AU2016280924B2 - Expansion turbine device - Google Patents
Expansion turbine device Download PDFInfo
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- AU2016280924B2 AU2016280924B2 AU2016280924A AU2016280924A AU2016280924B2 AU 2016280924 B2 AU2016280924 B2 AU 2016280924B2 AU 2016280924 A AU2016280924 A AU 2016280924A AU 2016280924 A AU2016280924 A AU 2016280924A AU 2016280924 B2 AU2016280924 B2 AU 2016280924B2
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- bearing
- gas
- chamber
- rotary shaft
- hydrostatic bearing
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- 230000002706 hydrostatic effect Effects 0.000 claims abstract description 204
- 239000003507 refrigerant Substances 0.000 claims description 48
- 239000000203 mixture Substances 0.000 claims description 27
- 238000003780 insertion Methods 0.000 claims description 23
- 230000037431 insertion Effects 0.000 claims description 23
- 238000011144 upstream manufacturing Methods 0.000 claims description 19
- 238000004891 communication Methods 0.000 claims description 5
- 230000003068 static effect Effects 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 abstract 2
- 239000007789 gas Substances 0.000 description 326
- 239000000470 constituent Substances 0.000 description 8
- 230000002093 peripheral effect Effects 0.000 description 8
- 239000002994 raw material Substances 0.000 description 5
- 230000007423 decrease Effects 0.000 description 4
- 230000003247 decreasing effect Effects 0.000 description 4
- 239000012528 membrane Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000004323 axial length Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000010687 lubricating oil Substances 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
- F16C32/0603—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion
- F16C32/0614—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion the gas being supplied under pressure, e.g. aerostatic bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/0002—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures characterised by the fluid to be liquefied
- F25J1/0005—Light or noble gases
- F25J1/001—Hydrogen
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/02—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process
- F25J1/0243—Start-up or control of the process; Details of the apparatus used; Details of the refrigerant compression system used
- F25J1/0257—Construction and layout of liquefaction equipments, e.g. valves, machines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/72—Sealings
- F16C33/76—Sealings of ball or roller bearings
- F16C33/80—Labyrinth sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J2240/00—Processes or apparatus involving steps for expanding of process streams
- F25J2240/02—Expansion of a process fluid in a work-extracting turbine (i.e. isentropic expansion), e.g. of the feed stream
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
- Sealing Of Bearings (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
This expansion turbine device is provided with a main body, a turbine impeller, a brake impeller, a rotation shaft, a hydrostatic gas bearing, a first labyrinth seal, a mixed gas discharge path, a first back pressure regulating valve, a temperature sensor, and a control device which, if the temperature of the mixed gas flowing through the mixed gas discharge path drops, controls the first back pressure regulating valve so as to raise the back pressure of the hydrostatic gas bearing.
Description
EXPANSION TURBINE APPARATUS
DESCRIPTION
Technical Field [0001] The present invention relates to an expansion turbine apparatus. Particularly, the present invention relates to a leakage prevention technique for the expansion turbine apparatus including hydrostatic gas bearings.
Background Art [0002] In general, a liquefying system which liquefies a raw material gas such as a hydrogen gas and a helium gas includes a feed line which sends the raw material gas, a refrigerant circulation line which circulates a refrigerant gas, and a heat exchanger which cools the raw material gas with a refrigerant. The refrigerant gas circulated through the refrigerant circulation line is compressed by a compressor, and then expanded in a heat insulating state by an expansion turbine, so that the temperature of the refrigerant gas is decreased. In the heat exchanger, the raw material gas is cooled by heat exchange with the refrigerant gas in a decreased temperature state.
[0003] A bearing which supports a rotary shaft is required for the expansion turbine. If a liquid bearing which uses lubricating oil is used as the bearing for the expansion turbine, the lubricating oil may flow into the refrigerant gas flowing through the expansion turbine. For this reason, a gas bearing which uses a gas with the same kind as that of the refrigerant gas is preferably used as the bearing. Among the gas bearings, a hydrostatic gas bearing is capable of suppressing friction between a bearing surface and the rotary shaft during start and stop of the liquefying system, and is suitable for a high-speed rotation. For this reason, the hydrostatic gas bearing is used as the bearing of the expansion turbine (e.g., see Patent Literature 1).
[0004] The expansion turbine which uses the hydrostatic gas bearing includes a bearing gas supply line which supplies to the hydrostatic gas bearing a bearing gas with the same kind as that of the refrigerant gas, and a bearing gas discharge line which discharges the bearing gas which has flowed through the hydrostatic gas bearing. A rotary shaft is inserted into a bearing chamber inside the expansion turbine, and the bearing gas supply line and the bearing gas discharge line are connected to each other. A turbine impeller provided at a first end (one end) of the rotary shaft is accommodated in the expansion chamber. The expansion chamber is provided with an expansion chamber entrance into which the refrigerant gas flows, at an outer peripheral side of the turbine impeller, and an expansion chamber exit from which the refrigerant gas is discharged, at a center portion in an axial direction. A brake impeller provided at a second end (the other end) of the rotary shaft is accommodated in a braking gas chamber. The braking gas chamber is provided with a communication passage via which the exit and entrance of the braking gas chamber are in communication with each other, and thus a closed circuit including the brake impeller is formed.
[0005] A labyrinth seal is provided on the back surface of the turbine impeller of the expansion turbine to suppress leakage of the refrigerant gas with a low temperature from the expansion chamber to the bearing chamber (e.g., see Patent Literature 2).
Citation List
Patent Literature [0006] Patent Literature 1: Japanese-Laid Open Patent Application Publication No. 2000-55050
Patent Literature 2: Japanese-Laid Open Patent Application Publication No. Hei.
6-26301
Summary of Invention
Technical Problem [0007] However, there is a clearance between the labyrinth seal and the rotary shaft. Therefore, the labyrinth seal cannot perfectly prevent the leakage due to a seal differential pressure. If the amount of leakage of the low-temperature gas from the expansion chamber to the bearing chamber is increased, efficiency of the expansion turbine is reduced. In addition, due to cooling of the bearing chamber, the dimension of a clearance between the rotary shaft and a radial hydrostatic bearing is changed. Depending on the case, contact between the rotary shaft and the radial hydrostatic bearing occurs.
[0008] In view of the above, an object of the present invention is to suppress seal leakage of a low-temperature gas in an expansion turbine including hydrostatic gas bearings.
