CN113883087 B CN 113883087B
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—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
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—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
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Abstract
The invention provides a meridian flow passage molded line of an impeller, a compressor and an air cycle machine, wherein the meridian flow passage molded line comprises: wheel disc profile: R/R0 ═ a1(Z/R0) 6 –b1(Z/R0) 5 +c1(Z/R0) 4 –d1(Z/R0) 3 +e1(Z/R0) 2 -f 1(Z/R0) + g 1; blade tip profile: R/R0 ═ a2(Z/R0) 6 –b2(Z/R0) 5 +c2(Z/R0) 4 –d2(Z/R0) 3 +e2(Z/R0) 2 -f 2(Z/R0) + g 2. According to the invention, the gas flow in the impeller flow channel can be uniform, the impact loss of the gas in the meridian flow channel of the compressor impeller is reduced, and the efficiency of the compressor impeller is improved.
Description
Technical Field
The invention relates to the technical field of air cycle machines, in particular to a meridian flow channel molded line of an impeller, a compressor and an air cycle machine.
Background
Modern aircraft mostly employ air cycle refrigeration systems. In order to take account of the ground refrigerating capacity and the efficiency of the air circulation refrigerating system, the air circulating machine in the air circulation refrigerating system adopts a three-wheel type, and is characterized in that: the cooling air fan and booster compressor are mounted on a shaft and are driven by an expansion turbine. The turbine drives the compressor, so that the pressure at the inlet of the turbine is improved, the expansion ratio is also improved, larger turbine temperature drop can be obtained, the air supply pressure or air entraining quantity of a refrigerating system is smaller under the same refrigerating requirement, the compensation loss of the performance of the air entraining airplane is small, the oil consumption of an engine is less, and the economical efficiency is good. The high-performance air cycle machine also puts higher requirements on the performance of the air compressor, the core part in the air compressor is an impeller, and the meridian circulation performance of the impeller is very important for the performance of the air compressor.
Patent CN102536893A discloses a compressor rotor of ACM comprising a plurality of blades. Each blade includes a root, a tip, a first surface, and a second surface. The first and second surfaces of the blade are defined as tabular data scaled according to desired factors, i.e., a set of coordinates in three directions, x, y, and z. But the invention has not been made specifically for the meridional flow channels of the impeller.
The air flow in the inlet part of the impeller is a process of turning from axial flow to radial flow. In the turning process of the airflow, the phenomenon of uneven flow velocity can occur due to the action of centrifugal force and boundary viscous force of turning of the airflow. The air flow near the disk is slower and the air flow near the tip is faster. This non-uniform flow rate deteriorates the flow inside the impeller, resulting in separation losses and reduced impeller efficiency.
The invention provides a meridian flow channel molded line of an impeller, an impeller of a compressor, the compressor and an air circulator, which are researched and designed, and solve the technical problems that the separation loss of gas in a flow channel is large, the impact loss is large, the impeller efficiency of the compressor is low and the like because the phenomenon that the flow velocity of gas flow in the meridian flow channel of the compressor is uneven exists in the air circulator in the prior art.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defects of large gas separation loss and low impeller efficiency of the air compressor caused by non-uniform flow velocity of air flow in a meridian flow channel of the air compressor in the air cycle machine in the prior art, so that the meridian flow channel profile of the impeller, the air compressor and the air cycle machine are provided.
In order to solve the above problems, the present invention provides a radial flow channel profile of an impeller, including:
the profile of the wheel disc and the profile of the blade tip,
the direction of a rotating shaft of the compressor impeller is a Z axis, the cross section of an inlet of the compressor impeller and a hub of the compressor impeller is taken as an original point O, the direction from the inlet to an outlet of the compressor impeller is positive, an R axis is determined by the original point O and is vertical to the Z axis, and R0 is the inlet radius of the compressor impeller; and comprises the following components:
said wheel disk typeThe line satisfies the following equation: R/R0 ═ a1(Z/R0) 6 –b1(Z/R0) 5 +c1(Z/R0) 4 –d1(Z/R0) 3 +e1(Z/R0) 2 -f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 is 3-7; f1 is 0-1; g1 is 0-2;
the blade tip profile satisfies the following equation: R/R0 ═ a2(Z/R0) 6 –b2(Z/R0) 5 +c2(Z/R0) 4 –d2(Z/R0) 3 +e2(Z/R0) 2 -f 2(Z/R0) + g2, wherein a2 is 7-11; b2 is 28-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0-3.
