CN103649465A - Radial gas expander - Google Patents
Radial gas expander Download PDFInfo
- Publication number
- CN103649465A CN103649465A CN201280033725.XA CN201280033725A CN103649465A CN 103649465 A CN103649465 A CN 103649465A CN 201280033725 A CN201280033725 A CN 201280033725A CN 103649465 A CN103649465 A CN 103649465A
- Authority
- CN
- China
- Prior art keywords
- stream
- impeller
- gas
- support member
- running shaft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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) is provided with a rotating shaft (3), an impeller (4) which is affixed to the rotating shaft (3), and a casing (2) by which the rotating shaft (3) is supported in a rotatable manner and which has formed therein an introduction flow path (20a) for introducing fluid into the impeller (4). The introduction flow path (20a) is provided with: nozzle blades (24) which guide fluid which is caused to flow into the impeller (4); and support members (25) which are provided upstream of the nozzle blades (24) and which are provided between the opposing wall surfaces of the introduction flow path (20a) so as to support the opposing wall surfaces. The support members (25) have a wing shape in a cross-section thereof.
Description
Technical field
The present invention relates to a kind of radial gas expander (radial flow gas decompressor) of arranging impeller in multistage mode and form on single axle.The application former No. 2011-190525 and advocate preference based on 09 01st, 2011 spy to Japanese publication, and here cite its content.
Background technique
The object of gas expander based on following and using,, by sucking the gas of the high pressure of discharging from equipment side, and make its expansion and make the pressure energy of gas convert speed to (mechanical energy) to reclaim power, thereby the power of drive motor etc. is reduced.
In recent years, since, required a kind of more gas expander of high pressure energy of tackling.As this gas expander, the known radial gas expander that the form of a plurality of impellers is set in multistage mode.An example as radial gas expander, known by comprising actuation gear and the booster engine forming with the small gear of actuation gear engagement, be configured in the radial gas expander (for example,, with reference to patent documentation 1) of the gear type (overdrive gear formula) that a plurality of impellers on pinion shaft form.
And, also between known bearing on single axle, arrange a plurality of impellers and make these impellers be built in the radial gas expander in single housing.No matter whether the radial gas expander that is arranged with a plurality of impellers on this single axle possess multi-stage impeller, as long as axle is single axle.Therefore, compare and can make high-pressure sealing ring, High Pressure Shell realize minimum number with radial gas expander of gear type etc., thereby even also can realize the radial gas expander that reliability is high (for example,, with reference to patent documentation 2) under the condition of high pressure more.
As shown in Figures 5 and 6, radial gas expander 101 in the past possesses the running shaft 3 that housing 2, rotation be arranged on housing 2 freely, a plurality of impellers 4 that are fixed on running shaft 3.
Radial gas expander 101 within it portion has for making two gas expansions interval 105a, the 105b of gas expansion.Housing 2 comprises housing body 6, be built in housing body 6 and barrier film group 7 that a plurality of barrier films of being linked by one form.Gas expansion interval 105a, 105b connect a plurality of barrier films 8,9a, 9b, 10a, 10b, 11a, 11b, 12a, 12b, 13a, the 13b that are formed with the close pattern bend that inter-stage is linked in the axial direction.
Gas expansion interval 105a, 105b have: according to each interval, import stream 120a, 120b with the suction port 18a of housing 2, the gas that 18b is communicated with; According to each interval, flow out stream 21a, 21b with the ejiction opening 19a of housing 2, the gas that 19b is communicated with.
Wherein, gas imports stream 120a, 120b and delimit and be arranged on the central central barrier film 8 of two gas expansions interval 105a, 105b and leaning between ectocentral barrier film 9a, 9b most in a plurality of barrier films central barrier film 8 except this.
And, at this gas, import upstream side on stream 120, impeller 4 and be provided with the nozzle wing 24 generating with the air-flow of the contour correspondence 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 a side the interval 105a of gas expansion expands, via gas pipe arrangement 22 and suction port 18b, import the opposing party's the interval 105b of gas expansion, thereby expand further.
Yet, in radial gas expander 101 in the past, in order to ensure gas, importing the flow path width of stream 120a and gas importing stream 120b, the upstream side that imports the nozzle wing 24 of stream 120a, 120b at gas is provided with spacer element 125.