Solution to Problem [0009] According to an aspect of the present invention, an expansion turbine apparatus includes a body formed with an expansion chamber, a braking gas chamber, and a shaft insertion hole inside the body, the shaft insertion hole being provided in such a manner that the expansion chamber and the braking gas chamber are in communication with each other via the shaft insertion hole and a rotary shaft is insertable into the shaft insertion hole; a turbine impeller accommodated in the expansion chamber to expand a refrigerant gas; a brake impeller which is accommodated in the braking gas chamber, and braked by a braking gas with the same kind as that of the refrigerant gas; the rotary shaft inserted into the shaft insertion hole with a clearance between the rotary shaft and the shaft insertion hole, the turbine impeller being provided at a first end portion of the rotary shaft, the brake impeller being provided at a second end portion of the rotary shaft; a hydrostatic gas bearing which is provided in a bearing chamber formed inside the shaft insertion hole and supports the rotary shaft in such a manner that the rotary shaft is rotatable, by a static pressure of a bearing gas with the same kind as that of the refrigerant gas supplied from an entrance and discharged from an exit; a first labyrinth seal provided in a region between an end of the bearing chamber, the end being closer to the expansion chamber, and a portion of the bearing chamber at which the hydrostatic gas bearing is disposed; a mixture gas discharge passage which discharges a mixture gas containing the bearing gas and the refrigerant gas which has leaked from the expansion chamber to the bearing chamber through the first labyrinth seal; a first back pressure control valve provided at the mixture gas discharge passage to control a back pressure of the hydrostatic gas bearing; a temperature sensor provided at the mixture gas discharge passage to measure a temperature of the mixture gas; and a controller which controls the first back pressure control valve so that the back pressure of the hydrostatic gas bearing is increased, in a case where the temperature of the mixture gas flowing through the mixture gas discharge passage is reduced.
[0010] In a case where the amount of the refrigerant gas which leaks from the expansion chamber to the bearing chamber through the first labyrinth seal is increased, the temperature of the mixture gas flowing through the mixture gas discharge passage is reduced. However, in accordance with the above-described configuration, the controller increases the back pressure of the hydrostatic gas bearing in a case where the temperature of the mixture gas is reduced. This makes it possible to reduce the differential pressure of the first labyrinth seal. As a result, the amount of leakage of the refrigerant gas can be reduced.
[0011] In the above-described expansion turbine apparatus, the hydrostatic gas bearing may include a first radial hydrostatic bearing and a second radial hydrostatic bearing which support the rotary shaft in a radial direction in such a manner that the rotary shaft is rotatable, and a thrust hydrostatic bearing which supports the rotary shaft in an axial direction in such a manner that the rotary shaft is rotatable, the first radial hydrostatic bearing, the thrust hydrostatic bearing, and the second radial hydrostatic bearing are disposed in this order inside the bearing chamber, in a direction from the expansion chamber toward the braking gas chamber, the first labyrinth seal may be provided in a region between the end of the bearing chamber, the end being closer to the expansion chamber, and a portion of the bearing chamber at which the first radial hydrostatic bearing is disposed, an upstream end of the mixture gas discharge passage may be connected to an exit of the first radial hydrostatic bearing, and upstream ends of a bearing gas dedicated discharge passage may be connected to an exit of the thrust hydrostatic bearing, and an exit of the second radial hydrostatic bearing.
[0012] In accordance with this configuration, a back pressure control is performed only for the first radial hydrostatic bearing located closer to the expansion chamber, independently of the other bearings. If the back pressure is excessively increased in the back pressure control, bearing performance is reduced. However, in accordance with the above-described configuration, only the first radial hydrostatic bearing which is adjacent to the first labyrinth seal and closer to the expansion chamber is controlled, and thus the back pressure control can be realized. In addition, the back pressures of the other bearings can be more flexibly set. In this way, a suitable control can be realized.
[0013] In the above-described expansion turbine apparatus, the hydrostatic gas bearing may include a first radial hydrostatic bearing and a second radial hydrostatic bearing which support the rotary shaft in a radial direction in such a manner that the rotary shaft is rotatable, and a thrust hydrostatic bearing which supports the rotary shaft in an axial direction in such a manner that the rotary shaft is rotatable, and the first radial hydrostatic bearing, the thrust hydrostatic bearing, and the second radial hydrostatic bearing may be disposed in this order inside the bearing chamber, in a direction from the expansion chamber toward the braking gas chamber, the expansion turbine apparatus may further include a second labyrinth seal provided in a region between the first radial hydrostatic bearing and the thrust hydrostatic bearing in the bearing chamber; a bearing gas dedicated discharge passage, upstream ends of which are connected to an exit of the thrust hydrostatic bearing and an exit of the second radial hydrostatic bearing; a second back pressure control valve provided at the bearing gas dedicated discharge passage to control a back pressure of the thrust hydrostatic bearing and a back pressure of the second radial hydrostatic bearing; a braking line, a first end of which is connected to an exit of the braking gas chamber and a second end of which is connected to an entrance of the braking gas chamber; and a gas flow passage, a first end of which is connected to the braking line and a second end of which is connected to the bearing gas dedicated discharge passage.
[0014] In accordance with this configuration, a pressure in the braking line, and back pressures of the thrust hydrostatic bearing and the second radial hydrostatic bearing can be made uniform by utilizing the gas flow passage, and a pressure control can be performed independently of a control for the bearing back pressure of the first radial hydrostatic bearing. In addition, in accordance with this configuration, since the second labyrinth seal is disposed in a region between the first radial hydrostatic bearing and the thrust hydrostatic bearing, a distance between the second radial hydrostatic bearing and the expansion chamber can be reduced, and the axial length of the rotary shaft from the second radial hydrostatic bearing to the expansion chamber side can be reduced. As a result, a mass of a rotary member can be reduced, and vibration stability can be improved.