In some embodiments, a1 ═ 2.135; b1 ═ 9.9607; c1 ═ 17.511; d1 ═ 14.103; e1 ═ 5.4936; f1 ═ 0.6551; g1 ═ 1.0068.
In some embodiments, a2 ═ 9.1301; b2 ═ 30.664; c2 ═ 38.809; d2 ═ 22.518;
e2＝6.3658；f2＝0.5434；g2＝1.7692。
in some embodiments, the coordinate θ is tangential about the axis of rotation and positive in a direction opposite the direction of rotation of the compressor wheel; r0 is the perpendicular distance of the disc profile from the Z axis at the inlet.
In some embodiments, the disk profile is formed by mapping a disk camber to a meridian plane, and the tip profile is formed by mapping a tip camber to a meridian plane, the meridian plane being a longitudinal section through an axis of the rotating shaft.
The invention also provides a compressor impeller which comprises a meridian flow channel, wherein the molded line of the meridian flow channel is the molded line of the meridian flow channel of the compressor impeller in any item.
In some embodiments, when including the disk curve and the tip curve:
the compressor impeller comprises a plurality of blades and a wheel disc, the blades are arranged on the wheel disc at intervals along the circumferential direction, the curved surface of each blade arranged on the wheel disc is a wheel disc curved surface, and one side surface of each blade deviating from the wheel disc curved surface is a blade top curved surface.
In some embodiments, the compressor further comprises a hub connected to one axial end of the wheel disc, the hub has a first central shaft hole, the wheel disc has a second central shaft hole, and a rotating shaft can simultaneously penetrate into the first central shaft hole and the second central shaft hole to drive the compressor impeller to rotate.
The invention also provides a compressor, which comprises the compressor impeller, a diffuser and a shell, wherein the diffuser is arranged on the shell;
when the compressor impeller comprises blades and a wheel disc, the shell is connected with the blades of the compressor impeller, and the shell, the blades and the wheel disc jointly enclose a relatively sealed compression flow channel.
The invention also provides an air cycle machine comprising the compressor of any one of the preceding claims.
The meridian flow channel molded line of the impeller, the compressor and the air cycle machine have the following beneficial effects:
the invention provides a novel meridian flow channel molded line of a centrifugal impeller, which consists of a wheel disc molded line and a blade top molded line, wherein the wheel disc molded line meets the following equation: R/R0 ═ a1(Z/R0) 6 –b1(Z/R0) 5 +c1(Z/R0) 4 –d1(Z/R0) 3 +e1(Z/R0) 2 -f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 is 3-7; f1 is 0-1; g1 is 0-2; the tip profile line satisfies the following equation: R/R0 ═ a2(Z/R0) 6 –b2(Z/R0) 5 +c2(Z/R0) 4 –d2(Z/R0) 3 +e2(Z/R0) 2 -f 2(Z/R0) + g2, wherein a2 is 7-11; b2 is 28-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0 ~ 3, can effectively determine impeller meridian runner, when flowing in this meridian runner, can effectively reduce the centrifugal force and the boundary viscous force effect that the air current turned, the increase is close to the air current velocity of rim plate, reduce the air current velocity of being close to the blade top, the air current velocity of flow between effective even rim plate to the blade top, the gas flow in the even impeller runner, thereby reduce the impact loss of gas in compressor impeller meridian runner, improveThe efficiency of the impeller of the air compressor is lower, so that the fluid impact loss is lower, and the efficiency of the impeller is higher.
Drawings
FIG. 1 is a view of the external appearance of the air cycle machine of the present invention;
FIG. 2 is a cross-sectional view of an air cycle machine of the present invention;
FIG. 3 is a meridional flow path view of a compressor wheel of the present invention;
FIG. 4 is a perspective view of a compressor wheel of the present invention;
figure 5 is a plot of the velocity vector of the gas of the present invention in a meridional flow channel.
The reference numerals are represented as:
01. a compressor impeller; 0101. a meridian flow channel; 010101, a wheel disc profile; 010102, a blade tip profile; 0102. a wheel disc curved surface; 0103. a leaf top curved surface; 0104. an inlet; 0105. an outlet; 0106. a rotating shaft; 02. a diffuser; 03. a housing; 1. a blade; 2. a wheel disc; 21. a second central shaft hole; 3. a hub; 31. a first central shaft hole; t01, expansion inlet; t02, expansion outlet; c01, a compression inlet; c02, compression outlet; f01, a fan inlet; f02, and a fan outlet.
