CN116608138A

CN116608138A - Turbine type fluid machine

Info

Publication number: CN116608138A
Application number: CN202310109024.XA
Authority: CN
Inventors: 楳山亮
Original assignee: Toyota Industries Corp
Current assignee: Toyota Industries Corp
Priority date: 2022-02-17
Filing date: 2023-02-14
Publication date: 2023-08-18
Also published as: JP2023119769A; US20230258200A1; DE102023103647A1

Abstract

The invention provides a turbine type fluid machine capable of sufficiently increasing the pressure of a 2 nd compressed fluid and realizing low manufacturing cost and miniaturization. A turbine type fluid machine is provided with a casing (1), 1 st and 2 nd impellers (7, 8), a compressed fluid passage (9), 1 st flow passages (31 a-31 g), and the like. The 1 st and 2 nd impeller chambers (27 a, 29 a) are formed in the casing. The 1 st impeller (7) is housed in the 1 st impeller chamber (27 a), and the 1 st compressed air is formed by compressing air. The 2 nd impeller (8) is housed in the 2 nd impeller chamber (29 a), and the 1 st compressed air is compressed to form the 2 nd compressed air. The compressed fluid passage supplies the 1 st compressed air to the 2 nd impeller chamber. The 1 st whole flow path (31 a-31 g) is arranged in the compression fluid passage. The 1 st flow path extends in the direction in which the compressed fluid passage extends, and rectifies and supplies the 1 st compressed fluid to the 2 nd impeller chamber.

Description

Turbine type fluid machine

Technical Field

The present invention relates to a turbine type fluid machine.

Background

Patent documents 1 and 2 disclose conventional turbo-type fluid machines. The turbine type fluid machine of patent document 1 includes a casing, an electric motor, an impeller, a drive shaft, and a compressed fluid passage. An impeller chamber and a motor chamber are formed in the housing. The impeller chamber includes a 1 st impeller chamber and a 2 nd impeller chamber separated from the 1 st impeller chamber in the axial direction of the drive shaft. The motor chamber is disposed between the 1 st impeller chamber and the 2 nd impeller chamber. The electric motor is accommodated in the motor chamber.

The impeller includes a 1 st impeller accommodated in the 1 st impeller chamber and a 2 nd impeller accommodated in the 2 nd impeller chamber. The drive shaft is housed in the housing, extends in the axial direction, and connects the 1 st and 2 nd impellers to the electric motor. Further, a discharge port and a suction port are formed in the housing. The discharge port communicates with the 1 st impeller chamber and the suction port communicates with the 2 nd impeller chamber. The compressed fluid passage is located outside the housing and connects the discharge port and the suction port.

In this turbo type fluid machine, the 1 st and 2 nd impellers rotate by the rotation of the electric motor, and the fluid is compressed in 2 stages. Specifically, the 1 st impeller compresses the fluid in the 1 st impeller chamber to become the 1 st compressed fluid. The 1 st compressed fluid is supplied from the 1 st impeller chamber to the 2 nd impeller chamber through the compressed fluid passage. Then, the 2 nd impeller compresses the 1 st compressed fluid to become the 2 nd compressed fluid.

The turbine type fluid machine imparts a rotational component to the 1 st compressed fluid and the 2 nd compressed fluid by the 1 st impeller and the 2 nd impeller rotating. In the turbo type fluid machine, the 1 st compressed fluid is supplied to the 2 nd impeller chamber while flowing through the compressed fluid passage in a state having a rotational component. Therefore, when the 1 st compressed fluid is compressed by the 2 nd impeller to become the 2 nd compressed fluid, it is difficult to increase the pressure of the 2 nd compressed fluid due to the rotational component of the 1 st compressed fluid, and the compression performance of the fluid is low.

In contrast, in the turbine type fluid machine of patent document 2, a partition plate is provided in the compressed fluid passage. The partition plate has an opening formed in the center thereof through which the 1 st compressed fluid can flow, and is annular. In addition, a plurality of return guide vanes are formed in the partition plate. The return guide vanes are arranged along the circumferential direction of the partition plate.

In this turbo type fluid machine, the 1 st compressed fluid flowing through the compressed fluid passage is guided from the outer peripheral side of the partition plate to the opening by the return guide vanes, flows through the opening, and flows toward the suction port. In this way, in the turbo fluid machine, the partition plate rectifies the 1 st compressed fluid by each return guide vane and supplies the rectified compressed fluid to the 2 nd impeller chamber. As a result, the turbine fluid machine can sufficiently increase the pressure of the 2 nd compressed fluid.

[ Prior Art literature ]

[ patent literature ]

Japanese patent application laid-open No. 2015-187444

Japanese patent application laid-open No. 8-200296

Disclosure of Invention

Problems to be solved by the invention

Such turbine type fluid machinery is required to be miniaturized in order to improve the mountability to a vehicle or the like. However, in the turbo type fluid machine of patent document 2, the partition plate is complicated in structure, and therefore it is difficult to miniaturize the partition plate. In addition, the compressed fluid passage is inevitably enlarged to secure a space for disposing the partition plate. Therefore, in the turbine fluid machine, miniaturization is difficult. In addition, since the structure of the partition plate is complicated, the manufacturing cost increases in the turbine fluid machine.

The present invention has been made in view of the above-described conventional circumstances, and an object thereof is to provide a turbine fluid machine that can exhibit high compression performance and can be reduced in size and manufacturing cost.

Means for solving the problems

The turbine type fluid machine of the present invention comprises:

a housing formed with an impeller chamber and a motor chamber;

an electric motor accommodated in the motor chamber;

an impeller housed in the impeller chamber, the impeller compressing a fluid by rotation of the electric motor; a kind of electronic device with high-pressure air-conditioning system

A drive shaft housed in the housing and connecting the impeller and the electric motor,

the impeller chamber has a 1 st impeller chamber and a 2 nd impeller chamber separated from the 1 st impeller chamber in an axial direction of the drive shaft,

the impeller includes a 1 st impeller accommodated in the 1 st impeller chamber and compressing the fluid to be a 1 st compressed fluid, and a 2 nd impeller accommodated in the 2 nd impeller chamber and compressing the 1 st compressed fluid to be a 2 nd compressed fluid,

the turbine type fluid machine is characterized in that,

the turbine type fluid machine further includes:

a compressed fluid passage for supplying the 1 st compressed fluid to the 2 nd impeller chamber; and

And a plurality of rectifying passages provided in the compressed fluid passage and extending in a direction in which the compressed fluid passage extends, for rectifying the 1 st compressed fluid and supplying the same to the 2 nd impeller chamber.

