Centrifugal turbo-compressor having a gas flow path including a relaxation chamber

Abstract

The centrifugal turbo-compressor (2) includes a hermetic casing (3); a drive shaft (6) having a longitudinal axis and rotatably arranged within the hermetic casing (3); a compression stage including an impeller (17) connected to the drive shaft (6); a gas suction inlet (42); and a gas flow path (P) fluidly connected to the gas suction inlet (42) and configured to supply the compression stage with a gas flow. The gas flow path (P) includes a relaxation chamber (46) at least partially surrounding the drive shaft (6), the gas suction inlet (42) emerging substantially radially into the relaxation chamber (46); and a plurality of inlet flow guide channels (51) fluidly connected to the relaxation chamber (46) and angularly distributed around the longitudinal axis of the drive shaft (6), the inlet flow guide channels (51) extending radially towards the drive shaft (6) and being axially offset from the gas suction inlet (42) and the relaxation chamber (46).

Claims

1. A centrifugal turbo-compressor including: a hermetic casing, a drive shaft having a longitudinal axis (A) and rotatably arranged within the hermetic casing, a compression stage including an impeller connected to the drive shaft, a gas suction inlet, a gas flow path (P) fluidly connected to the gas suction inlet and configured to supply the compression stage with a gas flow, wherein the gas flow path (P) includes: a relaxation chamber at least partially surrounding the drive shaft, the gas suction inlet emerging substantially radially into the relaxation chamber, and a plurality of inlet flow guide channels fluidly connected to the relaxation chamber and angularly distributed around the longitudinal axis (A) of the drive shaft, the plurality of inlet flow guide channels extending radially towards the drive shaft and being axially offset from the gas suction inlet and the relaxation chamber, wherein the gas suction inlet and the relaxation chamber are configured with respect to the following equation: OD.sup.2−ID.sup.2>2*D1, where: OD is an outer diameter of the relaxation chamber taken in a radial direction to the longitudinal axis (A); ID is an inner diameter of the relaxation chamber taken in the radial direction to the longitudinal axis (A); and D1 is an inlet diameter of the gas suction inlet taken in an axial direction along the longitudinal axis (A).

2. The centrifugal turbo-compressor according to claim 1, wherein the relaxation chamber extends around the drive shaft along an angular sector less than 360°.

3. The centrifugal turbo-compressor according to claim 2, further including a separating wall part located opposite the gas suction inlet and configured such that the relaxation chamber includes a first arcuate chamber part extending from the gas suction inlet to the separating wall part along a first angular direction with respect to the longitudinal axis (A) of the drive shaft and a second arcuate chamber part extending from the gas suction inlet to the separating wall part along a second angular direction with respect to the longitudinal axis (A) of the drive shaft which is opposite of the first angular direction.

4. The centrifugal turbo-compressor according to claim 1, wherein the relaxation chamber has a horseshoe-shaped cross sectional profile.

5. The centrifugal turbo-compressor according to claim 1, wherein an axial length (L) of the relaxation chamber is greater than an inlet diameter (D1) of the gas suction inlet.

6. The centrifugal turbo-compressor according to claim 1, wherein the gas flow path (P) further includes a connecting channel extending around the drive shaft and fluidly connecting the relaxation chamber with the plurality of inlet flow guide channels.

7. The centrifugal turbo-compressor according to claim 6, wherein the connecting channel emerges into the relaxation chamber at an outer radial portion of the relaxation chamber so as to define a flow restriction for the gas flow.

8. The centrifugal turbo-compressor according to claim 6, wherein the connecting channel is annular.

9. The centrifugal turbo-compressor according to claim 1, further including inlet flow guide members at least partially defining the plurality of inlet flow guide channels, the inlet flow guide members being angularly distributed around the longitudinal axis (A) of the drive shaft.

10. The centrifugal turbo-compressor according to claim 9, wherein each of the inlet flow guide members extends radially towards the drive shaft and converges towards the drive shaft.