[0015] In the above-described expansion turbine apparatus, the hydrostatic gas bearing may include a first radial hydrostatic bearing and a second radial hydrostatic bearing which support the rotary shaft in a radial direction in such a manner that the rotary shaft is rotatable, and a thrust hydrostatic bearing which supports the rotary shaft in an axial direction in such a manner that the rotary shaft is rotatable, the first radial hydrostatic bearing, the thrust hydrostatic bearing, and the second radial hydrostatic bearing may be disposed in this order inside the bearing chamber, in a direction from the expansion chamber toward the braking gas chamber, the first labyrinth seal may be provided in a region between the end of the bearing chamber, the end being closer to the expansion chamber, and a portion of the bearing chamber at which the first radial hydrostatic bearing is disposed, an upstream end of the mixture gas discharge passage may be connected to an exit of the first radial hydrostatic bearing, the exit being closer to the expansion chamber, and upstream ends of a bearing gas dedicated discharge passage may be connected to an exit of the first radial hydrostatic bearing, the exit being closer to the braking gas chamber, an exit of the thrust hydrostatic bearing, and an exit of the second radial hydrostatic bearing.
[0016] In accordance with this configuration, the back pressure control is performed only for the exit of the first radial hydrostatic bearing closest to the first labyrinth seal, the exit being closer to the expansion chamber, the back pressure can be more flexibly set and a suitable control can be realized.
Advantageous Effects of Invention [0017] In accordance with the present invention, it becomes possible to suppress seal leakage of a low-temperature gas in an expansion turbine apparatus including hydrostatic gas bearings. As a result, it becomes possible to suppress reduction of efficiency of a turbine and cooling of a bearing chamber.
[0018] The above and further objects, features and advantages of the present invention will more fully be apparent from the following detailed description of preferred embodiment with reference to accompanying drawings.
Brief Description of Drawings [0019] Fig. 1 is a partial cross-sectional view showing the configuration of an expansion turbine apparatus according to Embodiment 1.
Fig. 2 is a schematic view showing the configuration of a radial hydrostatic bearing of Fig. 1.
Fig. 3 is a schematic view showing the configuration of a thrust hydrostatic bearing ofFig. 1.
Fig. 4 is a schematic view showing the configuration of a labyrinth seal ofFig. 1.
Fig. 5 is a schematic view showing the overall configuration of the expansion turbine apparatus ofFig. 1.
Fig. 6 is a schematic view showing the configuration of an expansion turbine apparatus according to Embodiment 2.
Fig. 7 is a schematic view showing the configuration of an expansion turbine apparatus according to Embodiment 3.
Fig. 8 is a schematic view showing the configuration of an expansion turbine apparatus according to Embodiment 4.
Description of Embodiments [0020] Hereinafter, embodiments of the present invention will be described with reference to the drawings. Throughout the drawings, the same or corresponding constituents are designated by the same reference symbols and will not be described in repetition.
[0021] (Embodiment 1)
Fig. 1 is a partial cross-sectional view showing the configuration of an expansion turbine apparatus according to Embodiment 1. As shown in Fig. 1, an expansion turbine apparatus 1 includes an expansion chamber 21, a braking gas chamber 20, and a shaft insertion hole 22, inside a body 10. The body 10 has, for example, a casing shape. The shaft insertion hole 22 is provided so that the expansion chamber 21 and the braking gas chamber 20 are in communication with each other via the shaft insertion hole 22, and a rotary shaft 13 is insertable into the shaft insertion hole 22.
[0022] The rotary shaft 13 is inserted into the shaft insertion hole 22 with a clearance between the rotary shaft 13 and the shaft insertion hole 22. A turbine impeller 11 is provided at a first end portion (one end portion) of the rotary shaft 13. A brake impeller 12 is provided at a second end portion (the other end portion) of the rotary shaft 13. The rotary shaft 13 extends vertically inside the body 10. The rotary shaft 13 is supported in such a manner that the rotary shaft 13 is rotatable around a vertical axis (axis extending vertically).
[0023] The turbine impeller 11 is accommodated in the expansion chamber 21 and configured to expand a refrigerant gas. The turbine impeller 11 is provided at the lower end portion of the rotary shaft 13. The body 10 is provided with an expansion chamber entrance 24 and an expansion chamber exit 26, in the lower end portion of the body 10. With this structure, the expansion chamber 21 accommodating the turbine impeller 11 is connected to a turbine line 16 (see Fig. 5) disposed outside the body 10. The refrigerant gas flows from the turbine line 16 into the expansion chamber entrance 24. The refrigerant gas is injected toward the turbine impeller 11. According to the rotation of the turbine impeller 11, the refrigerant gas is expanded and its temperature is decreased. After that, the refrigerant gas flows out of the body 10 through the expansion chamber exit 26.
[0024] The brake impeller 12 is accommodated in the braking gas chamber 20. The brake impeller 12 is braked by a braking gas with the same kind as that of the refrigerant gas. The brake impeller 12 is provided at the upper end portion of the rotary shaft 13. The body 10 is provided with a braking gas chamber entrance 27 and a braking gas chamber exit 29, in the upper portion of the body 10. In this structure, the braking gas chamber 20 accommodating the brake impeller 12 is connected to a braking line 15 (see Fig. 5) disposed outside the body 10. The braking gas with a room (normal) temperature flows from the braking line 15 into the braking gas chamber entrance 27, and then flows toward the brake impeller 12. According to the rotation of the brake impeller 12, the braking gas is compressed and its pressure and temperature are increased. After that, the refrigerant gas flows out of the braking gas chamber exit 29. Then, the braking gas flows through the braking line 15 and is returned to the braking gas chamber entrance 27.
[0025] A hydrostatic gas bearing 14 is provided in a bearing chamber 23 formed in the shaft insertion hole 22. The hydrostatic gas bearing 14 supports the rotary shaft 13 in such a manner that the rotary shaft 13 is rotatable, by a static pressure of a bearing gas with the same kind as that of the refrigerant gas which is supplied from the expansion chamber entrance 24 and discharged from the expansion chamber exit 26. The hydrostatic gas bearing 14 includes radial hydrostatic bearings 14a, 14d which support the rotary shaft 13 in a radial direction in such a manner that the rotary shaft 13 is rotatable, and thrust hydrostatic bearings 14b, 14c which support the rotary shaft 13 in an axial direction in such a manner that the rotary shaft 13 is rotatable. These hydrostatic gas bearings 14a to 14d have a substantially cylindrical shape and surround the outer periphery of the rotary shaft 13. In the bearing chamber 23, the first radial hydrostatic bearing 14d, the first thrust hydrostatic bearing 14c, the second thrust hydrostatic bearing 14b, and the radial hydrostatic bearing 14a are arranged in this order, in a direction from the expansion chamber 21 toward the braking gas chamber 20. The second thrust hydrostatic bearing 14b and the first thrust hydrostatic bearing 14c are disposed to vertically sandwich a thrust collar 34 protruding in the radial direction from the vertical center portion of the rotary shaft 13.
