CN103649465B - radial gas expander - Google Patents
radial gas expander Download PDFInfo
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- CN103649465B CN103649465B CN201280033725.XA CN201280033725A CN103649465B CN 103649465 B CN103649465 B CN 103649465B CN 201280033725 A CN201280033725 A CN 201280033725A CN 103649465 B CN103649465 B CN 103649465B
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- Prior art keywords
- stream
- support member
- impeller
- gas
- running shaft
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/12—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines with repeated action on same blade ring
- F01D1/14—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines with repeated action on same blade ring traversed by the working-fluid substantially radially
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
- F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
- F01D5/048—Form or construction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Measuring Volume Flow (AREA)
Abstract
This radial gas expander (1) possesses: running shaft (3); Impeller (4), it is fixed on running shaft (3); Housing (2), running shaft (3) supports as rotating by it, and be formed with the importing stream (20a) importing fluid to impeller (4), the nozzle wing (24) and support member (25) is provided with at this importing stream (20a), the nozzle wing (24) guides the fluid flowing into impeller (4), support member (25) is arranged on the upstream side of the nozzle wing (24), and support between the mutually opposing wall of importing stream (20a), support member (25) is formed as wing when analysing and observe observation.
Description
Technical field
The present invention relates to a kind of radial gas expander (radial flow gas decompressor) formed with multi-level approach arrangement impeller on single axle.The application based on 09 01st, 2011 spy to Japanese publication former No. 2011-190525 and CLAIM OF PRIORITY, and here cites its content.
Background technique
Gas expander uses based on following object, namely, by sucking the gas of high pressure of discharging from equipment side, and make it expand and make the pressure energy of gas convert speed to (mechanical energy) power to be reclaimed, thus the power of drive motor etc. is reduced.
In recent years, since, a kind of gas expander of tackling more high pressure energy has been required.As this gas expander, the known radial gas expander that the form of multiple impeller is set with multi-level approach.As an example of radial gas expander, the radial gas expander (for example, referring to patent documentation 1) of the gear type (overdrive gear formula) that known booster engine, the multiple impellers be configured on pinion shaft be made up of the small gear comprising actuation gear and engage with actuation gear are formed.
And, also arrange multiple impeller between known bearing on single axle and make these impellers be built in radial gas expander in single housing.No matter whether the radial gas expander that this single axle is arranged with multiple impeller possess multi-stage impeller, as long as axle is single axle.Therefore, high-pressure sealing ring can be made compared with radial gas expander of gear type etc., High Pressure Shell realizes minimum number, even if thus the high radial gas expander of reliability (for example, referring to patent documentation 2) also can be realized under the condition of more high pressure.
As shown in Figures 5 and 6, radial gas expander 101 in the past multiple impellers 4 of possessing housing 2, being rotatably arranged on the running shaft 3 of housing 2, being fixed on running shaft 3.
Radial gas expander 101 has therein for making two gas expansions of gas expansion interval 105a, 105b.Housing 2 comprises housing body 6, is built in housing body 6 and the barrier film group 7 be made up of the multiple barrier films integrally linked.Gas expansion interval 105a, 105b will be formed with multiple barrier films 8,9a, 9b, 10a, 10b, 11a, 11b, 12a, 12b, 13a, 13b connection of the close pattern bend linked by inter-stage in the axial direction.
Gas expansion interval 105a, 105b have: the gas be communicated with suction port 18a, 18b of housing 2 according to each interval imports stream 120a, 120b; The gas be communicated with ejiction opening 19a, 19b of housing 2 according to each interval flows out stream 21a, 21b.
Wherein, gas import stream 120a, 120b delimit in the barrier film 8 of the central authorities of the central authorities being arranged on two gas expansions interval 105a, 105b and the multiple barrier films except the barrier film 8 of these central authorities near central authorities between barrier film 9a, 9b.
And, import upstream side on stream 120, impeller 4 at this gas and be provided with the nozzle wing 24 generating the air-flow corresponding with the profile of impeller 4.
In the radial gas expander 101 of said structure, never the gas that illustrated equipment imports via suction port 18a is after the interval 105a of the gas expansion of a side expands, import the interval 105b of gas expansion of the opposing party via gas pipe arrangement 22 and suction port 18b, thus expand further.