In the turbine-type fluid machine of the present invention, the 1 st compressed fluid is rectified and supplied to the 2 nd impeller chamber through the respective whole flow paths provided in the compressed fluid passage. Thus, the turbine fluid machine can reduce the rotational component of the 1 st compressed fluid supplied to the 2 nd impeller chamber, compared with the case where the 1 st compressed fluid is supplied to the 2 nd impeller chamber without being rectified. Therefore, in the turbine fluid machine, the pressure of the 2 nd compressed fluid can be sufficiently increased by the 2 nd impeller.

In this turbo type fluid machine, since each of the rectifying passages has a shape extending in the direction in which the compressed fluid passage extends, the structure of each of the rectifying passages can be simplified, the size and cost can be reduced, and the 1 st compressed fluid can be properly rectified by each of the rectifying passages in the process of flowing the 1 st compressed fluid. In this turbo type fluid machine, a plurality of rectifying passages can be provided inside the turbo type fluid machine, and the size of the compressed fluid passage can be reduced.

Therefore, the turbine type fluid machine of the present invention can exhibit high compression performance and achieve miniaturization and low manufacturing cost.

The rectifying circuits are preferably arranged closer to the 2 nd impeller chamber than to the 1 st impeller chamber. In this case, the 1 st compressed fluid rectified by each rectifying passage can be supplied to the 2 nd impeller chamber while minimizing the pressure loss.

Further, each of the rectifying paths is preferably formed of a cylindrical body extending in a straight line. In this case, the entire flow paths can be easily formed, and therefore, the manufacturing cost can be further reduced. Further, since each of the rectifying passages is a cylindrical body, the 1 st compressed fluid can properly flow through the inside of each of the rectifying passages, and the 1 st compressed fluid can be properly rectified during the flow through the inside of each of the rectifying passages.

The compressed fluid passage is preferably provided with a cooling portion for cooling the 1 st compressed fluid flowing through each of the rectifying passages. In this case, the 1 st compressed fluid can be cooled and supplied to the 2 nd impeller chamber, and therefore, the 2 nd impeller does not need to be formed of a material having excessively high heat resistance. In this regard, the manufacturing cost can be reduced in the turbo type fluid machine.

In addition, by cooling the 1 st compressed fluid, the 2 nd compressed fluid can be suppressed from being heated. Therefore, in the turbine fluid machine, a cooling portion for cooling the 2 nd compressed fluid is not necessarily required. In this turbo type fluid machine, the compressed fluid passage can be suppressed from becoming high temperature.

Effects of the invention

The turbine type fluid machine of the present invention can exhibit high compression performance and realize miniaturization and low manufacturing cost.

Drawings

Fig. 1 is a cross-sectional view showing a turbo type fluid machine of embodiment 1.

Fig. 2 is an enlarged cross-sectional view of a main part of the turbine fluid machine according to example 1, showing the X portion of fig. 1.

Fig. 3 is a cross-sectional view of the turbo type fluid machine according to example 1, showing A-A of fig. 2 in a cross-section.

Fig. 4 is a schematic view showing the passage cross-sectional area of the compressed fluid passage and the passage cross-sectional area of the whole flow path in the turbo type fluid machine of example 1. Fig. 4 (a) shows the passage sectional area of the compressed fluid passage. Fig. 4 (B) shows the passage cross-sectional area of the entire flow path.

Fig. 5 is an enlarged cross-sectional view of the same essential part as fig. 2 showing the compressed fluid passage, the rectifying passage, and the cooling part of the turbo type fluid machine according to example 2.

Fig. 6 is a cross-sectional view of the turbo type fluid machine according to example 2, showing a cross-section taken in the B-B direction of fig. 5.

Fig. 7 is a schematic view showing the passage cross-sectional area of the compressed fluid passage and the passage cross-sectional area of the whole flow path in the turbo type fluid machine of example 2. Fig. 7 (a) shows the passage sectional area of the compressed fluid passage. Fig. 7 (B) shows the passage cross-sectional area of the entire flow path.

Fig. 8 is a cross-sectional view of the turbo type fluid machine according to example 2, showing the C-C cross-section of fig. 5.

Fig. 9 is a cross-sectional view of the turbo type fluid machine according to example 3 in the same direction as fig. 3.

Fig. 10 is a schematic view showing the passage cross-sectional area of the compressed fluid passage and the passage cross-sectional area of the whole flow path in the turbo type fluid machine of example 3. Fig. 10 (a) shows the passage sectional area of the compressed fluid passage. Fig. 10 (B) shows the passage cross-sectional area of the entire flow path.

Description of the reference numerals

1 … shell

3 … electric motor

5 … drive shaft

7 … impeller 1 (impeller)

8 … impeller 2 (impeller)

9 … compressed fluid passage

27a … No. 1 impeller chamber (impeller chamber)

29a … No. 2 impeller chamber (impeller chamber)

30 … motor chamber

31a to 31g … 1 st whole flow path (rectifying path)

33a to 33g …, 2 nd whole flow path (rectifying path)

35a to 35d … 3 rd flow path (flow path)

41 … cooling part

Detailed Description

Hereinafter, examples 1 to 3 embodying the present invention will be described with reference to the drawings. The turbine fluid machines of examples 1 to 3 were each mounted on a fuel cell vehicle and connected to a fuel cell stack. The fuel cell vehicle and the fuel cell stack are not shown.

As shown in fig. 1 to 3, the turbo fluid machine of example 1 includes a casing 1, an electric motor 3, a drive shaft 5, impellers including a 1 st impeller 7 and a 2 nd impeller 8, a compressed fluid passage 9, and 7 1 st whole passages 31a to 31g. The 1 st whole flow paths 31a to 31g are examples of "whole flow paths" in the present invention.

In the present embodiment, the front-rear direction of the turbine type fluid machine is defined by solid arrows shown in fig. 1. The front-rear direction is an example of the "axial direction of the drive shaft" in the present invention. In addition, the turbo fluid machine can change its posture appropriately according to the vehicle mounted thereon.

The case 1 is made of aluminum alloy. As shown in fig. 1, the casing 1 includes a motor casing 10, a 1 st plate 11, a 2 nd plate 12, a 3 rd plate 13, a 1 st compressor casing 14, and a 2 nd compressor casing 15.

The motor housing 10 has an end wall 10a and a peripheral wall 10b. The end wall 10a is located at the rear end of the motor housing 10, extending in the radial direction of the motor housing 10. The end wall 10a has a 1 st end face 101 facing forward and a 2 nd end face 102 located on the opposite side of the 1 st end face 101 and facing rearward. The 2 nd end surface 102 constitutes a rear end surface of the motor housing 10.

The peripheral wall 10b is integrally formed with the end wall 10a, and extends cylindrically from the end wall 10a toward the front. The front of the peripheral wall 10b is open. The motor case 10 has a bottomed tubular shape by the end wall 10a and the peripheral wall 10 b. A flange portion 10c is formed at the front end of the peripheral wall 10 b. The flange portion 10c protrudes radially outward of the motor housing 10 than the peripheral wall 10 b.