[formerly technical paper]
[patent documentation]
Patent documentation 1: No. 3457828 communique of Japan Patent
Patent documentation 2: TOHKEMY 2011-43070 communique
[problem that invention will solve]
But, because spacer element 125 is arranged on the upstream side of the nozzle wing 24, so there is the mobile problem of the gas of the disorderly flow nozzle wing 24.As shown in Figure 6, in the situation that the streamline L of the gas importing is disorderly because of spacer element 125, when the flow nozzle wing 24, produce loss.And because spacer element is arranged near the entrance that gas imports stream 120a, 120b, the reduction effect of therefore utilizing the importing flow path width of differential pressure to change is little.Therefore, because the variation of flow path width causes gas flow rate, change, when the flow nozzle wing 24, do not reach desired gas flow rate, thereby produce loss.Like this, spacer element 125 has hindered 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 is for what complete in light of this situation, and its object is to provide a kind of radial gas expander that can access desired performance.And, the object of the present invention is to provide a kind of radial gas expander of distortion of wall that can guarantee that gas imports the flow path width of stream 120a, 120b and can prevent from forming the barrier film of housing.
[for solving the mode of problem]
In order to realize above-mentioned object, the invention provides following mode.
The related radial gas expander of first method of the present invention possesses: running shaft; Impeller, it is fixed on described running shaft; Housing, it supports described running shaft for rotating, and is formed with the importing stream that imports fluid to described impeller.And, at described importing stream, being provided with the nozzle wing and support member, described nozzle wing guiding flows into the fluid of described impeller, and described support member is arranged on the upstream side of the described nozzle wing, and to supporting between the mutual opposed wall of described importing stream.In addition, described support member forms wing when analysing and observe observation.
According to this structure, by support member, make to shorten from being arranged on lower end to the distance of supporting point of the mutual opposed wall of the importing stream in housing, thereby can reduce the amount of deformation of opposed wall, and can guarantee desired flow path width.And, because support member forms wing analysing and observe while observing, therefore can prevent from making the situation of movement disorder of the fluid of the flow nozzle wing.
And the related radial gas expander of second method of the present invention possesses: running shaft; Two groups of impeller sets, it consists of the impeller that is fixed on described running shaft respectively, and is symmetrical arranged in the axial direction; Housing, it supports described running shaft for rotating, 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 imports stream and described first imports the adjacent setting of stream, and imports from the fluid of described first group of impeller sets ejection to second group of impeller sets.And, described second, import stream and be provided with the nozzle wing and support member, described nozzle wing guiding flows into the fluid of described impeller, described support member is arranged on the upstream side of the described nozzle wing, and to supporting between the mutual opposed wall of described the second importing stream, described support member forms wing when analysing and observe observation.
According to this structure, can in importing stream, the first importing stream and second guarantee desired flow path width.And, in the situation that it is large to flow into the pressure difference of the fluid of the first importing stream and the fluid of inflow the second importing stream, also can import by support member reduction and median wall and second amount of deformation of the mutual opposed wall of stream, and because support member forms wing analysing and observe while observing, therefore can prevent from making the situation of movement disorder of the fluid of the flow nozzle wing.
And, in Third Way of the present invention, described support member arranges a plurality of around described running shaft, and form so that described support member width each other along radially equal mode along with towards inner circumferential side, width being narrowed down gradually from outer radial periphery side.
According to this structure, the fluid that can make the surrounding by support member is speedup and import swimmingly the nozzle wing not.
And in cubic formula of the present invention, described housing has: housing body, be built in a plurality of barrier films that described housing body and one link, described importing stream is formed at described a plurality of barrier film.
According to this structure, can be more easily the housing that is incorporated with the nozzle wing and forms the support member of wing be assembled.And, can easily carry out inner maintenance.
[invention effect]
According to the present invention, can provide the radial gas expander of amount of deformation that can access desired performance and can reduce the wall of the barrier film that forms housing.
Accompanying drawing explanation
Fig. 1 is the sectional view of the related radial gas expander of embodiments of the present invention.
Fig. 2 is the A portion enlarged view of Fig. 1.
Fig. 3 is that the B of Fig. 2 is to view.
Fig. 4 is the figure that is illustrated in the streamline of the mobile gas of support fins periphery.
Fig. 5 is the sectional view of radial gas expander in the past.