[0026] Inside the body 10, a first common gas supply passage 35a, a second common gas supply passage 35b, and a common gas discharge passage 36 are provided. The first common gas supply passage 35 a, the second common gas supply passage 35b, and the common gas discharge passage 36 are provided at different positions in a circumferential direction. The first common gas supply passage 35a is connected to a bearing gas inlet 49. The first common gas supply passage 35a is used to flow the bearing gas to be supplied to a clearance of the second radial hydrostatic bearing 14a and a clearance of the first radial hydrostatic bearing 14d. The second common gas supply passage 35b is connected to the bearing gas inlet 49. The second common gas supply passage 35b is used to flow the bearing gas to be supplied to a clearance of the second thrust hydrostatic bearing 14b and a clearance of the first thrust hydrostatic bearing 14c. Although in the present embodiment, the first common gas supply passage 35a and the second common gas supply passage 35b are independent of each other, they may be configured as a common passage. The common gas discharge passage 36 is connected to a bearing gas outlet 50. The common gas discharge passage 36 is used to flow the bearing gas having been discharged from the clearances of the hydrostatic gas bearings 14a to 14d.
[0027] The first common gas supply passage 35a is divided into a first gas supply passage 37 and a second gas supply passage 38. The second common gas supply passage 35b is divided into a third gas supply passage 43 and a fourth gas supply passage 44. The first gas supply passage 37 is used to flow the bearing gas to be supplied to the clearance of the second radial hydrostatic bearing 14a. The second gas supply passage 38 is used to flow the bearing gas to be supplied to the clearance of the first radial hydrostatic bearing 14d. The third gas supply passage 43 is used to flow the bearing gas to be supplied to the clearance of the second thrust hydrostatic bearing 14b. The fourth gas supply passage 44 is used to flow the bearing gas to be supplied to the clearance of the first thrust hydrostatic bearing 14c.
[0028] The common gas discharge passage 36 is connected to a first gas discharge passage 39, a second gas discharge passage 40, a third gas discharge passage 41, and a fourth gas discharge passage 42. The first gas discharge passage 39 is used to flow the bearing gas having been discharged in an upward direction from the clearance of the second radial hydrostatic bearing 14a. The second gas discharge passage 40 is used to flow the bearing gas having been discharged in a downward direction from the clearance of the second radial hydrostatic bearing 14a and the bearing gas having been discharged in the upward direction from the clearance of the second thrust hydrostatic bearing 14b. The third gas discharge passage 41 is used to flow the bearing gas having been discharged in the downward direction from the clearance of the first thrust hydrostatic bearing 14c and the bearing gas having been discharged in the upward direction from the clearance of the first radial hydrostatic bearing 14d. The fourth gas discharge passage 42 is used to flow the bearing gas having been discharged in the downward direction from the clearance of the first radial hydrostatic bearing 14d. The refrigerant gas which has leaked from the expansion chamber 21 to a portion of the bearing chamber 23 corresponding to the first radial hydrostatic bearing 14d through the first labyrinth seal 30 flows into the fourth gas discharge passage 42.
[0029] Fig. 2 schematically shows the cross-section of the configuration of the first radial hydrostatic bearing 14d. As shown in Fig. 2, a bearing member 51 with a substantially cylindrical shape is provided to surround the outer periphery of the rotary shaft 13. The bearing member 51 has a clearance between the bearing member 51 and the rotary shaft 13. The bearing member 51 has a plurality of nozzle holes (bearing entrances) 51a formed in the circumferential direction. The bearing gas flowing through the second gas supply passage 38 which branches from the first common gas supply passage 35a of Fig. 1 is injected to the rotary shaft 13 through the nozzle holes 51a. A bearing membrane (indicated by dotted lines) of the first radial hydrostatic bearing 14d is formed between the inner peripheral surface of the bearing member 51 and the outer peripheral surface of the rotary shaft 13. The bearing gas (indicated by dotted-line arrows) having been discharged in the upward direction from a first end (bearing exit) of the clearance of the first radial hydrostatic bearing 14d is discharged through the third gas discharge passage 41 and then the common gas discharge passage 36 of Fig. 1. The bearing gas (indicated by dotted-line arrows) having been discharged in the downward direction from a second end (bearing exit) of the clearance of the first radial hydrostatic bearing 14d is discharged through the fourth gas discharge passage 42 and then the common gas discharge passage 36 of Fig. 1. The second radial hydrostatic bearing 14a of Fig. 1 has a structure similar to that of the first radial hydrostatic bearing 14d. The bearing membrane is formed by the bearing gas in the second radial hydrostatic bearing 14a. The bearing gases having been discharged in the upward direction and the downward direction from the both ends (bearing exit) of the clearance of the second radial hydrostatic bearing 14a are guided to the common gas discharge passage 36 through the first gas discharge passage 39 and the second gas discharge passage 40.
[0030] Fig. 3 schematically shows the cross-section of the thrust hydrostatic bearings 14b, 14c. As shown in Fig. 3, the rotary shaft 13 and the thrust collar 34 are disposed with a clearance inside the body 10. The third gas supply passage 43 branches from the second common gas supply passage 35b of Fig. 1. The third gas supply passage 43 is used to flow the bearing gas to be supplied to the clearance of the second thrust hydrostatic bearing 14b. The fourth gas supply passage 44 branches from the second common gas supply passage 35b. The fourth gas supply passage 44 is used to flow the bearing gas to be supplied to the clearance of the first thrust hydrostatic bearing 14c.