Detailed Description
Referring to fig. 1-5, the present invention provides a radial runner profile for a compressor wheel, comprising:
the direction of a rotating shaft 0106 of the compressor impeller is a Z axis, the cross section of an inlet 0104 of the compressor impeller and a hub of the compressor impeller is an original point O, the direction from the inlet 0104 to an outlet 0105 of the compressor impeller is positive, an R axis is determined by the original point O and is perpendicular to the Z axis, and R0 is the inlet radius of the compressor impeller; and comprises the following components:
the wheel disc type line 010101 satisfies the following equation: R/R0 ═ a1(Z/R0) 6 –b1(Z/R0) 5 +c1(Z/R0) 4 –d1(Z/R0) 3 +e1(Z/R0) 2 -f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 is 3-7; f1 is 0-1; g1 is 0-2;
the tip profile (010102) satisfies the following equation: R/R0 ═ a2(Z/R0) 6 –b2(Z/R0) 5 +c2(Z/R0) 4 –d2(Z/R0) 3 +e2(Z/R0) 2 -f 2(Z/R0) + g2, wherein a2 is 7-11; b2 is 28-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0-3.
The invention provides a novel meridian flow channel molded line of a centrifugal impeller, which consists of a wheel disc molded line and a blade top molded line, wherein the wheel disc molded line meets the following equation: R/R0 ═ a1(Z/R0) 6 –b1(Z/R0) 5 +c1(Z/R0) 4 –d1(Z/R0) 3 +e1(Z/R0) 2 -f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 is 3-7; f1 is 0-1; g1 is 0-2; the tip profile line satisfies the following equation: R/R0 ═ a2(Z/R0) 6 –b2(Z/R0) 5 +c2(Z/R0) 4 –d2(Z/R0) 3 +e2(Z/R0) 2 -f 2(Z/R0) + g2, wherein a2 is 7-11; b2 is 28-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0 ~ 3, can effectively determine impeller meridian runner, when flowing in this meridian runner, can effectively reduce the centrifugal force and the marginal viscous force effect that the air current turned, the increase is close to the airflow velocity of rim plate, reduce the airflow velocity of being close to the leaf top, effective even rim plate is to the airflow velocity between the leaf top, the gas flow in the even impeller runner, thereby reduce the impact loss of gas in compressor impeller meridian runner, improve compressor impeller efficiency, make fluid impact loss littleer, impeller efficiency is higher.
In some embodiments, a1 ═ 2.135; b1 ═ 9.9607; c1 ═ 17.511; d1 ═ 14.103; e1 ═ 5.4936; f1 ═ 0.6551; g1 ═ 1.0068. The parameters in the wheel disc molded line are further optimized, the flow velocity of the air flow close to the wheel disc can be further increased through the designed wheel disc molded line, the flow velocity of the air flow between the wheel disc and the blade top is uniform, the air flow in an impeller flow channel is uniform, the impact loss of the air in a meridian flow channel of the compressor impeller is reduced, and the efficiency of the compressor impeller is improved.
In some embodiments, a2 ═ 9.1301; b2 ═ 30.664; c2 ═ 38.809; d2 ═ 22.518;
e2 ═ 6.3658; f2 ═ 0.5434; g2 ═ 1.7692. The optimized values of the parameters in the blade top molded line can further reduce the flow velocity of the airflow close to the blade top, homogenize the flow velocity of the airflow between the wheel disc and the blade top, homogenize the flow of the air in the impeller flow channel, reduce the impact loss of the air in the meridian flow channel of the compressor impeller and improve the efficiency of the compressor impeller.
In some embodiments, the coordinate θ is tangential around the rotation axis 0106 and positive in the opposite direction of the rotation direction of the compressor wheel; r0 is the perpendicular distance between the wheel disc profile 010101 and the Z-axis at the inlet 0104. This is a preferred configuration of the rotation angle coordinate θ of the present invention, and a specific determination of R0.
In some embodiments, the wheel disc profile 010101 is formed by mapping a wheel disc curved surface 0102 to a meridian plane, and the blade tip profile 010102 is formed by mapping a blade tip curved surface 0103 to a meridian plane, which is a longitudinal section passing through the axis of the rotating shaft 0106. The wheel disc molded line is formed by projecting a wheel disc curved surface onto a meridian plane, and the blade top molded line is formed by projecting a blade top curved surface onto the meridian plane.