But in radial gas expander 101 in the past, import the flow path width of stream 120a and gas importing stream 120b in order to ensure gas, the upstream side importing the nozzle wing 24 of stream 120a, 120b at gas is provided with spacer element 125.
[at first technical paper]
[patent documentation]
Patent documentation 1: Japan Patent No. 3457828 publication
Patent documentation 2: Japanese Unexamined Patent Publication 2011-43070 publication
[inventing the problem that will solve]
But, because spacer element 125 is arranged on the upstream side of the nozzle wing 24, therefore there is the problem of the flowing of the gas of the disorderly flow nozzle wing 24.As shown in Figure 6, when disorder, loss is produced when the flow nozzle wing 24 because of spacer element 125 at the streamline L of the gas imported.And import near the entrance of stream 120a, 120b because spacer element is arranged on gas, the reduction effect therefore utilizing the importing flow path width of differential pressure to change is little.Therefore, the change because of flow path width causes gas flow rate to change, and does not reach desired gas flow rate when the flow nozzle wing 24, thus produces loss.Like this, spacer element 125 hinders the expansion character of impeller 4, and then causes the hydraulic performance decline of radial gas expander 101.
Summary of the invention
The present invention completes in light of this situation, and its object is to provides a kind of radial gas expander that can obtain desired performance.And, the object of the present invention is to provide and a kind ofly can guarantee that gas imports the flow path width of stream 120a, 120b and can prevent the radial gas expander of distortion of wall of the barrier film forming housing.
[for solving the mode of problem]
In order to realize above-mentioned object, the invention provides following mode.
Radial gas expander involved by the 1st aspect of the present invention possesses: running shaft; Impeller, it is fixed on described running shaft; Housing, described running shaft supports as rotating by it, and is formed with the importing stream importing fluid to described impeller.And described importing stream is provided with the nozzle wing and support member, and the described nozzle wing guides the fluid flowing into described impeller, and described support member is arranged on the upstream side of the described nozzle wing, and supports between the mutually opposing wall of described importing stream.In addition, described support member is formed as wing when analysing and observe observation.
According to this structure, by support member, the distance from the lower end of the mutually opposing wall of the importing stream be arranged in housing to supporting point is shortened, thus the amount of deformation of opposed wall can be reduced, and desired flow path width can be guaranteed.And, because support member is formed as wing when analysing and observe observation, therefore, it is possible to prevent the situation of the movement disorder of the fluid making the flow nozzle wing.
And the radial gas expander involved by the 2nd aspect of the present invention possesses: running shaft; Two groups of impeller sets, it is made up of the impeller being fixed on described running shaft respectively, and is symmetrical arranged in the axial direction; Housing, described running shaft supports as rotating by it, and be formed with the first importing stream and second and import stream, described first imports stream imports fluid to first group of impeller sets, described second importing stream and described first imports stream and is disposed adjacent, and imports the fluid from described first group of impeller sets ejection to second group of impeller sets.And, import stream described second and be provided with the nozzle wing and support member, the described nozzle wing guides the fluid flowing into described impeller, described support member is arranged on the upstream side of the described nozzle wing, and support between the mutually opposing wall of described second importing stream, described support member is formed as wing when analysing and observe observation.
According to this structure, can import in stream and the second importing stream first and guarantee desired flow path width.And, when the pressure difference that inflow first imports the fluid of stream and the fluid of inflow second importing stream is large, also can reduce by support member the amount of deformation importing the mutually opposing wall of stream with median wall and second, and because support member is formed as wing when analysing and observe observation, therefore, it is possible to prevent the situation of the movement disorder of the fluid making the flow nozzle wing.
And, in the 3rd aspect of the present invention, described support member arranges multiple around described running shaft, and is formed as making the radially equal mode of described support member width each other along with from outer radial periphery side towards inner circumferential side, width be narrowed gradually.
According to this structure, can make by the fluid of the surrounding of support member not speedup and import the nozzle wing swimmingly.
And in the 4th aspect of the present invention, described housing has: housing body, be built in described housing body and the multiple barrier films integrally linked, described importing stream is formed at described multiple barrier film.
According to this structure, can assemble by the easier housing to being incorporated with the nozzle wing and the support member that is formed as wing.And, easily can carry out inner maintenance.