11. The centrifugal turbo-compressor according to claim 1, further including an inlet distributor having an annular disc shape and surrounding the drive shaft, the plurality of inlet flow guide channels being at least partially defined by the inlet distributor.

12. The centrifugal turbo-compressor according to claim 1, wherein the gas flow path (P) further includes an annular supplying channel extending around the drive shaft and being fluidly connected to the plurality of inlet flow guide channels, the annular supplying channel being configured to axially supply the compression stage with the gas flow.

13. The centrifugal turbo-compressor according to claim 1, wherein the gas suction inlet includes a gas inlet part having a circular cross section, and a gas outlet part including a gas outlet emerging into the relaxation chamber, the gas outlet part diverging towards the relaxation chamber.

14. The centrifugal turbo-compressor according to claim 2, wherein the relaxation chamber has a horseshoe-shaped cross sectional profile.

15. The centrifugal turbo-compressor according to claim 2, wherein an axial length (L) of the relaxation chamber is greater than an inlet diameter (D1) of the gas suction inlet.

16. The centrifugal turbo-compressor according to claim 3, wherein an axial length (L) of the relaxation chamber is greater than an inlet diameter (D1) of the gas suction inlet.

17. The centrifugal turbo-compressor according to claim 4, wherein an axial length (L) of the relaxation chamber is greater than an inlet diameter (D1) of the gas suction inlet.

18. The centrifugal turbo-compressor according to claim 6, further including inlet flow guide members at least partially defining the plurality of inlet flow guide channels, the inlet flow guide members being angularly distributed around the longitudinal axis (A), wherein the connecting channel is configured with respect to the following equation: π*H*Di<π/4*(Do.sup.2−Di.sup.2), where: H is a height of each inlet flow guide member of the inlet flow guide members taken in an axial direction along the longitudinal axis (A); Di is an inner diameter of the connecting channel taken in the radial direction to the longitudinal axis (A); and Do is an outer diameter of the connecting channel taken in the radial direction to the longitudinal axis (A).

19. The centrifugal turbo-compressor according to claim 11, wherein the inlet distributor is slidably arranged in the axial direction along the longitudinal axis (A).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The following detailed description of one embodiment of the invention is better understood when read in conjunction with the appended drawings being understood, however, that the invention is not limited to the specific embodiment disclosed.

(2) FIG. 1 is a perspective view, partially in section, of a centrifugal turbo-compressor according to a first embodiment of the invention.

(3) FIG. 2 is an exploded perspective view of the centrifugal turbo-compressor of FIG. 1.

(4) FIG. 3 is a longitudinal section view of the centrifugal turbo-compressor of FIG. 1.

(5) FIG. 4 is a longitudinal section view of a gas flow path of the centrifugal turbo-compressor of FIG. 1.

(6) FIGS. 5 and 6 are cross section views of the centrifugal turbo-compressor of FIG. 1.

(7) FIG. 7 is a longitudinal section view of a centrifugal turbo-compressor according to a second embodiment of the invention.

DETAILED DESCRIPTION

(8) FIGS. 1 to 6 represent a hermetic centrifugal turbo-compressor 2, and particularly a double-stage hermetic centrifugal turbo-compressor, according to a first embodiment of the invention.

(9) The centrifugal turbo-compressor 2 includes a hermetic casing 3 including an impeller casing portion 3.1, a bearing casing portion 3.2 and a motor casing portion 3.3. As better shown on FIG. 3, the impeller casing portion 3.1 and the bearing casing portion 3.2 respectively include a cylindrical impeller housing 4 and a cylindrical bearing housing 5 which extend coaxially. The impeller casing portion 3.1 and the bearing casing portion 3.2 are secured to each other, for example by screwing or welding.

(10) The centrifugal turbo-compressor 2 also includes a drive shaft 6 rotatably arranged within the hermetic casing 3 and extending along a longitudinal axis A. The drive shaft 6 includes a first axial end portion 7, a second axial end portion 8 opposite to the first axial end portion 7, and an intermediate portion 9 arranged between the first and second end axial portions 7, 8.