The 1 st plate 11 is located in front of the motor housing 10. The 1 st plate 11 has a 1 st front surface 11a located at the front and a 1 st rear surface 11b located at the rear. The 1 st plate 11 has the 1 st rear surface 11b in contact with the flange portion 10c and is connected to the flange portion 10c. Thereby, the 1 st plate 11 closes the opening of the peripheral wall 10 b. In this way, the motor chamber 30 is partitioned by the end wall 10a, the peripheral wall 10b, and the 1 st rear surface 11b in the interior of the motor case 10.

The 1 st plate 11 is formed with a 1 st boss portion 11c, a 1 st recess portion 11d, and a 1 st shaft hole 11e. The 1 st boss portion 11c protrudes cylindrically rearward from the 1 st rear surface 11b, and extends into the motor chamber 30. The 1 st radial bearing 21a is provided inside the 1 st boss portion 11 c.

The 1 st concave portion 11d is recessed rearward from the 1 st front surface 11 a. Inside the 1 st concave portion 11d, a 1 st thrust bearing 23a and a 2 nd thrust bearing 23b are provided. The 1 st shaft hole 11e is located in the center portion of the 1 st plate 11, and penetrates the 1 st plate 11 in the front-rear direction. Thus, the 1 st shaft hole 11e communicates with the 1 st recess 11d at the front end and communicates with the 1 st boss 11c at the rear end. The 1 st boss portion 11c, the 1 st recess portion 11d, and the 1 st shaft hole 11e are coaxial with each other.

Further, a 2 nd boss portion 10d and a 2 nd shaft hole 10e are formed in an end wall 10a of the motor case 10. The 2 nd boss portion 10d protrudes cylindrically from the 1 st end surface 101 toward the front, and extends into the motor chamber 30. The 2 nd radial bearing 21b is provided inside the 2 nd boss portion 10 d. The 2 nd shaft hole 10e is located at the center of the end wall 10a, and penetrates the end wall 10a in the front-rear direction. Thus, the 2 nd shaft hole 10e communicates with the 2 nd boss portion 10d at the tip end. The 2 nd boss portion 10d and the 2 nd shaft hole 10e are coaxial with the 1 st boss portion 11c, the 1 st recess portion 11d and the 1 st shaft hole 11 e.

The 2 nd plate 12 is located in front of the 1 st plate 11. The 2 nd plate 12 has a 2 nd front surface 12a located at the front and a 2 nd rear surface 12b located at the rear. The 2 nd plate 12 is connected to the 1 st plate 11 by abutting the 2 nd rear surface 12b against the 1 st front surface 11 a.

The 2 nd plate 12 is formed with a 2 nd recess 12c and a 3 rd shaft hole 12d. The 2 nd concave portion 12c is concavely provided from the 2 nd front surface 12a toward the rear. The 2 nd recess 12c is formed to have a smaller diameter than the 1 st recess 11 d. A 1 st seal member 25a is provided inside the 2 nd recess 12 c. The 3 rd shaft hole 12d is located at the center of the 2 nd plate 12, and penetrates the 2 nd plate 12 in the front-rear direction. Thus, the 3 rd shaft hole 12d communicates with the 2 nd recess 12c at the front end and communicates with the 1 st recess 11d at the rear end. The 2 nd recess 12c and the 3 rd shaft hole 12d are coaxial with the 1 st boss portion 11c, the 1 st recess 11d and the 1 st shaft hole 11 e.

The 3 rd plate 13 is located at the rear of the motor housing 10. The 3 rd plate 13 has a 3 rd front surface 13a located at the front and a 3 rd rear surface 13b located at the rear. The 3 rd plate 13 is connected to the motor case 10 by abutting the 3 rd front surface 13a against the 2 nd end surface 102 of the end wall 10 a.

The 3 rd plate 13 is formed with a 3 rd recess 13c and a 4 th shaft hole 13d. The 3 rd concave portion 13c is concavely provided from the 3 rd rear surface 13b toward the front. The 3 rd recess 13c and the 2 nd recess 12c are formed to have the same diameter. A 2 nd seal member 25b is provided in the 3 rd recess 13 c. The 4 th shaft hole 13d is located at the center of the 3 rd plate 13, and penetrates the 3 rd plate 13 in the front-rear direction. Thus, the 4 th shaft hole 13d communicates with the 2 nd shaft hole 10e at the front end and communicates with the 3 rd recess 13c at the rear end. The 3 rd concave portion 13c and the 4 th shaft hole 13d are coaxial with the 2 nd boss portion 10d and the 2 nd shaft hole 10 e. That is, the 3 rd concave portion 13c and the 4 th shaft hole 13d are coaxial with the 1 st boss portion 11c, the 1 st concave portion 11d, the 1 st shaft hole 11e, the 2 nd concave portion 12c and the 3 rd shaft hole 12 d.

The 1 st compressor housing 14 is located forward of the 2 nd plate 12. The 1 st compressor housing 14 is cylindrical, abuts against the 2 nd front surface 12a of the 2 nd plate 12, and is connected to the 2 nd plate 12. Thus, the 1 st compressor housing 14 constitutes the front end portion of the housing 1. The 1 st compressor housing 14 has a 1 st suction port 14a and a 1 st discharge port 14b.

The 1 st suction port 14a is coaxial with the 3 rd shaft hole 12d, and extends in the front-rear direction inside the 1 st compressor housing 14. The front end of the 1 st suction port 14a opens at the front end surface 140 of the 1 st compressor housing 14. A suction pipe 37 is connected to the 1 st suction port 14 a. The air containing oxygen is sucked from the outside of the casing 1 to the 1 st suction port 14a through the suction pipe 37. Air is an example of "fluid" in the present invention.

The 1 st discharge port 14b extends radially inside the 1 st compressor housing 14 and opens to the outer peripheral surface 141 of the 1 st compressor housing 14. The 1 st straight passage 9a of the compressed fluid passage 9 described later is connected to the 1 st discharge port 14 b.

Further, between the 1 st compressor housing 14 and the 2 nd front surface 12a, a 1 st impeller chamber 27a, a 1 st discharge chamber 27b, and a 1 st diffusion flow path 27c are formed. The 1 st impeller chamber 27a communicates with the 1 st suction port 14 a. The 1 st discharge chamber 27b extends around the axis of the 1 st suction port 14a around the 1 st impeller chamber 27 a. The 1 st discharge chamber 27b communicates with the 1 st discharge port 14 b. The 1 st diffusion channel 27c communicates the 1 st impeller chamber 27a with the 1 st discharge chamber 27 b. Thus, the 1 st impeller chamber 27a communicates with the 1 st discharge port 14b through the 1 st diffusion channel 27c and the 1 st discharge chamber 27 b.