[invention effect]
According to the present invention, can provide and can obtain desired performance and the radial gas expander that can reduce the amount of deformation of the wall of the barrier film forming housing.
Accompanying drawing explanation
The sectional view of the radial gas expander of Fig. 1 involved by embodiments of the present invention.
Fig. 2 is the A portion enlarged view of Fig. 1.
Fig. 3 is the B direction view of Fig. 2.
Fig. 4 represents the figure at the streamline of the gas of support fins perimeter.
Fig. 5 is the sectional view of radial gas expander in the past.
Fig. 6 is the C direction view of Fig. 5, and for representing the figure at the streamline of the gas of spacer element perimeter.
Embodiment
With reference to accompanying drawing, embodiments of the present invention are described in detail.
As shown in Figures 1 and 2, the radial gas expander 1 involved by embodiments of the present invention possesses: the housing 2 of tubular; Housing 2 can be bearing in rotatably and at the running shaft 3 axially extended of housing 2; Be fixed on the multiple impellers 4 on running shaft 3.
In addition, in the following description, be described with the axial consistent of running shaft 3 with the axis of housing 2.And, only the axis of the axis of housing 2 and running shaft 3 is called axis.
Radial gas expander 1 possesses two intervals for expanding gas therein.That is, radial gas expander 1 possesses two gas expansions interval 5a, 5b of being made up of the interval 5a of the gas expansion being configured in the first axial side and the interval 5b of the gas expansion being configured in the second axial side.
The radial gas expander 1 of present embodiment possesses following structure, namely, rotary driving force is obtained by the gas importing the interval 5a of the first gas expansion, and the gas after expanding discharging from the interval 5a of the first gas expansion imports the interval 5b of the second gas expansion, obtains rotary driving force further.
Housing 2 has housing body 6, is arranged at the barrier film group 7 of the inside of housing body 6.Barrier film group 7 is made up of 11 barrier films 8,9a, 9b, 10a, 10b, 11a, 11b, 12a, 12b, 13a, the 13b connected in the mode that can axially extract.
The interval 5a of first gas expansion has the barrier film 8 being configured at central authorities and barrier film 9a, 10a, 11a, 12a, 13a of being connected with described the first axial side relative to barrier film 8.And the interval 5b of the second gas expansion has the barrier film 8 being configured at central authorities and barrier film 9b, 10b, 11b, 12b, 13b of being connected with described the second axial side relative to barrier film 8.
That is, two gas expansions interval 5a, 5b have as the structural element shared, central barrier film 8.
Be formed for the suction port 18a to the first gas expansion interval 5a importing gas, for importing the suction port 18b of gas to the interval 5b of the second gas expansion in housing body 6.
And, be formed for the ejiction opening 19a from the first gas expansion interval 5a ejection gas, for spraying the ejiction opening 19b of gas from the interval 5b of the second gas expansion in housing body 6.
In addition, the ejiction opening 19a of the interval 5a side of the first gas expansion and the suction port 18b of the interval 5b side of the second gas expansion is connected by gas pipe arrangement 22.
The middle ground configuration of the through barrier film group 7 of running shaft 3.The two end part of this running shaft 3 via bearing 15 using the mode that can rotate be bearing in two gas expansions interval 5a, 5b, also as barrier film 13a, 13b of respective end plate.And, the inner peripheral portion of barrier film 13a, 13b of the inner side being positioned at each bearing 15 is provided with dry gas seals part 16.
Multiple impeller 4 is fixed on running shaft 3, and the level Four impeller 4 forming the interval 5a of the first gas expansion and the level Four impeller 4 forming the interval 5b of the second gas expansion oppositely arrange each other.
Herein, for each impeller 4, when the opening towards outer radial periphery side being set to suction port 41, when the opening towards axis is set to ejiction opening 42, the level Four impeller 4 forming the interval 5a of the first gas expansion and the level Four impeller 4 forming the interval 5b of the second gas expansion configure in the mode of the side with suction port 41 towards the barrier film 8 of central authorities.That is, the impeller 4 forming the interval 5a of the first gas expansion configures in the mode of ejiction opening 42 towards the first side of axis, and the impeller 4 forming the interval 5b of the second gas expansion configures in the mode of ejiction opening 42 towards the second side of axis.