[0031] The bearing gas flowing through the third gas supply passage 43 is injected through a nozzle hole (bearing entrance) 43a. A bearing membrane (indicated by dotted lines) of the second thrust hydrostatic bearing 14b is formed between the lower end surface of an inner wall 22a of the shaft insertion hole 22 and the upper end surface of the thrust collar 34. The bearing gas flowing through the fourth gas supply passage 44 is injected through a nozzle hole 44a. A bearing membrane (indicated by dotted lines) of the first thrust hydrostatic bearing
14c is formed between the upper end surface of the inner wall 22a of the shaft insertion hole 22 and the lower end surface of the thrust collar 34. The bearing gas (indicated by dotted-line arrows) having been discharged in the upward direction from a first end (bearing exit) of the clearance of the second thrust hydrostatic bearing 14b is discharged through the second gas discharge passage 40 and then the common gas discharge passage 36 of Fig. 1. The bearing gas (indicated by dotted-line arrows) having been discharged in the downward direction from a second end (bearing exit) of the clearance of the first thrust hydrostatic bearing 14c is discharged through the third gas discharge passage 41 and then the common gas discharge passage 36 of Fig. 1. The bearing gas (indicated by dotted-line arrows) having been discharged in the downward direction from a first end (bearing exit) of the clearance of the second thrust hydrostatic bearing 14b and the bearing gas (indicated by dotted-line arrows) having been discharged in the upward direction from a second end (bearing exit) of the clearance of the first thrust hydrostatic bearing 14c are discharged through the common gas discharge passage 36.
[0032] The body 10 of Fig. 1 includes the bearing gas inlet 49 and the bearing gas outlet 50. The bearing gas inlet 49 is connected to the first common gas supply passage 35a and the second common gas supply passage 35b. The bearing gas outlet 50 is connected to the common gas discharge passage 36. Through the bearing gas inlet 49, the bearing gas is supplied to the hydrostatic gas bearings 14a to 14d inside the body 10 of the expansion turbine apparatus 1. As the bearing gas, the gas with the same kind as that of the refrigerant gas is used. By supplying the bearing gas to the clearances of the hydrostatic gas bearings 14a to 14d, the rotary shaft 13 can be rotatably supported inside the body 10, and a radial load and a thrust load of the rotary shaft 13 can be sufficiently home. During start-up and stop of the expansion turbine apparatus 1, no friction is generated between the outer peripheral surface of the rotary shaft 13 and the inner peripheral surfaces of the hydrostatic gas bearings 14a to 14d. As a result, the life of the expansion turbine apparatus 1 can be extended.
[0033] A first labyrinth seal 30 is provided in a region between the end of the bearing chamber 23, the end being closer to the expansion chamber 21 (the end on the expansion chamber 21 side), and a portion of the bearing chamber 23 at which the first radial hydrostatic bearing 14d is disposed (see Fig. 1). Fig. 4 is a schematic view showing the configuration of the first labyrinth seal 30. As shown in Fig. 4, the first labyrinth seal 30 has an inner peripheral surface surrounding the outer periphery of the rotary shaft 13 with a gap between the inner peripheral surface and the outer periphery of the rotary shaft 13. The inner peripheral surface of the first labyrinth seal 30 has a plurality of concave-convex portions forming the gap. Whenever the refrigerant flows into the gap, a leakage pressure gradually decreases. It becomes possible to suppress leakage of refrigerants which are the bearing gas and the refrigerant gas with an extremely low temperature which has been expanded in a heat insulating state in the expansion chamber 21. A second labyrinth seal 31 having a similar structure is provided in a region between the end of the bearing chamber 23, the end being closer to the braking gas chamber 20 and a portion of the bearing chamber 23 at which the second radial hydrostatic bearing 14a is disposed (see Fig. 1). The second labyrinth seal 31 can suppress leakage of the refrigerants which are the bearing gas and the braking gas in the braking gas chamber 20.
[0034] Fig. 5 is a schematic view showing the overall configuration of the expansion turbine apparatus 1 of Fig. 1. Hereinafter, the constituents already described above will not be described in repetition. As shown in Fig. 5, the expansion turbine apparatus 1 includes the body 10, the braking line 15, the turbine line 16, a bearing gas supply line 17, a gas discharge line 18, a temperature sensor 60, a first back pressure control valve 80, and a controller 90. [0035] The braking line 15 is a pipe which circulates the braking gas to be supplied to the brake impeller 12. A first end (one end) of the braking line 15 is connected to the braking gas chamber entrance 27 of the braking gas chamber 20 of Fig. 1, while a second end (the other end) of the braking line 15 is connected to the braking gas chamber exit 29 of the braking gas chamber 20. A heat exchanger 53 is provided in a portion of the braking line 15.
[0036] The heat exchanger 53 serves to decrease the temperature and pressure of the braking gas circulated through the braking line 15. The braking gas circulated through the braking line 15 is compressed, and thereby its temperature and pressure are increased, while flowing through the brake impeller 12. However, the braking gas flows through the heat exchanger 53 and thereby its temperature and pressure are decreased.
[0037] The turbine line 16 is a pipe used to supply the refrigerant gas to the turbine impeller 11. A first end of the turbine line 16 is connected to the expansion chamber entrance 24 of the expansion chamber 21 of Fig. 1. A second end of the turbine line 16 is connected to the expansion chamber exit 26 of the expansion chamber 21. The refrigerant with a low temperature and a high pressure which has been compressed by a compressor (not shown) at an upstream side of the expansion chamber entrance 24 of the expansion chamber 21 is led to the turbine impeller 11. The turbine impeller 11 decreases the temperature and pressure of the refrigerant with the low temperature and the high pressure by heat insulative expansion.
[0038] The bearing gas supply line 17 is configured to supply the bearing gas to the hydrostatic gas bearings 14a to 14d. A first end of the bearing gas supply line 17 is connected to, for example, a feed line which sends the raw material gas of the liquefying system. A second end of the bearing gas supply line 17 is connected to the bearing gas inlet 49 of the body 10 (see Fig. 1). The bearing gas supply line 17 is configured to supply the bearing gas to each of the second radial hydrostatic bearing 14a, the second thrust hydrostatic bearing 14b, the first thrust hydrostatic bearing 14c, and the first radial hydrostatic bearing 14d. The bearing gas supply line 17 is connected to the first common gas supply passage 35a and the second common gas supply passage 25b of Fig. 1. The bearing gas is supplied to the second radial hydrostatic bearing 14a and the first radial hydrostatic bearing 14d through the first gas supply passage 37 and the second gas supply passage 38, respectively, which branch from the first common gas supply passage 35 a. The bearing gas is supplied to the first thrust hydrostatic bearing 14c and the second thrust hydrostatic bearing 14b through the third gas supply passage 43 and the fourth gas supply passage 44, respectively, which branch from the second common gas supply passage 35b (see Fig. 1).