The 2 nd compressor housing 15 is located behind the 3 rd plate 13. Like the 1 st compressor housing 14, the 2 nd compressor housing 15 is also cylindrical. The 2 nd compressor housing 15 abuts against the 3 rd rear surface 13b of the 3 rd plate 13 and is coupled to the 3 rd plate 13. Thus, the 2 nd compressor housing 15 constitutes the rear end portion of the housing 1. Further, a 2 nd suction port 15a and a 2 nd discharge port 15b are formed in the 2 nd compressor housing 15.

The 2 nd suction port 15a is coaxial with the 1 st suction port 14a, and extends in the front-rear direction inside the 2 nd compressor housing 15. The rear end of the 2 nd suction port 15a opens at the rear end surface 150 of the 2 nd compressor housing 15. A 4 th linear passage 9d of the compressed fluid passage 9, which will be described later, is connected to the 2 nd suction port 15 a.

The 2 nd discharge port 15b extends in the radial direction of the 2 nd compressor housing 15 inside the 2 nd compressor housing 15, and opens at the outer peripheral surface 151 of the 2 nd compressor housing 15. A discharge pipe 39 is connected to the 2 nd discharge port 15 b. The turbine fluid machine is connected to the fuel cell stack via the discharge pipe 39.

Further, a 2 nd impeller chamber 29a, a 2 nd discharge chamber 29b, and a 2 nd diffusion flow path 29c are formed between the 2 nd compressor housing 15 and the 3 rd rear surface 13 b. The 2 nd impeller chamber 29a communicates with the 2 nd suction port 15 a. The 2 nd discharge chamber 29b extends around the axis of the 2 nd suction port 15a around the 2 nd impeller chamber 29 a. The 2 nd discharge chamber 29b communicates with the 2 nd discharge port 15 b. The 2 nd diffusion channel 29c communicates the 2 nd impeller chamber 29a with the 2 nd discharge chamber 29 b. Thus, the 2 nd impeller chamber 29a communicates with the 2 nd discharge port 15b through the 2 nd diffusion channel 29c and the 2 nd discharge chamber 29 b.

In this way, in the casing 1, the 1 st impeller chamber 27a and the 2 nd impeller chamber 29a are separated in the front-rear direction, and the motor chamber 30 is disposed between the 1 st impeller chamber 27a and the 2 nd impeller chamber 29 a. The 1 st impeller chamber 27a and the 2 nd impeller chamber 29a are collectively referred to as impeller chambers.

The electric motor 3 is accommodated in the motor chamber 30. The electric motor 3 has a stator 3a and a rotor 3b. The stator 3a is formed in a cylindrical shape extending in the front-rear direction, and is fixed to the inner peripheral surface of the peripheral wall 10 b. The stator 3a is connected to a power supply device (not shown) provided outside the casing 1. The rotor 3b is formed in a cylindrical shape having a diameter smaller than that of the stator 3a and extending in the front-rear direction. The rotor 3b is disposed in the stator 3 a.

The drive shaft 5 is formed in a cylindrical shape extending in the axial direction, i.e., in the front-rear direction, and includes, in order from the front toward the rear, a 1 st shaft portion 5a, a 2 nd shaft portion 5b, a 3 rd shaft portion 5c, a 4 th shaft portion 5d, and a 5 th shaft portion 5e. The 1 st shaft portion 5a and the 5 th shaft portion 5e are formed to have the same diameter, and the diameter is smallest in the drive shaft 5. The 2 nd and 4 th shaft portions 5b and 5d are formed to have the same diameter, and are formed to have diameters larger than those of the 1 st and 5 th shaft portions 5a and 5e. The 2 nd shaft portion 5b is connected to the 1 st shaft portion 5a at the tip end. The 4 th shaft portion 5d is connected at the rear end to the 5 th shaft portion 5e. The 3 rd shaft portion 5c is formed to have the largest diameter in the drive shaft 5. The 3 rd shaft portion 5c is connected to the 2 nd shaft portion 5b at the front end and to the 4 th shaft portion 5d at the rear end.

The drive shaft 5 is inserted into the housing 1 and is rotatable about a drive axis O. In addition, in the drive shaft 5, the 1 st shaft portion 5a extends into the 1 st impeller chamber 27 a. The drive shaft center O extends parallel to the front-rear direction of the turbine fluid machine.

The 2 nd shaft portion 5b is inserted into the 3 rd shaft hole 12d and the 1 st shaft hole 11e, and extends into the 2 nd recess 12c and the 1 st recess 11 d. The 2 nd shaft portion 5b is inserted into the 1 st seal member 25a in the 2 nd recess portion 12 c. Thereby, the 1 st seal member 25a seals between the 1 st impeller chamber 27a, the 1 st recess 11d, and the motor chamber 30. The 2 nd shaft portion 5b is inserted into the 1 st recess 11d, and is press-fitted into the support plate 51 in addition to the 1 st and 2 nd thrust bearings 23a and 23b. The support plate 51 is located between the 1 st thrust bearing 23a and the 2 nd thrust bearing 23b. Thereby, the support plate 51 sandwiches the 1 st thrust bearing 23a in the front-rear direction with the 2 nd rear surface 12b, and sandwiches the 2 nd thrust bearing 23b in the front-rear direction with the wall surface of the 1 st concave portion 11 d.

The 3 rd shaft portion 5c extends into the motor chamber 30, is inserted into the rotor 3b, and is fixed to the rotor 3b. The 3 rd shaft portion 5c is supported by the 1 st radial bearing 21a in the 1 st boss portion 11c, and is supported by the 2 nd radial bearing 21b in the 2 nd boss portion 10 d.

The 4 th shaft portion 5d is inserted through the 4 th shaft hole 13d, and extends to the 3 rd recess 13c. The 4 nd shaft portion 5d is inserted into the 2 nd seal member 25b in the 3 rd recess portion 13c. Thereby, the 2 nd seal member 25b seals between the 2 nd impeller chamber 29a and the motor chamber 30. And, the 5 th shaft portion 5e extends into the 2 nd impeller chamber 29 a.

The 1 st impeller 7 is accommodated in the 1 st impeller chamber 27 a. The 1 st impeller 7 is formed in a substantially conical shape having a diameter gradually expanding (diameter expanding) from the front toward the rear. On the other hand, the 2 nd impeller 8 is housed in the 2 nd impeller chamber 29 a. The 2 nd impeller 8 and the 1 st impeller 7 have a symmetrical shape in the front-rear direction. That is, the 2 nd impeller 8 is formed in a substantially conical shape in which the diameter gradually decreases (diameter narrows) from the front toward the rear. The 1 st impeller 7 is made of aluminum alloy, and the 2 nd impeller 8 is made of steel.

The 1 st impeller 7 is fixed to the 1 st shaft portion 5a of the drive shaft 5. The 2 nd impeller 8 is fixed to the 5 th shaft portion 5e of the drive shaft 5. In this way, the drive shaft 5 connects the 1 st and 2 nd impellers 7, 8 to the electric motor 3.