In addition, identical symbol is marked to multiple impeller 4, but the size of multiple impeller 4 is different.Specifically, multiple impeller 4 is to adapt to the mode of the expansion stroke of gas to change size.
Central authorities barrier film 8 and its both sides be formed between barrier film 9a, 9b be communicated with suction port 18a, 18b respectively first import stream 20a and second and import stream 20b.That is, first of the interval 5a of the first gas expansion import that stream 20a is formed at the barrier film 8 of central authorities between the wall 81 of the first side and the wall 91 of second side of barrier film 9a.And, second of the interval 5b of the second gas expansion import that stream 20b is formed at the barrier film 8 of central authorities between the wall 82 of the second side and the wall 92 of first side of barrier film 9b.
Thus, the first importing stream 20a and second imports stream 20b and is adjacent to configuration across the barrier film 8 of central authorities.
Equally, also as barrier film 13a, 13b of end plate with adjacent be formed with derivation stream 21a, 21b of being communicated with above-mentioned ejiction opening 19a, 19b respectively between barrier film 12a, 12b with them.
Wherein the derivation stream 21a of the interval 5a of the first gas expansion is communicated with the ejiction opening 19a of housing body 6, and the derivation stream 21b of the interval 5b of the second gas expansion is communicated with the ejiction opening 19b of housing body 6.
Each first impeller 4 upstream side imported in stream 20a and second importing stream 20b is provided with the multiple nozzle wings 24 guided to the inflow of impeller 4 to gas.In the present embodiment, 17 nozzle wings 24 are provided with.
As shown in Figure 3, the nozzle wing 24 in the circumferential direction equally spaced arrange.The so-called wing being formed as leading edge circle trailing edge point from section shape during end on observation of each nozzle wing 24.And the leading edge of the nozzle wing 24 is configured in circumferential direction outer circumferential side, and trailing edge is configured in circumferential direction inner circumferential side, and trailing edge tiltedly configures to the inclination of sense of rotation R direct of travel relative to leading edge in the mode of the sense of rotation R along running shaft 3.That is, in the flow direction upstream side configuration front end and in configuration rear end, downstream side of gas.
And the section shape of the nozzle wing 24 such as utilizes numerical value fluid mechanics (CFD) parsing to determine.Therefore, the section shape of the nozzle wing 24 of present embodiment is formed as relative to the center line of the flow direction (hereinafter referred to as grain direction) along gas is unsymmetrical.That is, the nozzle wing 24 has the shape as the flowing of gas imported swimmingly impeller 4, to promote the effect making gas expansion speedup in impeller 4.
The more outer circumferential side of the nozzle wing 24 is provided with multiple (17) support fins 25 as support member.Support fins 25 is same with the nozzle wing 24, in the circumferential direction equally spaced arrange.The so-called aerofoil profile being formed as leading edge circle trailing edge point from the section shape of end on observation of each support fins 25.And the leading edge of support fins 25 is configured in circumferential direction outer circumferential side, and trailing edge is configured in circumferential direction inner circumferential side, and trailing edge tiltedly configures to the inclination of sense of rotation R direct of travel relative to leading edge in the mode along sense of rotation R.That is, for support fins 25, in grain direction upstream side configuration front end, in configuration rear end, downstream side.
And the shape of support fins 25 is formed as making support fins 25 width W each other in the grain direction mode that namely radial direction is roughly equal, makes width narrow gradually along with from outer radial periphery side towards inner circumferential side.
In addition, the section shape of support fins 25 is different from the nozzle wing 24, forms symmetric figure relative to the center line along grain direction.For the shape of support fins 25, the position of circumference and the position of radial direction, in order to not affect the gas of the importing nozzle wing 24 as far as possible, still utilize CFD etc. to determine, be particularly preferably set to the shape along streamline.And, in order to the impact of flow line to be controlled, in less (make streamline not disorderly) scope, preferably shorten the length of grain direction as far as possible.And the flow due to gas causes streamline to change, therefore preferably suitably to determine according to service condition.
It is the close pattern bend (intermediate flow passage) 27 of U-shaped that barrier film 9a, 10a, 11a, 12a and 9b in the centre of each gas expansion interval 5a, 5b, 10b, 11b, 12b are formed the section that the ejiction opening 42 of the impeller 4 of prime is connected with the suction port 41 of the impeller 4 of rear class.These close pattern bends 27 are provided with the nozzle wing 24 of the upstream side being configured in impeller 4 and are set to 17 reflux blades 28 of the good air-flow of efficiency for the air-flow of the suction port 41 by the impeller 4 to rear class.