[0039] The upstream end of the gas discharge line 18 is connected to the exit of the bearing chamber 23 corresponding to the hydrostatic gas bearings 14a to 14d to discharge the bearing gas which has flowed through the hydrostatic gas bearings 14a to 14d. In the present embodiment, the upstream end of the gas discharge line 18 is connected to the bearing gas outlet 50 of Fig. 1. The gas discharge line 18 includes the first gas discharge passage 39, the second gas discharge passage 40, the third gas discharge passage 41, the fourth gas discharge passage 42, and the common gas discharge passage 36 of Fig. 1 (see Fig. 1). The gas discharge line 18 is a mixture gas discharge passage configured to discharge a mixture gas containing the bearing gas which has flowed through the hydrostatic gas bearings 14a to 14d, and the refrigerant gas which has leaked from the turbine line 16 (expansion chamber) to a portion of the bearing chamber 23 corresponding to the first radial hydrostatic bearing 14d through the first labyrinth seal 30.
[0040] The temperature sensor 60 is attached on the gas discharge line 18 and configured to measure a bearing discharge gas temperature Ti in the gas discharge line 18. The temperature sensor 60 is configured to output the measured temperature information to the controller 90. [0041] The first back pressure control valve 80 is provided at the gas discharge line 18 and configured to control a back pressure in the gas discharge line 18 in accordance with a command from the controller 90.
[0042] The controller 90 is provided at the gas discharge line 18 and configured to control opening and closing of the first back pressure control valve 80 based on the bearing discharge gas temperature Ti measured by the temperature sensor 60. In the present embodiment, the controller 90 has a function of controlling the compressor and other devices, as well as the expansion turbine apparatus 1. The controller 90 is, for example, a microcomputer configured to mainly include CPU, ROM, and an input/output interface. Process data such as measurement values of the pressure and temperature of the gas discharge line 18 and a turbine rotational speed are input to the input side of the controller 90. The first back pressure control valve 80, a supply valve, a discharge valve, and others are connected to the output side of the controller 90. The CPU is configured to execute control programs stored in the ROM. The CPU controls the first back pressure control valve 80 so that a set bearing back pressure is obtained while monitoring the temperature measurement value of the process data. In a case where the bearing discharge gas temperature Ti becomes lower than a reference value Ts, the controller 90 increases a bearing back pressure Pi. The reference value Ts of the temperature is a predetermined value or a specified range value in a normal state.
[0043] Next, the operation of the expansion turbine apparatus 1 configured as described above will be described with reference to Fig. 5. The expansion turbine apparatus 1 rotates at an ultra-high speed by the refrigerant with the low temperature and the high pressure which is supplied through the turbine line 16. During the operation (running) of the expansion turbine apparatus 1, the bearing gas is supplied from the bearing gas supply line 17 to the hydrostatic gas bearings 14a to 14d of the turbine body 10. Thus, the rotary shaft 13 is rotatably supported inside the body 10, and the radial load and thrust load of the rotary shaft 13 are borne. The bearing gas of the hydrostatic gas bearings 14a to 14d is discharged from the gas discharge line 18. The first labyrinth seal 30 is provided in a region between the end of the bearing chamber 23, the end being closer to the expansion chamber 21 accommodating the turbine impeller 11, and a portion of the bearing chamber 23 at which the first radial hydrostatic bearing 14d is disposed. However, some of the refrigerant gas leaks from the turbine line 16 (expansion chamber) to the bearing chamber 23 through the first labyrinth seal 30. Therefore, the mixture gas containing the bearing gas and the refrigerant gas having leaked exits in the gas discharge line 18. In a case where the amount of the refrigerant gas which leaks from the turbine line 16 (expansion chamber) to the bearing chamber 23 through the first labyrinth seal 30 is increased, the temperature of the gas discharge line 18 which is measured by the temperature sensor 60 is reduced. As the differential pressure in the first labyrinth seal 30 is increased, the amount of leakage of the refrigerant gas is increased. It is difficult to attach a sensor on an entrance or an exit of the first labyrinth seal 30, and it is difficult to accurately measure a pressure. In view of this, in a case where the bearing discharge gas temperature Ti in the gas discharge line 18 becomes lower than the reference value Ts, the controller 90 increases the bearing back pressure Pi. This reduces the differential pressure in the first labyrinth seal 30. As a result, the amount of leakage of the refrigerant gas can be reduced.
[0044] (Embodiment 2)
Next, Embodiment 2 will be described with reference to Fig. 6. Hereinbelow, the same constituents as those of Embodiment 1 will not be described, and only the constituents different from those of Embodiment 1 will be described.
[0045] Fig. 6 is a schematic view showing the configuration of an expansion turbine apparatus 1A according to Embodiment 2. As shown in Fig. 6, the expansion turbine apparatus lAis different from the expansion turbine apparatus 1 according to Embodiment 1 (Fig. 5) in that the upstream end of the gas discharge line (mixture gas discharge passage) 18 is connected to the exit of the first radial hydrostatic bearing 14d and the upstream ends of a bearing gas discharge line (bearing gas dedicated discharge passage) 18a are connected to the exit of the first thrust hydrostatic bearing 14c, the exit of the second thrust hydrostatic bearing 14b, and the exit of the second radial hydrostatic bearing 14a. The gas discharge line 18 is configured to discharge the bearing gas which has flowed through the first radial hydrostatic bearing 14d. The bearing gas discharge line 18a is configured to discharge the bearing gas which has flowed through the thrust hydrostatic bearings 14b, 14c and the second radial hydrostatic bearing 14a. In the present embodiment, the downstream end of the bearing gas discharge line 18a is joined to a portion of the gas discharge line 18. A third labyrinth seal 32 is provided in a region between the first radial hydrostatic bearing 14d and the first thrust hydrostatic bearing 14c.
[0046] In the present embodiment, the temperature sensor 60 and the first back pressure control valve 80 are provided at the gas discharge line 18. A pressure sensor 100 and a second back pressure control valve 110 are provided at the bearing gas discharge line 18a. By use of the pressure sensor 100 and the second back pressure control valve 110, pressure controls for the hydrostatic gas bearings 14a, 14b, 14c are performed. In addition, a back pressure control independent of the pressure controls for the hydrostatic gas bearings 14a, 14b, 14c is performed only for the first radial hydrostatic bearing 14d located closer to the expansion chamber 21. If the back pressure is excessively increased in the back pressure control, bearing performance is reduced. However, in the present embodiment, only the first radial hydrostatic bearing 14d which is adjacent to the first labyrinth seal 30 and closer to the expansion chamber 21 is controlled, and thus the back pressure control is realized. In addition, the back pressures of the other hydrostatic gas bearings 14a, 14b, 14c can be more flexibly set. In this way, a suitable control can be realized.