Fig. 6 is that the C of Fig. 5 is to view, and for being illustrated in the figure of the streamline of the mobile gas of spacer element periphery.
Embodiment
With reference to accompanying drawing, embodiments of the present invention are described in detail.
As shown in Figures 1 and 2, the related radial gas expander 1 of embodiments of the present invention possesses: the housing 2 of tubular; Can be bearing in rotatably housing 2 and at the upwardly extending running shaft 3 of axle of housing 2; Be fixed on a plurality of impellers 4 on running shaft 3.
In addition, in the following description, with housing 2 axially and axially consistent the describing of running shaft 3.And, only that being axially called of the axial and running shaft 3 of housing 2, is axial.
Radial gas expander 1 within it portion possesses two intervals for expanding gas.That is, radial gas expander 1 possesses two gas expansions interval 5a, the 5b that consist of the interval 5a of the gas expansion that is configured in the first axial side and the interval 5b of the gas expansion that is configured in the second axial side.
The radial gas expander 1 of present embodiment possesses following structure,, by importing the gas of the interval 5a of the first gas expansion, obtain rotary driving force, and will discharge and gas expanding imports the interval 5b of the second gas expansion from the interval 5a of the first gas expansion, further obtain rotary driving force.
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 consists of 11 barrier films 8,9a, 9b, 10a, 10b, 11a, 11b, 12a, 12b, 13a, 13b connecting along the mode of axially extracting.
The interval 5a of the first gas expansion has barrier film 9a, 10a, 11a, 12a, the 13a that is disposed at central barrier film 8 and is connected with the first side of barrier film 8.And the interval 5b of the second gas expansion has barrier film 9b, 10b, 11b, 12b, the 13b that is disposed at central barrier film 8 and is connected with the second side of barrier film 8.
That is, two gas expansions interval 5a, 5b have as barrier film 8 shared structural element, central authorities.
In housing body 6, be formed with for the suction port 18a to the interval 5a importing of the first gas expansion gas, for import the suction port 18b of gas to the interval 5b of the second gas expansion.
And, in housing body 6, be formed with for the ejiction opening 19a from the interval 5a ejection of the first gas expansion gas, for the ejiction opening 19b from the interval 5b ejection of the second gas expansion gas.
In addition, by gas pipe arrangement 22, connect 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.
Running shaft 3 connects the middle ground configuration of barrier film group 7.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, the 13b of end plate separately.And, in the perimembranous of barrier film 13a, 13b that is positioned at the inner side of each bearing 15, be provided with dry gas seals part 16.
A plurality of impellers 4 are fixed on running shaft 3, and the level Four impeller 4 that forms the interval 5a of the first gas expansion is oppositely arranged each other with the level Four impeller 4 that forms the interval 5b of the second gas expansion.
Herein, for each impeller 4, when the opening towards outer radial periphery side being made as to suction port 41, when axial opening is set to ejiction opening 42, with the side with suction port 41, the mode to central barrier film 8 configures the level Four impeller 4 that forms the level Four impeller 4 of the interval 5a of the first gas expansion and form the interval 5b of the second gas expansion.That is, with ejiction opening 42, the mode towards the first axial side configures the impeller 4 of the interval 5a of formation the first gas expansion, and with ejiction opening 42, the mode towards the second axial side configures the impeller 4 of the interval 5b of formation the second gas expansion.
In addition, to the identical symbol of a plurality of impeller 4 mark, yet the size of a plurality of impeller 4 is different.Particularly, a plurality of impellers 4 change size to adapt to the mode of the expansion stroke of gas.
Between central barrier film 8 and barrier film 9a, 9b in its both sides, be formed with the first importing stream 20a and second being communicated with suction port 18a, 18b respectively and import stream 20b.That is, the first importing stream 20a of the interval 5a of the first gas expansion is formed between the wall 81 of the first side of central barrier film 8 and the wall 91 of the second side of barrier film 9a.And second of the interval 5b of the second gas expansion imports stream 20b and is formed between the wall 82 of the second side of central barrier film 8 and the wall 92 of the first side of barrier film 9b.
Thus, the first importing stream 20a and second imports stream 20b and across central barrier film 8, is adjacent to configuration.
Equally, also as barrier film 13a, the 13b of end plate and with barrier film 12a, the 12b of their adjacency between be formed with respectively and above-mentioned ejiction opening 19a, derivation stream 21a, the 21b that 19b is communicated with.