The action of the radial gas expander 1 of said structure is described.First, the gas of High Temperature High Pressure is imported into the interval 5a of the first gas expansion from the equipment of regulation via suction port 18a.Gas repeatedly carries out suction, the expansion of gas in the interval 5a of the first gas expansion by level Four impeller 4 points of four-stages, and sprays from ejiction opening 19a.Next, gas imports the interval 5b of the second gas expansion via gas pipe arrangement 22 and suction port 18b, expands, and spray from ejiction opening 19b at the interval 5b of the second gas expansion.
In the inside of two gas expansions interval 5a, 5b, the gas of inflow flows in the axial direction.Wherein, according to said structure, gas flows to mutual opposite direction.That is, gas moves from the second side direction first effluent of axis at the interval 5a of gas expansion.And gas moves from the first side direction second effluent of axis at the interval 5b of gas expansion.
Herein, with import the pressure of the gas of the first importing stream 20a via suction port 18a compared with, the pressure importing the gas of the second importing stream 20b via suction port 18b is lower.That is, across barrier film 8, the adjacent first pressure and second imported in stream 20a imports the pressure difference change of the pressure in stream 20b greatly.
According to above-mentioned mode of execution, even if the pressure difference importing the pressure in stream 20b at the first pressure and second imported in stream 20a is large, and to the barrier film 8 being formed at the central authorities that the first importing stream 20a and second imports between stream 20b be applied with make this barrier film 8 be out of shape such power when, can amount of deformation be reduced by being provided with support fins 25.And support fins 25 is formed as wing when analysing and observe observation, as shown in Figure 4, the disorder of the streamline L of the gas of the perimeter of support fins 25 can be reduced in.
And, support fins 25 with make the radially equal mode of support fins 25 width W each other along with from outer radial periphery side direction inner circumferential side, width is narrowed gradually formed, can make thus by the gas of the surrounding of support fins 25 not speedup and import the nozzle wing 24 swimmingly.
And, because support fins 25 is relative to grain direction symmetrically shape, therefore, it is possible to more easily manufacture.
And, because the multiple barrier film groups 7 forming housing 2 can be split in the axial direction, therefore, it is possible to easily carry out inner maintenance.
In addition, technical scope of the present invention is not limited to above-mentioned mode of execution, without departing from the spirit and scope of the invention, can apply various change.Such as, also support fins 25 can be set to relative to grain direction is asymmetrical shape.
Industrial utilizability
According to radial gas expander of the present invention, desired performance can be obtained, and the amount of deformation of the wall of the barrier film forming housing can be reduced.
Reference numeral explanation
1-radial gas expander
2-housing
3-running shaft
4-impeller
5-gas expansion is interval
6-housing body
7-barrier film group
8,9a, 9b, 10a, 10b, 11a, 11b, 12a, 12b, 13a, 13b-barrier film
20a-the first imports stream (importing stream)
20b-the second imports stream (importing stream)
24-nozzle wing
25-support fins (support member)
27-close pattern bend
28-reflux blade
Claims (3)
1. a radial gas expander, wherein, possesses:
Running shaft;
Impeller, it is fixed on described running shaft;
Housing, described running shaft supports as rotating by it, and is formed with the importing stream importing fluid to described impeller,
Described importing stream is provided with the nozzle wing and support member, the fluid that impeller described in described nozzle wing subtend flows into guides, described support member is arranged on the upstream side of the described nozzle wing, and supports between the mutually opposing wall of described importing stream
Described support member is formed as wing when analysing and observe observation,
Described support member arranges multiple around described running shaft, and is formed as making the radially equal mode of described support member width each other along with from outer radial periphery side towards inner circumferential side, width be narrowed gradually.