The compressed fluid passage 9 is formed separately from the housing 1 and is provided outside the housing 1. The compression fluid passage 9 has a 1 st straight passage 9a, a 2 nd straight passage 9b, a 3 rd straight passage 9c, a 4 th straight passage 9d, a 1 st corner passage 9e, a 2 nd corner passage 9f, and a 3 rd corner passage 9g. The 1 st to 4 th straight passages 9a to 9d and the 1 st to 3 rd corner passages 9e to 9g, that is, the compressed fluid passage 9, are formed of cylindrical metal pipes, and can be circulated with the 1 st compressed air therein. Further, details of the 1 st compressed air will be described later.

The 1 st to 4 th linear passages 9a to 9d can allow the 1 st compressed air to flow in the longitudinal direction and extend linearly in the longitudinal direction. As shown in fig. 2 and 3, the length of the inner diameter of the 3 rd linear passage 9c is 1 st length L1. Regarding the 1 st, 2 nd, 4 th straight passages 9a, 9b, 9d shown in fig. 1, the length of the inner diameter is also set to the 1 st length L1. The 1 st to 3 rd corner passages 9e to 9g are bent substantially at right angles. The 1 st to 3 rd corner passages 9e to 9g are formed to have an inner diameter larger than that of the 1 st to 4 th straight passages 9a to 9d, and are internally insertable through the 1 st to 4 th straight passages 9a to 9 d.

In the compressed fluid passage 9, a 1 st straight passage 9a, a 1 st corner passage 9e, a 2 nd straight passage 9b, a 2 nd corner passage 9f, a 3 rd straight passage 9c, a 3 rd corner passage 9g, and a 4 th straight passage 9d are arranged in this order in the flow direction of the 1 st compressed air described later. In the compressed fluid passage 9, one end of the 1 st straight passage 9a is connected to the 1 st discharge port 14b. The other end of the 1 st straight passage 9a is connected to one end of the 2 nd straight passage 9b by the 1 st corner passage 9 e. The other end side of the 2 nd straight passage 9b is connected to one end side of the 3 rd straight passage 9c by the 2 nd corner passage 9 f. The 3 rd corner passage 9g connects the other end of the 3 rd linear passage 9c to one end of the 4 th linear passage 9 d. The other end of the 4 th linear passage 9d is connected to the 2 nd suction port 15a. In this way, the compressed fluid passage 9 connects the 1 st discharge port 14b and the 2 nd suction port 15a. The 1 st to 4 th straight passages 9a to 9d constitute straight portions in the compressed fluid passage 9, and the 1 st to 3 rd corner passages 9e to 9g constitute corner portions in the compressed fluid passage 9.

Here, in the compressed fluid passage 9, the distance from the 3 rd linear passage 9c to the 2 nd suction port 15a is shorter than the distance from the 1 st discharge port 14b to the 3 rd linear passage 9 c. That is, in the compressed fluid passage 9, the 3 rd linear passage 9c is disposed closer to the 2 nd suction port 15a than to the 1 st discharge port 14b, that is, closer to the 2 nd impeller chamber 29a than to the 1 st impeller chamber 27 a. In addition, the shape of the compressed fluid passage 9 can be appropriately designed.

As shown in fig. 1 to 3, the 1 st whole flow paths 31a to 31g are provided inside the 3 rd straight path 9 c. Thus, the 1 st flow path 31a to 31g is disposed in the compressed fluid passage 9 at a position closer to the 2 nd impeller chamber 29a than to the 1 st impeller chamber 27 a.

As shown in fig. 2 and 3, the 1 st whole flow paths 31a to 31g are all identical in structure and are formed of a metal cylindrical body extending in a straight line parallel to the longitudinal direction of the 3 rd straight path 9 c. More specifically, the 1 st whole flow paths 31a to 31g are formed of metal pipes for public use. Accordingly, the 1 st compressed air can flow through the 1 st whole flow paths 31a to 31 g. The 1 st whole flow paths 31a to 31g are formed to have a length direction shorter than that of the 3 rd straight path 9 c. If the number of the 1 st whole flow paths 31a to 31g is plural, the number thereof can be appropriately designed. The 1 st whole flow paths 31a to 31g may be formed of a resin cylinder.

The length of each inner diameter of the 1 st whole flow paths 31a to 31g is set to the 2 nd length L2. Here, the 2 nd length L2 is shorter than the 1 st length L1 which is the length of the inner diameter of the compressed fluid passage 9. More specifically, the 2 nd length L2 is a length shorter than one third of the 1 st length L1. Thus, as shown in fig. 4 (B), the 2 nd passage cross-sectional area S2, which is the passage cross-sectional area of each of the 1 st whole passages 31a to 31g, is smaller than the 1 st passage cross-sectional area S1, which is the passage cross-sectional area of the 3 rd linear passage 9c shown in fig. 4 (a). The sum of the 7 2 nd channel cross-sectional areas S2 corresponding to the number of 1 st whole channels 31a to 31g is also smaller than the 1 st channel cross-sectional area S1.

As shown in fig. 3, the 1 st whole flow paths 31a to 31g are bonded to each other in a state where the 1 st whole flow path 31a is located at the center portion of the compressed fluid passage 9 and the other 1 st whole flow paths 31b to 31g are aligned in the circumferential direction of the 1 st whole flow path 31 a. The 1 st whole flow passages 31a to 31g are inserted into the 3 rd linear passage 9c in this state, and are bonded and fixed to the inner peripheral surface 901 of the 3 rd linear passage 9 c. Thus, the 1 st whole flow paths 31a to 31g are provided inside the 3 rd straight path 9 c.

In the turbo fluid machine having the above-described structure, the electric motor 3 shown in fig. 1 is supplied with power from the power supply device, so that the electric motor 3 operates, and the drive shaft 5 rotates around the drive shaft center O. Thus, the 1 st impeller 7 rotates around the drive axis O in the 1 st impeller chamber 27a, and the 2 nd impeller 8 rotates around the drive axis O in the 2 nd impeller chamber 29 a. In this way, in the turbo fluid machine, the air sucked from the 1 st suction port 14a is compressed in 2 stages by the 1 st impeller 7 and the 2 nd impeller 8.

Specifically, the 1 st impeller 7 compresses the air sucked into the 1 st impeller chamber 27a from the 1 st suction port 14a to become 1 st compressed air, and circulates the 1 st compressed air from the 1 st impeller chamber 27a toward the 1 st discharge chamber 27 b. That is, the 1 st compressed air is higher in pressure than the air sucked from the 1 st suction port 14a into the 1 st impeller chamber 27 a.

The 1 st compressed air is discharged from the 1 st discharge port 14b into the compressed fluid passage 9, flows through the 1 st straight passage 9a, the 1 st corner passage 9e, the 2 nd straight passage 9b, the 2 nd corner passage 9f, the 3 rd straight passage 9c, the 1 st whole flow passages 31a to 31g, the 3 rd corner passage 9g, and the 4 th straight passage 9d in this order, and is supplied from the 2 nd suction port 15a into the 2 nd impeller chamber 29 a.