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.
At each first impeller 4 upstream sides that import in stream 20a and the second importing stream 20b, be provided with a plurality of nozzle wings 24 that the inflow to impeller 4 of gas is guided.In the present embodiment, be provided with 17 nozzle wings 24.
As shown in Figure 3, the nozzle wing 24 equally spaced sets at Zhou Fangxiang.Each nozzle wing 24 from end on observation time section shape form the so-called wing of leading edge circle trailing edge point.And the leading edge of the nozzle wing 24 is configured in Zhou Fangxiang outer circumferential side, trailing edge is configured in Zhou Fangxiang inner circumferential side, and trailing edge rolls tiltedly configuration with respect to leading edge to sense of rotation R direct of travel in the mode of the sense of rotation R along running shaft 3.That is, at the flow direction upstream side configuration front end of gas and in configuration rear end, downstream side.
And the section shape of the nozzle wing 24 for example utilizes numerical value fluid mechanics (CFD) parsing to determine.Therefore the center line that, the section shape of the nozzle wing 24 of present embodiment forms with respect to the flow direction along gas (following, to be called grain direction) is unsymmetrical.That is, the nozzle wing 24 has as flowing of gas imported swimmingly to the shape of impeller 4, to promote to make the effect of gas expansion speedup in impeller 4.
More outer circumferential side at the nozzle wing 24 is provided with a plurality of (17) support fins 25 as support member.Support fins 25 is same with the nozzle wing 24, at Zhou Fangxiang, equally spaced sets.The section shape from end on observation of each support fins 25 forms the so-called aerofoil profile of leading edge circle trailing edge point.And the leading edge of support fins 25 is configured in Zhou Fangxiang outer circumferential side, trailing edge is configured in Zhou Fangxiang inner circumferential side, and trailing edge rolls tiltedly configuration with respect to leading edge to sense of rotation R direct of travel in the mode along sense of rotation R.That is, for support fins 25, at grain direction upstream side configuration front end, in configuration rear end, downstream side.
And, the shape of support fins 25 form so that support fins 25 width W each other in the i.e. mode about equally radially of grain direction, along with towards inner circumferential side, width being narrowed down gradually from outer radial periphery side.
In addition, the section shape of support fins 25 is different from the nozzle wing 24, with respect to the center line along grain direction, forms symmetric figure.For the shape of support fins 25, circumferential position and position radially, in order not affect the gas that imports the nozzle wing 24 as far as possible, still utilize CFD etc. to determine, be particularly preferably set to the shape along streamline.And, in less for the impact of flow line is controlled at (make streamline not disorderly) scope, preferably shorten the length of grain direction as far as possible.And, because causing streamline, the flow of gas changes, therefore preferably according to service condition, suitably determine.
Action to the radial gas expander 1 of said structure describes.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 by 4 minutes four-stages of level Four impeller in the interval 5a of the first gas expansion, 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, and at the second gas expansion, interval 5b expands, and sprays from ejiction opening 19b.
In the inside of interval 5a, 5b of two gas expansions, the gas of inflow flows in the axial direction.Wherein, according to said structure, gas flows to mutual opposite direction.That is, gas at the interval 5a of gas expansion from second axial side direction the first side flow.And, gas at the interval 5b of gas expansion from first axial side direction the second side flow.
, compare with the pressure that imports the gas of the first importing stream 20a via suction port 18a, the pressure of gas that imports the second importing stream 20b via suction port 18b is lower herein.That is, across barrier film 8, adjacent first import the pressure difference that pressure and second in stream 20a imports the pressure in stream 20b and become large.
According to above-mentioned mode of execution, even if it is large that the pressure in the first importing stream 20a and second imports the pressure difference of the pressure in stream 20b, and the central barrier film 8 being formed between the first importing stream 20a and the second importing stream 20b is applied with in the situation that makes the such power of these barrier film 8 distortion, by being provided with support fins 25, can reduces amount of deformation.And support fins 25 forms wing analysing and observe while observing, as shown in Figure 4, can be reduced in the disorder of the streamline L of the mobile gas of the periphery of support fins 25.
And, support fins 25 is so that support fins 25 width W each other forms along with width being narrowed down gradually from outer radial periphery side direction inner circumferential side along radially equal mode, and the gas that can make thus the surrounding by support fins 25 is speedup and import swimmingly the nozzle wing 24 not.