(11) The centrifugal turbo-compressor 2 further includes a first compression stage 11 and a second compression stage 12 arranged in the cylindrical impeller housing 4 and configured to compress a gas, and for example a refrigerant. The first compression stage 11 includes a fluid inlet 13 and a fluid outlet 14, while the second compression stage 12 includes a fluid inlet 15 and a fluid outlet 16, the fluid outlet 14 of the first compression stage 11 being fluidly connected to the fluid inlet 15 of the second compression stage 12.

(12) The first and second compression stages 11, 12 respectively include an impeller 17 and an additional impeller 18 which are connected to the first axial end portion 7 of the drive shaft 6 and which extend coaxially with the drive shaft 6. The impeller 17 includes a front-side equipped with a plurality of blades 19 configured to accelerate, during rotation of the drive shaft 6, the gas entering the first compression stage 11, while the additional impeller 18 includes a front-side equipped with a plurality of blades 21 configured to accelerate, during rotation of the drive shaft 6, the gas entering the second compression stage 12. Further each of the impeller 17 and the additional impeller 18 includes a back-side extending substantially perpendicularly to the drive shaft 6.

(13) The impeller and additional impellers 17, 18 are arranged in a back-to-back configuration, so that the directions of fluid flow at the flow inlets 13, 15 of the first and second compression stages 11, 12 are opposite to each other.

(14) Further the first and second compression stage 11, 12 respectively includes a first aerodynamic member 22 and a second aerodynamic member 23 each having an annular disc shape. The first and second aerodynamic members 22, 23 respectively face the front-sides of the impeller 17 and the additional impeller 18. The outer diameters of the first and second aerodynamic members 22, 23 are substantially equal to the inner diameter of the cylindrical impeller housing 4. According to the embodiment shown on FIGS. 1 to 6, the first and second aerodynamic members 22, 23 are axially slidably arranged in the cylindrical impeller housing 4.

(15) The centrifugal turbo-compressor 2 also includes an electric motor 24 connected to the second axial end portion 8 of the drive shaft 6 and configured to drive in rotation the drive shaft 6 about the longitudinal axis A. The electric motor 24 is arranged in the motor casing portion 3.3.

(16) The centrifugal turbo-compressor 2 further includes an axial bearing arrangement, also named thrust bearing arrangement, arranged between the impeller 17 and the electrical motor 24 and configured to limit an axial movement of the drive shaft 6 during operation. The axial bearing arrangement may be a fluid axial bearing arrangement, and for example a gas axial bearing arrangement.

(17) According to the embodiment shown on FIGS. 1 to 6, the axial bearing arrangement includes an axial bearing member 25 arranged on an outer surface of the intermediate portion 9 of the drive shaft 6 and extending radially outwardly with respect to the drive shaft 6.

(18) The axial bearing arrangement also includes a first axial bearing plate 26 and a second axial bearing plate 27 each having an annular disc shape, and being arranged in parallel. The first axial bearing plate 26 faces towards the impeller 17, while the second axial bearing plate 27 faces towards the electrical motor 24.

(19) The axial bearing arrangement further includes a spacer ring 28 surrounding the axial bearing member 25, and being clamped between the first and second axial bearing plates 26, 27 at radial outer portions of the first and second axial bearing plates 26, 27. The spacer ring 28 particularly defines an axial distance between the first and second axial bearing plates 26, 27, said axial distance being slightly greater than the width of the axial bearing member 25.

(20) Advantageously, the centrifugal turbo-compressor 2 is configured so that gas is introduced between the axial bearing member 25, and the first and second axial bearing plates 26, 27 to form a gas axial bearing.

(21) The centrifugal turbo-compressor 2 also includes a radial bearing arrangement configured to rotatably support the drive shaft 6. The radial bearing arrangement includes a bearing sleeve 29, also named bearing housing, which extends around the drive shaft 6 and along the intermediate portion 9 of the drive shaft 6. The bearing sleeve 29 is at least partially arranged in the cylindrical bearing housing 5 and is located between the axial bearing arrangement and the electrical motor 24. The bearing sleeve 29 may be a one-piece bearing sleeve, or may be made from separated parts assembled together.