The 2 nd impeller 8 compresses the 1 st compressed air supplied into the 2 nd impeller chamber 29a to become the 2 nd compressed air having a higher pressure than the 1 st compressed air, and circulates the 2 nd compressed air from the 2 nd impeller chamber 29a to the 2 nd discharge chamber 29 b. In this way, the 2 nd compressed air is discharged from the 2 nd discharge port 15b into the discharge pipe 39, and is supplied to the cathode of the fuel cell stack through the discharge pipe 39.

In the turbine-type fluid machine, the 1 st compressed air and the 2 nd compressed air are respectively given a rotational component by the 1 st impeller 7 and the 2 nd impeller 8 rotating around the drive axis O. In the turbo fluid machine, the 1 st compressed air flowing through the compressed fluid passage 9 can be rectified and supplied into the 2 nd impeller chamber 29a through the 1 st rectification passages 31a to 31 g.

That is, as indicated by the broken-line arrows in fig. 2, the 1 st compressed air discharged from the 1 st discharge port 14b reaches the 1 st whole flow paths 31a to 31g through the 1 st straight path 9a, the 1 st corner path 9e, the 2 nd straight path 9b, the 2 nd corner path 9f, and the 3 rd straight path 9c in a state having a large number of rotation components. The 1 st compressed air reaching the 1 st whole flow paths 31a to 31g flows through the inside of each 1 st whole flow path 31a to 31g. The length of each inner diameter of the 1 st whole flow paths 31a to 31g is set to be the 2 nd length L2, and is shorter than the 1 st length L1 which is the length of the inner diameter of the 3 rd linear path 9 c. Therefore, the 1 st whole flow paths 31a to 31g have a smaller diameter than the 3 rd straight path 9c, and the 2 nd path cross-sectional area S2 is smaller than the 1 st path cross-sectional area S1. That is, the inside of the 1 st whole flow paths 31a to 31g is narrower than the inside of the 3 rd straight path 9 c.

Accordingly, the 1 st compressed air flowing through the 1 st flow passages 31a to 31g is gradually rectified in this process, and the rotational component of the 1 st compressed air is reduced. As a result, the 1 st compressed air passing through the 1 st flow-through passages 31a to 31g flows through the 3 rd corner passage 9g and the 4 th straight passage 9d in a state in which the rotational component is reduced as compared with before reaching the 1 st flow-through passages 31a to 31g. Accordingly, the 1 st compressed air is supplied from the 2 nd suction port 15a into the 2 nd impeller chamber 29a in a state in which the rotational component is reduced as compared with the state in which the compressed air is discharged to the 1 st discharge port 14 b.

In this way, in the turbine fluid machine, when the 1 st compressed air is compressed by the 2 nd impeller 8 to be the 2 nd compressed air, the pressure of the 2 nd compressed air can be sufficiently increased. In this way, in the turbine type fluid machine, the 2 nd compressed air having a high pressure can be supplied to the cathode of the fuel cell stack. In addition, strictly speaking, since a gap exists between the 1 st whole flow paths 31a to 31g and the 3 rd straight path 9c, a part of the 1 st compressed air flows through the gap. The 1 st compressed air flowing through the gap is supplied into the 2 nd impeller chamber 29a together with the 1 st compressed air flowing through the 1 st whole flow paths 31a to 31g, and compressed by the 2 nd impeller 8.

Here, the 1 st whole flow paths 31a to 31g are formed of cylindrical bodies having a 2 nd passage cross-sectional area S2 smaller than the 1 st passage cross-sectional area S1 and extending in a straight line, more specifically, pipes of public products. The sum of the 7 2 nd passage cross-sectional areas S2 corresponding to the number of 1 st whole passages 31a to 31g is smaller than the 1 st passage cross-sectional area S1. In this turbine type fluid machine, the 1 st compressed air can be properly rectified while the 1 st compressed air is flowing through the 1 st flow passages 31a to 31g, while the 1 st flow passages 31a to 31g are simplified in structure and reduced in size and cost. In this turbo type fluid machine, the 1 st flow path 31a to 31g can be provided inside the compressed fluid passage 9, and the 3 rd linear passage 9c can be suppressed, and further, the size of the compressed fluid passage 9 can be suppressed from being increased.

Therefore, the turbo type fluid machine of example 1 can exhibit high compression performance, and can be miniaturized and manufactured at low cost.

In particular, the 1 st whole flow paths 31a to 31g are disposed in the 3 rd linear path 9c, and thus are disposed closer to the 2 nd impeller chamber 29a than to the 1 st impeller chamber 27 a. Therefore, the turbine type fluid machine can reduce the pressure loss of the 1 st compressed air as much as possible during the period from the 2 nd suction port 15a to the 2 nd impeller chamber 29a after passing through the 1 st flow-through passages 31a to 31 g.

Further, since the 1 st whole flow paths 31a to 31g are formed of a cylindrical body, for example, the 1 st compressed air can appropriately flow through the inside of the 1 st whole flow paths as compared with the case where the 1 st whole flow paths 31a to 31g are formed of rectangular cylindrical bodies. Therefore, the pressure loss of the 1 st compressed air during the internal circulation of the 1 st whole flow paths 31a to 31g can be reduced.

Example 2

In the turbo type fluid machine of example 2, the 1 st impeller 7 and the 2 nd impeller 8 (see fig. 1) are both made of an aluminum alloy. As shown in fig. 5 and 6, the turbine-type fluid machine is provided with 7 2 nd rectifying passages 33a to 33g inside the 3 rd linear passage 9 c. The 2 nd flow path 33a to 33g are also an example of the "flow path" in the present invention.

The 2 nd whole flow paths 33a to 33g are all identical in structure. As shown in fig. 5, the 2 nd rectifying passages 33a to 33g are also formed of a metal cylindrical body extending in a straight line parallel to the longitudinal direction of the 3 rd straight passage 9 c. More specifically, the 2 nd rectifying passages 33a to 33g are also formed of metal pipes of common products. Accordingly, the 1 st compressed air can flow through the 2 nd flow-straightening passages 33a to 33 g. The number of the 2 nd rectifying circuits 33a to 33g can be appropriately designed if a plurality of the 2 nd rectifying circuits are provided. The 2 nd flow-through passages 33a to 33g may be formed by a resin cylinder.