And, because support fins 25 is symmetric shape with respect to grain direction, therefore can more easily manufacture.
And, owing to forming a plurality of barrier film groups 7 of housing 2, can cut apart in the axial direction, therefore can 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 changes.For example, also support fins 25 can be set to be asymmetrical shape with respect to grain direction.
Industrial utilizability
According to radial gas expander of the present invention, can access desired performance, and can reduce the amount of deformation of the wall of the barrier film that forms housing.
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 (4)
1. a radial gas expander, wherein, possesses:
Running shaft;
Impeller, it is fixed on described running shaft;
Housing, it supports described running shaft for rotating, and is formed with the importing stream that imports fluid to described impeller,
At described importing stream, be provided with the nozzle wing and support member, the fluid that described in described nozzle wing subtend, impeller flows into guides, described support member is arranged on the upstream side of the described nozzle wing, and to supporting between the mutual opposed wall of described importing stream
Described support member forms wing when analysing and observe observation.
2. a radial gas expander, wherein, possesses:
Running shaft;
Two groups of impeller sets, it consists of the impeller that is fixed on described running shaft respectively, and is symmetrical arranged in the axial direction;
Housing, it supports described running shaft for rotating, 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 imports stream and described first imports the adjacent setting of stream, and import from the fluid of described first group of impeller sets ejection to second group of impeller sets
Described second, import stream and be provided with the nozzle wing and support member, the fluid that described in described nozzle wing subtend, impeller flows into guides, described support member is arranged on the upstream side of the described nozzle wing, and to supporting between the mutual opposed wall of described the second importing stream
Described support member forms wing when analysing and observe observation.
3. radial gas expander as claimed in claim 1 or 2, wherein,
Described support member arranges a plurality of around described running shaft, and form so that described support member width each other along radially equal mode along with towards inner circumferential side, width being narrowed down gradually from outer radial periphery side.
4. the radial gas expander as described in any one in claim 1～3, wherein,
Described housing has: housing body; Be built in a plurality of barrier films that described housing body and one link,
Described importing stream is formed at described barrier film each other.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2011-190525 | 2011-09-01 | ||
| JP2011190525A JP5959816B2 (en) | 2011-09-01 | 2011-09-01 | Radial gas expander |
| PCT/JP2012/050165 WO2013031244A1 (en) | 2011-09-01 | 2012-01-06 | Radial gas expander |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103649465A true CN103649465A (en) | 2014-03-19 |
| CN103649465B 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) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112377269A (en) * | 2021-01-11 | 2021-02-19 | 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 |
| CN113202565A (en) * | 2020-02-03 | 2021-08-03 | 三菱重工压缩机有限公司 | Rotary machine |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6483106B2 (en) | 2013-06-28 | 2019-03-13 | エクソンモービル アップストリーム リサーチ カンパニー | System and method utilizing an axial flow expander |
| WO2014208777A1 (en) * | 2013-06-28 | 2014-12-31 | Mitsubishi Heavy Industries Compressor Corporation | Axial flow expander |
| 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 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4285631A (en) * | 1978-11-20 | 1981-08-25 | Plessey Handel Und Investments Ag | Radial flow centrifugal impeller |
| 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 |
| WO2008090628A1 (en) * | 2007-01-26 | 2008-07-31 | Hitachi, Ltd. | Steam turbine type power generating apparatus and method of operating the same |
| CN101575990A (en) * | 2008-05-05 | 2009-11-11 | 霍尼韦尔国际公司 | Turbocharger with variable nozzle having vane sealing surfaces |