[0047] (Embodiment 3)
Next, Embodiment 3 will be described with reference to Fig. 7. Hereinbelow, the same constituents as those of the above-described embodiments will not be described, and only the constituents different from those of the above-described embodiments will be described. [0048] Fig. 7 is a schematic view showing the configuration of an expansion turbine apparatus IB according to Embodiment 3. As shown in Fig. 7, the expansion turbine apparatus IB is different from the expansion turbine apparatus 1 according to Embodiment 1 (Fig. 5) in that the second labyrinth seal 31 is disposed in a region between the first radial hydrostatic bearing 14d and the first thrust hydrostatic bearing 14c. The upstream end of the gas discharge line (mixture gas discharge passage) 18 is connected to the exit of the first radial hydrostatic bearing 14d. The upstream ends of the bearing gas discharge line (bearing gas dedicated discharge passage) 18a are connected to the exit of the first thrust hydrostatic bearing 14c, the exit of the second thrust hydrostatic bearing 14b, and the exit of the second radial hydrostatic bearing 14a. In addition, the pressure sensor 100 and the second back pressure control valve 110 are provided at the bearing gas discharge line 18a. Further, the expansion turbine apparatus IB of the present embodiment includes a gas flow passage 15b, a first end (one end) of which is connected to the braking line 15 and a second end (the other end) of which is connected to the bearing gas discharge line 18a.
[0049] In accordance with the above-described configuration, in addition to the advantages of Embodiment 2, the pressure in the braking line 15, and the back pressures of the thrust hydrostatic bearings 14b, 14c and the second radial hydrostatic bearing 14a can be made uniform by utilizing the gas flow passage 15b. The pressures can be controlled by use of the pressure sensor 100 and the second back pressure control valve 110.
[0050] In addition, in accordance with the above-described configuration, since the second labyrinth seal 31 is disposed in the region between the first radial hydrostatic bearing 14d and the thrust hydrostatic bearing 14c, a distance between the second radial hydrostatic bearing 14a and the expansion chamber 21 can be reduced, and the axial length of the rotary shaft 13 from the second radial hydrostatic bearing 14a to the expansion chamber 21 side can be reduced. As a result, a mass of a rotary member can be reduced, and vibration stability can be improved. [0051] (Embodiment 4)
Next, Embodiment 4 will be described with reference to Fig. 8. Hereinbelow, the same constituents as those of the above-described embodiments will not be described, and only the constituents different from those of the above-described embodiments will be described. [0052] Fig. 8 is a block diagram showing the configuration of an expansion turbine apparatus 1C according to Embodiment 4. As shown in Fig. 8, the expansion turbine apparatus 1C is different from the expansion turbine apparatus 1 according to Embodiment 1 (Fig. 5) in that the upstream end of the gas discharge line 18 is connected to only the exit of the first radial hydrostatic bearing 14d, the exit being closer to the expansion chamber, and the upstream ends of the bearing gas discharge line 18a are connected to the exit of the first radial hydrostatic bearing 14d, the exit being closer to the braking gas chamber, the exits of the thrust hydrostatic bearings 14b, 14c, and the exit of the second radial hydrostatic bearing 14a. The gas discharge line 18 discharges a mixture gas containing the bearing gas having been discharged to a region closer to the expansion chamber, through the clearance of the first radial hydrostatic bearing 14d, and the refrigerant gas having leaked from the expansion chamber 21 to the bearing chamber 23 through the first labyrinth seal 30.
[0053] In accordance with this configuration, the back pressure control is performed only for the exit of the first radial hydrostatic bearing 14d closest to the first labyrinth seal 30, the exit being closer to the expansion chamber. This makes it possible to effectively suppress temperature decrease due to the low-temperature gas which leaks. In addition, the back pressure can be flexibly set, and a suitable control can be realized.
[0054] Numerous modifications and alternative embodiments of the present invention will be apparent to those skilled in the art in view of the foregoing description. Accordingly, the description is to be construed as illustrative only, and is provided for the purpose of teaching those skilled in the art the best mode of conveying out the invention. The details of the structure and/or function may be varied substantially without departing from the spirit of the invention.
Industrial Applicability [0055] The present invention is effectively used in an expansion turbine including hydrostatic gas bearings.
Claims (4)
1. An expansion turbine apparatus including:
a body formed with an expansion chamber, a braking gas chamber, and a shaft insertion hole inside the body, the shaft insertion hole being provided in such a manner that the expansion chamber and the braking gas chamber are in communication with each other via the shaft insertion hole and a rotary shaft is insertable into the shaft insertion hole;
a turbine impeller accommodated in the expansion chamber to expand a refrigerant gas;
a brake impeller which is accommodated in the braking gas chamber, and braked by a braking gas with the same kind as that of the refrigerant gas;
the rotary shaft inserted into the shaft insertion hole with a clearance between the rotary shaft and the shaft insertion hole, the turbine impeller being provided at a first end portion of the rotary shaft, the brake impeller being provided at a second end portion of the rotary shaft;
a hydrostatic gas bearing which is provided in a bearing chamber formed inside the shaft insertion hole and supports the rotary shaft in such a manner that the rotary shaft is rotatable, by a static pressure of a bearing gas with the same kind as that of the refrigerant gas supplied from an entrance and discharged from an exit;
a first labyrinth seal provided in a region between an end of the bearing chamber, the end being closer to the expansion chamber, and a portion of the bearing chamber at which the hydrostatic gas bearing is disposed;
a mixture gas discharge passage which discharges a mixture gas containing the bearing gas and the refrigerant gas which has leaked from the expansion chamber to the bearing chamber through the first labyrinth seal;
a first back pressure control valve provided at the mixture gas discharge passage to control a back pressure of the hydrostatic gas bearing;
a temperature sensor provided at the mixture gas discharge passage to measure a temperature of the mixture gas; and a controller which controls the first back pressure control valve so that the back pressure of the hydrostatic gas bearing is increased, in a case where the temperature of the mixture gas flowing through the mixture gas discharge passage is reduced.