The invention also provides a compressor impeller which comprises a meridian flow channel, wherein the molded line of the meridian flow channel is the molded line of the meridian flow channel of the compressor impeller in any item.
The compressor impeller of the invention adopts the special meridian flow channel molded line, so that the gas flow in the impeller flow channel can be effectively and uniformly, the impact loss of the gas in the meridian flow channel of the compressor impeller is reduced, and the efficiency of the compressor impeller is improved.
The gas of the invention has better streamline flow in the meridian flow channel, as shown in figure 5, and has no obvious backflow and separation flow, thereby reducing the impact loss of the gas in the meridian flow channel of the compressor impeller.
In some embodiments, when including the disk curved surface 0102 and the blade top curved surface 0103:
the compressor impeller comprises a plurality of blades 1 and a wheel disc 2, wherein the blades 1 are arranged on the wheel disc 2 at intervals along the circumferential direction, the wheel disc 2 is provided with curved surfaces of the blades 1 which are 0102, and one side surface of each blade 1 deviating from the curved surface 0102 of the wheel disc is 0103 of the top of each blade. The invention is a further optimized structure form of the compressor impeller, namely the position structures of the blade top curved surface and the wheel disc curved surface.
In some embodiments, the hub 3 is connected to one axial end of the wheel disc 2, the hub 3 has a first central shaft hole 31, the wheel disc 2 has a second central shaft hole 21, and a rotating shaft can simultaneously penetrate into the first central shaft hole 31 and the second central shaft hole 32 to drive the compressor impeller to rotate. The impeller can be effectively sleeved on the rotating shaft through the arrangement of the hub.
The invention also provides a compressor, which comprises the compressor impeller 01, a diffuser 02 and a shell 03;
when the compressor impeller comprises the blades 1 and the wheel disc 2, the shell 03 is connected with the blades 1 of the compressor impeller 01, and the shell 03, the blades 1 and the wheel disc 2 jointly enclose a relatively sealed compression flow channel.
The compressor impeller of the invention adopts a special meridian flow channel molded line, has no obvious backflow and flow separation, can effectively and uniformly flow the gas in the impeller flow channel, reduces the impact loss of the gas in the meridian flow channel of the compressor impeller, and improves the efficiency of the compressor impeller.
The invention also provides an air cycle machine which comprises the air compressor.
The air cycle machine for compressed air refrigerating system has the advantages that after the air flows into the expansion inlet T01 and works through the expansion machine, the pressure and the temperature are reduced, and the air flows out of the expansion outlet T02, so that the aim of adjusting the pressure and the temperature of the air is fulfilled. The work of expansion drives the compressor and fan. One air flow is sucked from a compression inlet C01, is compressed by a compression impeller and then is discharged from a compression outlet C02, and the compressed air is supplied to an expansion machine, so that the inlet pressure of the expansion machine is improved, the expansion ratio is increased, the temperature drop of the expansion machine is enlarged, and the aims of small air-entraining quantity, small compensation loss, low oil consumption of an engine and good economical efficiency of the system under the same refrigeration requirement are fulfilled. Meanwhile, another air flow is sucked in through the fan inlet F01 and is discharged out at the fan outlet F02, so that the purpose of providing cooling air flow for the compressed air refrigeration system is achieved. As shown in fig. 1.
The air circulator of the invention adopts the special compressor impeller which adopts a special meridian flow passage molded line, so that the air flow in the compressor impeller does not obviously flow back and separate in the flowing process, the air flow in the impeller flow passage can be effectively and uniformly flowed, the impact loss of the air in the meridian flow passage of the compressor impeller is reduced, and the efficiency of the compressor impeller is improved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A meridian flow passage molded line of an impeller is characterized in that: the method comprises the following steps:
a wheel disc profile (010101) and a blade tip profile (010102),
the direction of a rotating shaft (0106) of the impeller is a Z axis, the cross section of the inlet (0104) of the impeller and the hub (3) of the impeller is taken as an origin O, the direction from the inlet (0104) to the outlet (0105) of the impeller is positive, the origin O is used for determining an R axis perpendicular to the Z axis, and R0 is the inlet radius of the impeller; and has the following components:
the wheel disc profile (010101) satisfies the equation: R/R0 ═ a1(Z/R0) 6 –b1(Z/R0) 5 +c1(Z/R0) 4 –d1(Z/R0) 3 +e1(Z/R0) 2 -f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 is 3-7; f1 is 0-1; g1 is 0-2;
the tip profile (010102) satisfies the following equation: R/R0 ═ a2(Z/R0) 6 –b2(Z/R0) 5 +c2(Z/R0) 4 –d2(Z/R0) 3 +e2(Z/R0) 2 -f 2(Z/R0) + g2, wherein a2 is 7-11; b2 is 28-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0-3.