(22) According to the embodiment shown on FIGS. 1 to 6, the bearing sleeve 29 notably includes: a radial bearing part 31 which is tubular and which surrounds the intermediate portion 9 of the drive shaft 6, the radial bearing part 31 being configured to rotatably support the drive shaft 6, an outer sleeve part 32 surrounding the radial bearing part 31 and including an axial end face 33 facing towards the electrical motor 24 and abutting against an annular axial bearing surface 34 of the bearing casing portion 3.2, and an annular gap 35 formed between the radial bearing part 31 and the outer sleeve part 32 and facing towards the second axial bearing plate 27.

(23) The bearing sleeve 29 further includes an abutment surface 36 against which the second axial bearing plate 27 abuts. The abutment surface 36 is advantageously located at an axial end face of the outer sleeve part 32 facing towards the second axial bearing plate 27, and extends transversally, and advantageously perpendicularly, to the longitudinal axis A of the drive shaft 6. Therefore the bearing sleeve 29 is clamped between the second axial bearing plate 27 and the axial bearing surface 34 of the bearing casing portion 3.2.

(24) The centrifugal turbo-compressor 2 further includes an inlet distributor 37 arranged for example in the cylindrical bearing housing 5 and configured to supply, and for example to axially supply, the first compression stage 11, with gas. The inlet distributor 37 is adjacent to the first aerodynamic member 22, and has an annular disc shape and an outer diameter substantially equal to the inner diameter of the cylindrical bearing housing 5. The inlet distributor 37 is advantageously axially slidably arranged in the cylindrical bearing housing 5.

(25) The centrifugal compressor 2 may further include an elastic element arranged between the impeller casing portion 3.1 and the second aerodynamic member 23. Advantageously, the elastic element is an annular spring washer, for example of the Belleville type, coaxially arranged with the drive shaft 6. The elastic element is for example arranged in an annular recess formed in an axial surface of the impeller casing portion 3.1.

(26) According to an embodiment of the invention, the elastic element axially biases the first and second aerodynamic members 22, 23, an inter-stage sealing device 39 provided between the impeller 17 and the additional impeller 18, the inlet distributor 37 and the bearing sleeve 29 with a predetermined force, for example in the range of 8000 to 10000 N, against the annular axial bearing surface 34 of the bearing casing portion 3.2.

(27) The elastic element allows, notably when a thermal expansion occurs in the centrifugal turbo-compressor 2, an axial sliding of the first and second aerodynamic members 22, 23, the inter-stage sealing device 39, the inlet distributor 37 and the bearing sleeve 29 with respect to the hermetic casing 3, and thus avoids deformations of said parts which could lead to a shortened lifetime of the centrifugal turbo-compressor 2.

(28) The centrifugal turbo-compressor 2 may further includes one or several elastic member(s) axially biasing the first and second axial bearing plates 26, 27 and the spacer ring 28 with a predetermined force, for example in the range of 1000 to 2000 N, against the abutment surface 36 of the bearing sleeve 29. The centrifugal turbo-compressor 2 may for example includes several elastic members located between the first aerodynamic member 22 and the first axial bearing plate 26 and each arranged in a respective through hole provided in the inlet distributor 37. Each elastic member may for example be a coil spring.

(29) The centrifugal turbo-compressor 2 also includes a gas suction inlet 42 provided on the hermetic casing 3, and for example on the bearing casing portion 3.2. According to the embodiment shown on FIGS. 1 to 6, the gas suction inlet 42 includes a gas inlet part 43 having a circular cross section, and a gas outlet part 44 diverging opposite the gas inlet part 43. Advantageously, the gas inlet part 43 extends radially with respect to the longitudinal axis A of the drive shaft 6.