2. a radial gas expander, wherein, possesses:
Running shaft;
Two groups of impeller sets, it is made up of the impeller being fixed on described running shaft respectively, and is symmetrical arranged in the axial direction;
Housing, described running shaft supports as rotating by it, and be formed with the first importing stream and second and import stream, described first imports stream imports fluid to first group of impeller sets, described second importing stream and described first imports stream and is disposed adjacent, and described second imports stream imports the fluid sprayed from described first group of impeller sets to second group of impeller sets
Import stream described second and be provided with the nozzle wing and support member, described in described nozzle wing subtend, the fluid of second group of impeller sets inflow guides, described support member is arranged on the upstream side of the described nozzle wing, and supports between the mutually opposing wall of described second importing stream
Described support member is formed as wing when analysing and observe observation,
Described support member arranges multiple around described running shaft, and is formed as making the radially equal mode of described support member width each other along with from outer radial periphery side towards inner circumferential side, width be narrowed gradually.
3. radial gas expander as claimed in claim 1 or 2, wherein,
Described housing has: housing body; Be built in described housing body and the multiple barrier films integrally linked,
Described importing stream is formed at described multiple barrier film each other.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2011190525A JP5959816B2 (en) | 2011-09-01 | 2011-09-01 | Radial gas expander |
| JP2011-190525 | 2011-09-01 | ||
| PCT/JP2012/050165 WO2013031244A1 (en) | 2011-09-01 | 2012-01-06 | Radial gas expander |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103649465A CN103649465A (en) | 2014-03-19 |
| CN103649465B true CN103649465B (en) | 2016-02-10 |
Family
ID=47755770
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280033725.XA Expired - Fee Related CN103649465B (en) | 2011-09-01 | 2012-01-06 | radial gas expander |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20140126994A1 (en) |
| JP (1) | JP5959816B2 (en) |
| CN (1) | CN103649465B (en) |
| DE (1) | DE112012003648T5 (en) |
| WO (1) | WO2013031244A1 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105579686B (en) | 2013-06-28 | 2018-02-23 | 埃克森美孚上游研究公司 | Utilize the system and method for axially stream expanding machine |
| US10036265B2 (en) | 2013-06-28 | 2018-07-31 | Mitsubishi Heavy Industries Compressor Corporation | Axial flow expander |
| CN103993914A (en) * | 2014-05-23 | 2014-08-20 | 马鞍山市晨光高耐磨科技发展有限公司 | Stator steam inlet structure of run-off type steam turbine |
| WO2016127731A1 (en) * | 2015-02-15 | 2016-08-18 | 靳北彪 | Inter-pressure impeller mechanism |
| IT201800002047A1 (en) * | 2018-01-26 | 2019-07-26 | Nuovo Pignone Tecnologie Srl | A MULTI-STAGE RADIAL TURBOEXPANT |
| JP7345383B2 (en) | 2018-01-31 | 2023-09-15 | 株式会社クボタ | rice transplanter |
| JP7493346B2 (en) | 2020-02-03 | 2024-05-31 | 三菱重工コンプレッサ株式会社 | Rotating Machinery |
| CN112377269B (en) * | 2021-01-11 | 2021-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Anti-distortion stator design method suitable for contra-rotating lift propulsion device |
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- 2012-01-06 DE DE112012003648.4T patent/DE112012003648T5/en not_active Withdrawn
- 2012-01-06 US US14/125,990 patent/US20140126994A1/en not_active Abandoned
- 2012-01-06 WO PCT/JP2012/050165 patent/WO2013031244A1/en active Application Filing
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| JPS63147903A (en) * | 1986-12-09 | 1988-06-20 | Isuzu Motors Ltd | Turbine casing structure |
| CN1692214A (en) * | 2002-10-18 | 2005-11-02 | 三菱重工业株式会社 | Exhaust turbocharger with the variable-nozzle mechanism, and its manufacturing method |
| CN101575990A (en) * | 2008-05-05 | 2009-11-11 | 霍尼韦尔国际公司 | Turbocharger with variable nozzle having vane sealing surfaces |
| JP2011043070A (en) * | 2009-08-19 | 2011-03-03 | Mitsubishi Heavy Industries Compressor Corp | Radial gas expander |
Also Published As
| Publication number | Publication date |
|---|---|
| JP5959816B2 (en) | 2016-08-02 |
| DE112012003648T5 (en) | 2014-08-28 |
| US20140126994A1 (en) | 2014-05-08 |
| CN103649465A (en) | 2014-03-19 |
| JP2013053530A (en) | 2013-03-21 |
| WO2013031244A1 (en) | 2013-03-07 |
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