2. The radial flow channel profile of an impeller of claim 1, wherein:
a1＝2.135；b1＝9.9607；c1＝17.511；d1＝14.103；e1＝5.4936；f1＝0.6551；g1＝1.0068。
3. the radial flow channel profile of an impeller of claim 1, wherein:
a2＝9.1301；b2＝30.664；c2＝38.809；d2＝22.518；e2＝6.3658；f2＝0.5434；g2＝1.7692。
4. the radial flow channel profile of an impeller according to any one of claims 1 to 3, wherein:
-the coordinate θ is tangential around the rotation axis (0106) and positive in the opposite direction of the direction of rotation of the impeller; r0 is the perpendicular distance between the wheel disc profile (010101) at the inlet (0104) and the Z axis.
5. The radial flow channel profile of an impeller according to any one of claims 1 to 3, wherein:
the wheel disc profile (010101) is formed by mapping a wheel disc curved surface (0102) onto a meridian plane, the tip profile (010102) is formed by mapping a tip curved surface (0103) onto a meridian plane, and the meridian plane is a longitudinal section passing through an axis of the rotating shaft (0106).
6. A compressor wheel, characterized by: comprising a radial flow channel, the profile of which is that of the impeller of any one of claims 1 to 5.
7. The compressor wheel of claim 6, wherein:
when including the wheel disc camber (0102) and the blade tip camber (0103):
the compressor impeller comprises blades (1) and a wheel disc (2), wherein the blades (1) are arranged on the wheel disc (2) at intervals in the circumferential direction, the wheel disc (2) is provided with curved surfaces of the blades (1) which are wheel disc curved surfaces (0102), the blades (1) deviate from one side surface of each wheel disc curved surface (0102) to form a blade top curved surface (0103).
8. The compressor wheel of claim 7, wherein:
still include wheel hub (3), wheel hub (3) connect in the axial one end of rim plate (2), just wheel hub (3) have first central shaft hole (31), rim plate (2) have second central shaft hole (21), and the pivot can penetrate simultaneously first central shaft hole (31) with in second central shaft hole (21) with the drive the compressor impeller rotates.
9. A compressor, characterized by: compressor wheel (01) according to one of claims 6 to 8, further comprising a diffuser (02) and a housing (03);
when the compressor impeller comprises the blades (1) and the wheel disc (2), the shell (03) is connected with the blades (1) of the compressor impeller (01), and the shell (03), the blades (1) and the wheel disc (2) jointly enclose a relatively sealed compression flow channel.
10. An air cycle machine, characterized by: comprising an air compressor as claimed in claim 9.
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| CN113464497A (en) * | 2021-06-24 | 2021-10-01 | 珠海格力电器股份有限公司 | Diffuser, compressor and air cycle machine |
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| CN2743586Y (en) * | 2004-11-03 | 2005-11-30 | 大连经济技术开发区泽通机械有限公司 | New type impeller of booster air compressor for diesel locomotive |
| CN102608914B (en) * | 2011-12-22 | 2014-03-12 | 西安交通大学 | Optimization design method of radial-flow-type hydraulic turbine |
| CN102518602B (en) * | 2011-12-29 | 2014-12-24 | 中联重科股份有限公司 | Centrifugal fan impeller and centrifugal fan |
| CN106640210B (en) * | 2016-09-14 | 2019-03-05 | 西安交通大学苏州研究院 | A kind of design method of diameter-axial-flow expansion turbine impeller blade three-dimensional molded line |
| CN107092763B (en) * | 2017-05-22 | 2020-07-10 | 宁波聚清源环保科技有限公司 | Method for three-dimensional design of turbomachinery impeller with castability |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113464497A (en) * | 2021-06-24 | 2021-10-01 | 珠海格力电器股份有限公司 | Diffuser, compressor and air cycle machine |
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