Here, the length of each inner diameter of the 2 nd rectifying paths 33a to 33g is set to the 3 rd length L3. The 3 rd length L3 is shorter than the 2 nd length L2 which is the length of each inner diameter of the 1 st whole flow paths 31a to 31g in example 1. Therefore, as shown in fig. 7 (B), the 3 rd passage cross-sectional area S3, which is the passage cross-sectional area of each of the 2 nd flow-through passages 33a to 33g, is smaller than the 1 st passage cross-sectional area S1, which is the passage cross-sectional area of the 3 rd linear passage 9c shown in fig. 7 (a). The sum of the 7 3 rd channel cross-sectional areas S3 corresponding to the number of 2 nd rectifying channels 33a to 33g is also smaller than the 1 st channel cross-sectional area S1. Other structures of the 2 nd flow channels 33a to 33g are the same as those of the 1 st flow channels 31a to 31 g. The mounting of the 2 nd rectifying circuits 33a to 33g to the 3 rd straight passage 9c will be described later.

As shown in fig. 5, in the turbine-type fluid machine, a cooling portion 41 is provided in the compressed fluid passage 9. The cooling unit 41 includes a 1 st connection port 41a, a 2 nd connection port 41b, a supply pipe 41c, a return pipe 41d, a pump 41e, a 1 st partition wall 41f, a 2 nd partition wall 41g, and a cooling chamber 41h.

The 1 st connection port 41a and the 2 nd connection port 41b are formed in the 3 rd linear passage 9c in a state of being separated from each other. More specifically, the 1 st connection port 41a and the 2 nd connection port 41b are formed in the 3 rd linear passage 9c at the positions where the 2 nd whole flow passages 33a to 33g are provided. The 1 st connection port 41a is formed at a position downstream of the 2 nd connection port 41b in the flow direction of the 1 st compressed air. The 1 st connection port 41a and the 2 nd connection port 41b radially penetrate the 3 rd linear passage 9c, and communicate the inside of the 3 rd linear passage 9c with the outside.

One end of the supply pipe 41c is connected to the 1 st connection port 41a, and the other end is connected to a radiator (not shown) of the vehicle. The other end of the return pipe 41d is connected to the 2 nd connection port 41b, and one end is connected to the radiator. The supply pipe 41c and the return pipe 41d can supply water and circulate a coolant 43 (see fig. 8) such as a long-acting coolant therein. A pump 41e shown in fig. 5 is provided in the supply pipe 41c, and circulates the cooling liquid 43 between the cooling chamber 41h and the radiator through the supply pipe 41c and the return pipe 41d. The pump 41e may be provided in the return pipe 41d.

The 1 st partition wall 41f and the 2 nd partition wall 41g are identical in structure and made of a resin such as synthetic rubber. Hereinafter, the 1 st partition wall 41f will be described. As shown in fig. 6, the 1 st partition wall 41f is formed in a disk shape having a 1 st length L1, the length of which is equal to the length of the inner diameter of the 3 rd linear passage 9 c. In addition, 7 mounting holes 411 to 417 are provided through the 1 st partition wall 41 f. The 1 st partition wall 41f and the 2 nd partition wall 41g may be made of metal.

As shown in fig. 5, the 1 st partition wall 41f and the 2 nd partition wall 41g are separated from each other in the flow direction of the 1 st compressed air and are provided inside the 3 rd linear passage 9 c. More specifically, the 1 st partition wall 41f is provided in the 3 rd linear passage 9c at a position upstream of the 2 nd connection port 41b in the 1 st compressed air flow direction. On the other hand, the 2 nd partition wall 41g is provided in the 3 rd linear passage 9c at a position downstream of the 1 st connection port 41a in the flow direction of the 1 st compressed air. The 1 st partition wall 41f and the 2 nd partition wall 41g are adhered to the inner peripheral surface 901 of the 3 rd linear passage 9 c. Thus, the 1 st partition wall 41f and the 2 nd partition wall 41g partition the inside of the 3 rd linear passage 9 c.

The cooling chamber 41h is formed between the 1 st partition wall 41f, the 2 nd partition wall 41g, and the inner peripheral surface 901 in the 3 rd linear passage 9 c. The cooling chamber 41h is sealed between the inside and the outside by the 1 st partition wall 41f and the 2 nd partition wall 41 g. The cooling chamber 41h is connected to a supply pipe 41c through a 1 st connection port 41a, and is connected to a return pipe 41d through a 2 nd connection port 41 b.

The 2 nd flow-through passages 33a to 33g are respectively inserted into the mounting holes 411 to 417 of the 1 st partition wall 41f and the 2 nd partition wall 41g. Specifically, as shown in fig. 6, the 2 nd rectifying passage 33a is inserted into the mounting hole 411, the 2 nd rectifying passage 33b is inserted into the mounting hole 412, the 2 nd rectifying passage 33c is inserted into the mounting hole 413, the 2 nd rectifying passage 33d is inserted into the mounting hole 414, the 2 nd rectifying passage 33e is inserted into the mounting hole 415, the 2 nd rectifying passage 33f is inserted into the mounting hole 416, and the 2 nd rectifying passage 33g is inserted into the mounting hole 417. Thus, the 2 nd rectifying passages 33a to 33g are arranged in a state where the 2 nd rectifying passage 33a is located at the center portion of the 3 rd linear passage 9c and the other 2 nd rectifying passages 33b to 33g are arranged in the circumferential direction of the 2 nd rectifying passage 33a, and are fixed to the 1 st partition wall 41f and the 2 nd partition wall 41g.

Thus, the 2 nd flow-through passages 33a to 33g are fixed to the 1 st partition wall 41f and the 2 nd partition wall 41g, and are provided in the cooling chamber 41 h. Here, in the turbo type fluid machine, the interval between the 2 nd rectifying passages 33a to 33g and the inner peripheral surface 901 of the 3 rd linear passage 9c are respectively widened as compared with the turbo type fluid machine of example 1. Other components of the turbo type fluid machine are the same as those of the turbo type fluid machine of example 1, and the same reference numerals are given to the same components, and detailed description thereof is omitted.

In the turbine type fluid machine, the 1 st compressed air reaching the 2 nd flow passages 33a to 33g flows through the 2 nd flow passages 33a to 33 g. As a result, in the same manner as in the turbo type fluid machine of example 1, the 1 st compressed air is supplied from the 2 nd suction port 15a into the 2 nd impeller chamber 29a in a state in which the rotational component is reduced.

In the turbo type fluid machine, the pump 41e is operated, so that the cooling liquid 43 flows into the cooling chamber 41h from the supply pipe 41c as shown in fig. 8. Accordingly, the cooling chamber 41h exchanges heat with the cooling liquid 43 through the 1 st compressed air flowing through the 2 nd rectifying passages 33a to 33 g. Thereby, the cooling unit 41 cools the 1 st compressed air flowing through the 2 nd rectification passages 33a to 33 g.