(30) The gas outlet part 44 particularly includes a gas outlet 45 which is oblong and which extends along a circumferential direction with respect to the longitudinal axis A of the drive shaft 6. Advantageously, the gas outlet 45 has a first dimension taken along the longitudinal axis A of the drive shaft 6 and a second dimension taken along the circumferential direction, the second dimension being higher than the first dimension. According to an embodiment of the invention, the first dimension and the second dimension of the gas outlet 45 respect the following equation:

(31) Do2*Do1>D1.sup.2, where D1 is the inlet diameter of the gas suction inlet 42, which particularly corresponds to the inner diameter of the gas inlet part 43, Do1 is the first dimension of the gas outlet 45 and Do2 is the second dimension of the gas outlet 45.

(32) Furthermore, the centrifugal turbo-compressor 2 includes a gas flow path P fluidly connected to the gas suction inlet 42 and configured to supply the first compression stage, and particularly the impeller 17, with a gas flow. The gas flow path P is schematically shown on FIG. 1.

(33) The gas flow path P includes a relaxation chamber 46 extending around the drive shaft 6. The gas suction inlet 42, and particularly the gas outlet part 44, emerges radially into the relaxation chamber 46. As better shown on FIG. 4, the relaxation chamber 46 has an axial length L which is higher than the inlet diameter D1 of the gas suction inlet 42. Advantageously, the relaxation chamber 46 has an outer diameter OD and an inner diameter ID which respect the following equation:
OD.sup.2−ID.sup.2>2*D1.

(34) According to the embodiment shown on FIGS. 1 to 6, the relaxation chamber 46 is defined by the hermetic casing 3, and for example by the bearing casing portion 3.2, and extends around the drive shaft 6 along an angular sector lower than 360°.

(35) Advantageously, the relaxation chamber 46 has a horseshoe-shaped cross sectional profile. To this end, the hermetic casing 3, and particularly the bearing casing portion 3.2, includes an annular volume 47 partially defining the relaxation chamber 46 and a separating wall part 48 located within the annular volume 47 and opposite the gas suction inlet 42, the separating wall part 48 being configured such that the relaxation chamber 46 includes a first arcuate chamber part 46.1 extending from the gas suction inlet 42 to the separating wall part 48 and a second arcuate chamber part 46.2 extending from the gas suction inlet 42 to the separating wall part 48. The first and second arcuate chamber parts 46.1, 46.2 extend on both side of the longitudinal axis A of the drive shaft 6.

(36) The gas flow path P further includes a connecting channel 49 extending around the drive shaft 6 and coaxially to the longitudinal axis A of the drive shaft 6. The connecting channel 49 is annular and is fluidly connected to the relaxation chamber 46. Advantageously, the connecting channel 49 emerges into the relaxation chamber 46 at an outer radial portion of the relaxation chamber 46 so as to define a flow restriction for the gas flow, and particularly an annular flow restriction.

(37) According to the embodiment shown on FIGS. 1 to 6, the connecting channel 49 has an inner diameter Di which is higher than the inner diameter ID of the relaxation chamber 46, and an outer diameter Do which is equal to the outer diameter OD of the relaxation chamber 46.

(38) The gas flow path P further includes a plurality of inlet flow guide channels 51 fluidly connected to the relaxation chamber 46 via the connecting channel 49. The inlet flow guide channels 51 are regularly angularly distributed around the longitudinal axis A of the drive shaft 6, and have advantageously substantially identical widths. The inlet flow guide channels 51 extend radially towards the drive shaft 6 and are axially offset from the gas suction inlet 42 and the relaxation chamber 46. Particularly, the inlet flow guide channels 51 extend in a same extension plane which is perpendicular to the longitudinal axis A of the drive shaft 6 and which is axially offset from the central axis of the gas suction inlet 42.