2. The expansion turbine apparatus according to claim 1, wherein the hydrostatic gas bearing includes a first radial hydrostatic bearing and a second radial hydrostatic bearing which support the rotary shaft in a radial direction in such a manner that the rotary shaft is rotatable, and a thrust hydrostatic bearing which supports the rotary shaft in an axial direction in such a manner that the rotary shaft is rotatable, wherein the first radial hydrostatic bearing, the thrust hydrostatic bearing, and the second radial hydrostatic bearing are disposed in this order inside the bearing chamber, in a direction from the expansion chamber toward the braking gas chamber, wherein the first labyrinth seal is provided in a region between the end of the bearing chamber, the end being closer to the expansion chamber, and a portion of the bearing chamber at which the first radial hydrostatic bearing is disposed, wherein an upstream end of the mixture gas discharge passage is connected to an exit of the first radial hydrostatic bearing, and wherein upstream ends of a bearing gas dedicated discharge passage are connected to an exit of the thrust hydrostatic bearing, and an exit of the second radial hydrostatic bearing.
3. The expansion turbine apparatus according to claim 1, wherein the hydrostatic gas bearing includes a first radial hydrostatic bearing and a second radial hydrostatic bearing which support the rotary shaft in a radial direction in such a manner that the rotary shaft is rotatable, and a thrust hydrostatic bearing which supports the rotary shaft in an axial direction in such a manner that the rotary shaft is rotatable, and wherein the first radial hydrostatic bearing, the thrust hydrostatic bearing, and the second radial hydrostatic bearing are disposed in this order inside the bearing chamber, in a direction from the expansion chamber toward the braking gas chamber, the expansion turbine apparatus further including:
a second labyrinth seal provided in a region between the first radial hydrostatic bearing and the thrust hydrostatic bearing in the bearing chamber;
a bearing gas dedicated discharge passage, upstream ends of which are connected to an exit of the thrust hydrostatic bearing and an exit of the second radial hydrostatic bearing;
a second back pressure control valve provided at the bearing gas dedicated discharge passage to control a back pressure of the thrust hydrostatic bearing and a back pressure of the second radial hydrostatic bearing;
a braking line, a first end of which is connected to an exit of the braking gas chamber and a second end of which is connected to an entrance of the braking gas chamber; and a gas flow passage, a first end of which is connected to the braking line and a second end of which is connected to the bearing gas dedicated discharge passage.
4. The expansion turbine apparatus according to claim 1, wherein the hydrostatic gas bearing includes a first radial hydrostatic bearing and a second radial hydrostatic bearing which support the rotary shaft in a radial direction in such a manner that the rotary shaft is rotatable, and a thrust hydrostatic bearing which supports the rotary shaft in an axial direction in such a manner that the rotary shaft is rotatable, wherein the first radial hydrostatic bearing, the thrust hydrostatic bearing, and the second radial hydrostatic bearing are disposed in this order inside the bearing chamber, in a direction from the expansion chamber toward the braking gas chamber, wherein the first labyrinth seal is provided in a region between the end of the bearing chamber, the end being closer to the expansion chamber, and a portion of the bearing chamber at which the first radial hydrostatic bearing is disposed, wherein an upstream end of the mixture gas discharge passage is connected to an exit of the first radial hydrostatic bearing, the exit being closer to the expansion chamber, and wherein upstream ends of a bearing gas dedicated discharge passage are connected to an exit of the first radial hydrostatic bearing, the exit being closer to the braking gas chamber, an exit of the thrust hydrostatic bearing, and an exit of the second radial hydrostatic bearing.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2015-123768 | 2015-06-19 | ||
| JP2015123768A JP6526492B2 (en) | 2015-06-19 | 2015-06-19 | Expansion turbine device |
| PCT/JP2016/002899 WO2016203767A1 (en) | 2015-06-19 | 2016-06-15 | Expansion turbine device |
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| AU2016280924A1 AU2016280924A1 (en) | 2018-01-25 |
| AU2016280924B2 true AU2016280924B2 (en) | 2019-01-31 |
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| AU2016280924A Active AU2016280924B2 (en) | 2015-06-19 | 2016-06-15 | Expansion turbine device |
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| JP (1) | JP6526492B2 (en) |
| CN (1) | CN107636259B (en) |
| AU (1) | AU2016280924B2 (en) |
| WO (1) | WO2016203767A1 (en) |
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| JP7048258B2 (en) | 2017-10-27 | 2022-04-05 | 川崎重工業株式会社 | Expansion turbine |
| JP6985886B2 (en) * | 2017-10-27 | 2021-12-22 | 川崎重工業株式会社 | Gas expansion system |
| US10422373B1 (en) * | 2018-04-04 | 2019-09-24 | General Electric Company | Machine thrust bearing assembly |
| DE102019127456A1 (en) * | 2019-10-11 | 2021-04-15 | Atlas Copco Energas Gmbh | Method for operating a turbo machine |
| CN111365080B (en) * | 2020-03-09 | 2022-07-26 | 浙江省能源集团有限公司 | Natural gas static pressure air bearing two-stage expansion generator and power generation system |
| FR3114870B1 (en) * | 2020-10-05 | 2022-12-16 | Air Liquide | Installation and process for refrigeration and/or liquefaction of a fluid |
| CN113503368B (en) * | 2021-08-23 | 2022-09-16 | 蒋雪莲 | Abrasion-free soft sealing butterfly valve |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US3038318A (en) * | 1957-06-07 | 1962-06-12 | Sulzer Ag | Expansion turbine and turbocompressor connected therewith in a cold producing plant |
| US3105631A (en) * | 1961-08-15 | 1963-10-01 | Sulzer Ag | Expansion turbine having a gas bearing |
| JPH06101498A (en) * | 1992-09-18 | 1994-04-12 | Hitachi Ltd | Magnetic bearing type turbine compressor |
| JPH07259855A (en) * | 1994-03-17 | 1995-10-09 | Hitachi Ltd | Gas bearing turbine with thrust balance chamber |
| JP5824229B2 (en) * | 2011-04-08 | 2015-11-25 | 川崎重工業株式会社 | Liquefaction system |
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| JP2017008775A (en) | 2017-01-12 |
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| WO2016203767A1 (en) | 2016-12-22 |
| JP6526492B2 (en) | 2019-06-05 |
| AU2016280924A1 (en) | 2018-01-25 |
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