| US20100037458A1 (en) * | 2005-06-08 | 2010-02-18 | Dresser-Rand Company | Impeller with machining access panel |
| JP2011043070A (en) * | 2009-08-19 | 2011-03-03 | Mitsubishi Heavy Industries Compressor Corp | Radial gas expander |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3369737A (en) * | 1962-12-10 | 1968-02-20 | Gen Electric | Radial flow machine |
| JPS54151772A (en) * | 1978-05-22 | 1979-11-29 | Toyota Motor Corp | Fluid torque convertor |
| JPS6050962B2 (en) * | 1978-12-04 | 1985-11-11 | 株式会社日立製作所 | radial turbine |
| JPS63201326A (en) * | 1987-02-16 | 1988-08-19 | Juichi Unno | Gas turbine |
| JPH053684Y2 (en) * | 1987-10-26 | 1993-01-28 | ||
| JPH0315666A (en) * | 1989-06-12 | 1991-01-24 | Hitachi Ltd | Hydraulic turbine |
| US5562405A (en) * | 1994-03-10 | 1996-10-08 | Weir Pumps Limited | Multistage axial flow pumps and compressors |
| US6709232B1 (en) * | 2002-09-05 | 2004-03-23 | Honeywell International Inc. | Cambered vane for use in turbochargers |
| GB2440344A (en) * | 2006-07-26 | 2008-01-30 | Christopher Freeman | Impulse turbine design |
| JP4812597B2 (en) * | 2006-11-09 | 2011-11-09 | トヨタ自動車株式会社 | Turbocharger |
| GB2462115A (en) * | 2008-07-25 | 2010-01-27 | Cummins Turbo Tech Ltd | Variable geometry turbine |
-
2011
- 2011-09-01 JP JP2011190525A patent/JP5959816B2/en not_active Expired - Fee Related
-
2012
- 2012-01-06 CN CN201280033725.XA patent/CN103649465B/en not_active Expired - Fee Related
- 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
- 2012-01-06 DE DE112012003648.4T patent/DE112012003648T5/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4285631A (en) * | 1978-11-20 | 1981-08-25 | Plessey Handel Und Investments Ag | Radial flow centrifugal impeller |
| 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 |
| US20100037458A1 (en) * | 2005-06-08 | 2010-02-18 | Dresser-Rand Company | Impeller with machining access panel |
| WO2008090628A1 (en) * | 2007-01-26 | 2008-07-31 | Hitachi, Ltd. | Steam turbine type power generating apparatus and method of operating the same |
| 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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113202565A (en) * | 2020-02-03 | 2021-08-03 | 三菱重工压缩机有限公司 | Rotary machine |
| US11560903B2 (en) | 2020-02-03 | 2023-01-24 | Mitsubishi Heavy Industries Compressor Corporation | Rotary machine |
| CN112377269A (en) * | 2021-01-11 | 2021-02-19 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2013053530A (en) | 2013-03-21 |
| US20140126994A1 (en) | 2014-05-08 |
| DE112012003648T5 (en) | 2014-08-28 |
| CN103649465B (en) | 2016-02-10 |
| JP5959816B2 (en) | 2016-08-02 |
| WO2013031244A1 (en) | 2013-03-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103649465A (en) | Radial gas expander | |
| JP4927129B2 (en) | Radial gas expander | |
| CN109139256B (en) | Inlet pre-swirl gas turbine engine | |
| CN101994529B (en) | Steam turbine and cooling and heat insulation method of steam turbine | |
| CN104105886B (en) | Rotary machine | |
| US20130164119A1 (en) | Seal structure and centrifugal compressor | |
| CN104838149B (en) | Centrifugal compressor | |
| CN108729952A (en) | More turbine vane frames | |
| CN103206262A (en) | Airfoil | |
| JP6643235B2 (en) | Multistage centrifugal compressor | |
| CN106801623A (en) | Turbo blade | |
| CN109252900B (en) | Combined type turbine | |
| CN102472114A (en) | Multi-stage radial turbine | |
| CN103573691A (en) | Pump impeller | |
| US10989201B2 (en) | Centrifugal compressor | |
| CN105422186A (en) | Axial flow type turbine with small blade structure | |
| JP5693112B2 (en) | Axial turbine and method for exhausting flow from an axial turbine | |
| RU2737270C1 (en) | Turbo-machine component with internal cooling | |
| CN107250555A (en) | Movable vane piece and axial-flow type rotating machinery | |
| US20190169989A1 (en) | Flow channel for a turbomachine | |
| WO2019107488A1 (en) | Multi-stage centrifugal compressor, casing, and return vane | |
| EP3290650A1 (en) | Low-pressure steam turbine diffuser for reducing shock losses | |
| CN109083687A (en) | Minimize the method for crossing the crossing current of cooling hole and the component for turbogenerator | |
| JP2011202623A (en) | Radial flow turbo machine | |
| CN103423171B (en) | Turbocompressor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160210 Termination date: 20190106 |