(39) As better shown on FIG. 5, the centrifugal turbo-compressor 2 includes inlet flow guide members 52 partially defining the inlet flow guide channels 51 and being regularly angularly distributed around the longitudinal axis A of the drive shaft 6. Particularly, the inlet flow guide members 52 are arranged such that each pair of adjacent inlet flow guide members 52 defines a respective inlet flow guide channel 51. According to the embodiment shown on FIGS. 1 to 6, each of the inlet flow guide members 52 extends radially towards the drive shaft 6 and converges towards the drive shaft 6. Advantageously, each inlet flow guide member 52 has an airfoil-shaped cross-sectional profile, and includes a leading edge having a high radius of curvature and a trailing tip oriented towards the drive shaft 6. Each inlet flow guide member 52 may have a constant height.

(40) As better shown on FIG. 5, one of the inlet flow guide channels 51 is located at a same angular position as the separating wall part 48 while being axially offset from the separating wall part 48.

(41) According to the embodiment shown on FIGS. 1 to 6, each inlet flow guide member 52 is partially defined by the inlet distributor 37 and by a stationary flow guiding part 53 having an annular disc shape, the stationary flow guiding part 53 surrounding the inlet distributor 37 and being clamped between the impeller casing portion 3.1 and the bearing casing portion 3.2.

(42) Particularly, the inlet distributor 37 includes inlet flow guide elements 54 extending radially towards the drive shaft 6 and projecting from an axial surface of the inlet distributor 37 facing towards the impeller 17, and the stationary flow guiding part 53 also includes inlet flow guide portions 55 projecting from an axial surface of the stationary flow guiding part 53 facing towards the impeller 17. Each inlet flow guide element 54 is particularly angularly aligned with a respective inlet flow guide portion 55 so as to define a respective inlet flow guide member 52.

(43) According to the embodiment shown on FIGS. 1 to 6, the connecting channel 49 is defined by the stationary flow guiding part 53 and by the hermetic casing 3, and the connecting channel 49 is configured so as to respect the following equation:

(44) π*H*Di<π/4*(Do.sup.2−Di.sup.2), where H is the height of each inlet flow guide member 52 (which corresponds to the dimension of each inlet flow guide channel 51 taken along the longitudinal axis A), Di is the inner diameter of the connecting channel 49 and Do is the outer diameter of the connecting channel 49.

(45) The gas flow path P further includes an annular supplying channel 56 fluidly connected to the inlet flow guide channels 51, and configured to axially supply the impeller 17 with the gas flow. Advantageously, the annular supplying channel 56 extends around the drive shaft 6 and is internally defined by an annular converging surface 57 which converges towards the impeller 17. According to the embodiment shown on FIGS. 1 to 6, the annular converging surface 57 is provided on a covering part 58 which is secured to the inlet distributor 37, the covering part 58 extending around the drive shaft 6 and being configured such that the gas flow flowing from the inlet flow guide channels 51 to the impeller 17 does not contact a rotational part, and for example the drive shaft 6.

(46) During operation of the centrifugal turbo-compressor 2, a gas flow, flowing out the gas suction inlet 42, comes radially into the relaxation chamber 46, and then flows at low speed in the first and second arcuate chamber parts 46.1, 46.2 before entering the connecting channel 49. The gas flow coming out of the connecting channel 49 enters the inlet flow guide channels 51 and flows radially through the inlet flow guide channels before being axially supplied to the impeller 17 via the annular supplying channel 56.

(47) Such a configuration of the gas flow path and of the gas suction inlet substantially minimizes the pressure losses at the inlet of the gas flow path and substantially minimizes the flow distortions through the inlet flow guide channels. This results in a more homogenous flow distribution along a circumferential direction at the fluid inlet of the first impeller, and thus substantially improves the compressor efficiency, while enabling an easy manufacturing of the turbo-compressor.

(48) FIG. 7 represents a single-stage hermetic centrifugal turbo-compressor 2 according to a second embodiment of the invention which differs from the first embodiment essentially in that it includes only compression stage, and thus one impeller 17 and one aerodynamic member 22.

(49) Of course, the invention is not restricted to the embodiment described above by way of non-limiting examples, but on the contrary it encompasses all embodiments thereof.