Here, in the cooling unit 41, the 1 st connection port 41a is provided at a position downstream of the 2 nd connection port 41b in the flow direction of the 1 st compressed air. Therefore, as shown by solid arrows in fig. 5, the coolant 43 flowing from the supply pipe 41c into the cooling chamber 41h flows toward the 2 nd connection port 41b and the return pipe 41d upstream in the flow direction of the 1 st compressed air in the cooling chamber 41 h. Therefore, the flow direction of the 1 st compressed air flowing through the 2 nd rectifying passages 33a to 33g is opposite to the flow direction of the cooling liquid 43 flowing through the cooling chamber 41 h. Accordingly, the 1 st compressed air flowing through the 2 nd rectification passages 33a to 33g and the cooling liquid 43 perform heat exchange appropriately, so that the cooling unit 41 can sufficiently cool the 1 st compressed air.

In this way, in the turbine type fluid machine, the 1 st compressed air can be cooled and supplied into the 2 nd impeller chamber 29a, and therefore, the 2 nd impeller 8 does not need to have excessively high heat resistance. Therefore, in this turbo type fluid machine, by making the 2 nd impeller 8 of aluminum alloy, the weight of the 2 nd impeller 8 can be reduced and the manufacturing cost can be reduced.

In addition, since the cooling of the 1 st compressed air by the cooling unit 41 can suppress the temperature rise of the 2 nd compressed air in the turbo fluid machine, it is not necessarily necessary to provide a cooling unit for cooling the 2 nd compressed air. In this turbo type fluid machine, the compressed fluid passage 9 can be prevented from being heated by the 1 st compressed air, and therefore, the case 1 can be prevented from being heated by the heat of the compressed fluid passage 9. The other functions of the turbo type fluid machine are the same as those of the turbo type fluid machine of example 1.

Example 3

As shown in fig. 9, in the turbo type fluid machine of example 3, 4 3 rd whole flow passages 35a to 35d are provided in the 3 rd linear passage 9 c. The 3 rd flow channels 35a to 35d are also examples of "flow channels" in the present invention. In the turbo fluid machine, a partition plate 45 is provided in the 3 rd linear passage 9 c.

The partition plate 45 is made of metal, extends in a cross shape in the radial direction of the 3 rd linear passage 9c, and extends linearly in the longitudinal direction in parallel with the 3 rd linear passage 9 c. Here, the length of the partition plate 45 in the radial direction of the 3 rd linear passage 9c is equal to the 1 st length L1 which is the length of the inner diameter of the 3 rd linear passage 9 c. Although not shown, the length of the partition plate 45 in the longitudinal direction is the same as that of the 1 st whole flow paths 31a to 31 g. In addition, the shape of the partition plate 45 can be appropriately designed. The partition plate 45 may be made of resin.

Then, the 3 rd whole flow passages 35a to 35d are defined in the inner region of the 3 rd linear passage 9c by the partition plate 45. Here, the partition plate 45 extends linearly in the longitudinal direction parallel to the 3 rd linear passage 9c, and therefore, also in the 3 rd whole flow passages 35a to 35d, extends linearly in the longitudinal direction parallel to the 3 rd linear passage 9 c.

The cross-sectional shape of the 3 rd whole flow passages 35a to 35d in the direction orthogonal to the flow direction of the 1 st compressed air is a sector shape in which the 3 rd linear passage 9c is substantially divided into four equal parts. Thus, as shown in fig. 10 (B), the 4 th passage cross-sectional area S4, which is the passage cross-sectional area of each of the 3 rd whole passages 35a to 35d, is smaller than the 1 st passage cross-sectional area S1, which is the passage cross-sectional area of the 3 rd linear passage 9c shown in fig. 10 (a). The sum of the 4 th channel cross-sectional areas S4 corresponding to the number of 3 rd whole channels 35a to 35d is also smaller than the 1 st channel cross-sectional area S1. The other structure of the turbo type fluid machine is the same as that of the turbo type fluid machine of example 1.

In the turbine type fluid machine, the 1 st compressed air reaching the 3 rd flow passages 35a to 35d flows through the 3 rd flow passages 35a to 35 d. As a result, in the turbo fluid machine, the 1 st compressed air is supplied from the 2 nd suction port 15a into the 2 nd impeller chamber 29a in a state where the rotational component is reduced. In the turbo fluid machine, the 3 rd whole flow passages 35a to 35d can be easily provided in the 3 rd linear passage 9c by providing the partition plate 45 in the 3 rd linear passage 9c. Therefore, in the turbine fluid machine, the structure of the 3 rd flow passages 35a to 35d can be further simplified. The other functions of the turbo type fluid machine are the same as those of the turbo type fluid machine of example 1.

The present invention has been described above with reference to examples 1 to 3, but the present invention is not limited to examples 1 to 3, and can be applied to any suitable modification within the scope of the present invention.

For example, in the turbo fluid machine of example 1, the 1 st flow-through passages 31a to 31g are provided in the 3 rd linear passage 9c of the compressed fluid passage 9, but the present invention is not limited thereto, and the 1 st flow-through passages 31a to 31g may be provided in the 1 st linear passage 9a, the 4 th linear passage 9d, or the like. The same applies to the turbo type fluid machines of examples 2 and 3.

In the turbo type fluid machine of example 1, the 1 st whole flow paths 31a to 31g may be provided to a plurality of portions of the compressed fluid passage 9. The same applies to the turbo type fluid machines of examples 2 and 3.

In the turbo type fluid machine of examples 1 to 3, the compressed fluid passage 9 may be integrally formed in the casing 1.

In the turbo type fluid machine of examples 1 to 3, the "fluid" in the present invention is air, but the present invention is not limited thereto, and the refrigerant or the like used for the air conditioner may be the "fluid" in the present invention.

[ INDUSTRIAL APPLICABILITY ]

The present invention can be used for fuel cell systems, air conditioning systems, and the like.

Claims

1. A turbine type fluid machine is provided with:

a housing formed with an impeller chamber and a motor chamber;

an electric motor accommodated in the motor chamber;

the impeller chamber having a 1 st impeller chamber and a 2 nd impeller chamber, the 2 nd impeller chamber being separated with respect to the 1 st impeller chamber in an axial direction of the drive shaft,

The impeller includes a 1 st impeller accommodated in the 1 st impeller chamber and compressing the fluid to obtain a 1 st compressed fluid, and a 2 nd impeller accommodated in the 2 nd impeller chamber and compressing the 1 st compressed fluid to obtain a 2 nd compressed fluid,

the turbine type fluid machine is characterized in that,

the turbine type fluid machine further includes:

2. The turbomachinery of claim 1, wherein the turbine engine further comprises a turbine engine,

each of the rectification paths is disposed closer to the 2 nd impeller chamber than to the 1 st impeller chamber.

3. A turbomachine according to claim 1 or 2, wherein,

each of the rectification routes is formed of a cylindrical body extending linearly.

4. A turbomachine according to any one of claims 1 to 3, wherein,

the compressed fluid passage is provided with a cooling unit that cools the 1 st compressed fluid flowing through each of the rectifying passages.