CN105464711A - Novel axial flow turbine suitable for pulse pressure charging - Google Patents
Novel axial flow turbine suitable for pulse pressure charging Download PDFInfo
- Publication number
- CN105464711A CN105464711A CN201510931846.1A CN201510931846A CN105464711A CN 105464711 A CN105464711 A CN 105464711A CN 201510931846 A CN201510931846 A CN 201510931846A CN 105464711 A CN105464711 A CN 105464711A
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- Prior art keywords
- stator
- rotating shaft
- rotor
- spiral case
- flow
- 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.)
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- 230000035485 pulse pressure Effects 0.000 title abstract 3
- 238000005266 casting Methods 0.000 claims description 3
- 238000007493 shaping process Methods 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 2
- 238000002156 mixing Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 230000001360 synchronised effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000012512 characterization method Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
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
- F01D1/04—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 axially
-
- 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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a novel axial flow turbine suitable for pulse pressure charging. The novel axial flow turbine comprises a volute, stators, a rotor, a rotating shaft, a seal ring and a bearing. A gas inlet is formed in the front end of the volute, and a pressure expander is arranged at the rear end of the volute. An exhaust port is fixedly formed in the upper end of the pressure expander. The stators are each in an annular shape and located on the inner wall of the gas inlet of the volute. The front end of the rotating shaft is in an arc shape and located on the portion, close to the rear side, between the stators. The rear end of the rotating shaft is fixed to the rear side wall of the volute through the bearing. The rotor is fixed to the portion, close to the front end, on the rotating shaft. The front end of the pressure expander is located on the rear side of the rear side wall of the rotor. According to the novel axial flow turbine suitable for pulse pressure charging, work of the stators and work of the rotor are closer to the quasi-steady state, and therefore the efficiency of the rotor is improved; and in addition, flowing at the outlet of the rotor is uniform in the circumferential direction, and the mixing loss generated on the downstream part of the rotor due to circumferential-direction ununiformity is also reduced to some extent.
Description
Technical field
The invention belongs to exhaust turbine pressuring technology field, especially relate to a kind of novel axial-flow turbine of applicable pulse pressure-charging.
Background technique
The energy that pulse pressure-charging utilizes internal-combustion engine pulse to be vented exports to the merit improving booster turbine, and conventional runoff, mixed flow and axial flow all adopt spiral case I. C. engine exhaust to be assigned to the circumference of turbine rotor.This method is unfavorable for the energy making full use of pulse, and its reason is the decrease in efficiency of rotor, and detail is as follows:
1, under pulsating inlet condition, spiral case because of its runner longer, flow velocity lower (relative rotor), thus produce unsteady aerodynamic effect, cause rotor inlet condition circumferentially uneven and change in time, pressure at inlet, temperature and liquid speed are no longer synchronous.
2, because rotor each blade path entry condition is uneven, its exit condition is also no longer even, which results in the blending of falling liquid film homogenization in rotor outlet downstream, causes and start loss.
3, because each characteristic quantity that flows is not synchronous in time, the mass flow rate of turbine is no longer synchronous with expansion ratio of turbine.Thus the efficient district of turbine is no longer synchronous in time with high traffic areas, so that the efficiency of turbine is more permanent and efficiency that is pseudo steady state is low.
Therefore be badly in need of wanting a kind of can the turbo machine of Appropriate application pulse energy.
Summary of the invention
In view of this, the present invention is intended to propose a kind of novel axial-flow turbine that can improve the efficiency of booster turbine under pulsating inlet condition, with the pulse energy of Appropriate application engine exhaust.
For achieving the above object, technological scheme of the present invention is achieved in that
A novel axial-flow turbine for applicable pulse pressure-charging, comprises spiral case, stator, rotor, rotating shaft, seal ring and bearing;
The front end of described spiral case is provided with a suction port, and rear end is provided with a Diffuser, and the upper end of this Diffuser is installed with a relief opening;
Described stator in the form of a ring, is positioned on the inwall of described volute air-inlet mouth, and the rear sidewall of this stator and the central axis of described rotating shaft are at an angle;
The front end of described rotating shaft is arc-shaped, and the position of rear side is partial in the front end of this rotating shaft between described stator, and the rear end of this rotating shaft is fixed on by bearing on the rear sidewall of described spiral case;
Described rotor is fixed on the position described rotating shaft being partial to front end, and the angle of inclination of the front panel of this rotor and the rear sidewall of described stator is suitable;
The front end of described Diffuser is positioned at the rear side of described rotor rear sidewall, and the rear end of this Diffuser is connected with described rotating shaft sealing by described seal ring, and described seal ring to be fixed in described rotating shaft and to be positioned at the front of described bearing.
Further, described stator is fixed stator, and this stator is fixed on the inwall of described volute air-inlet mouth, and under the design conditions of motor, the exit flow of this stator and the axial angle of rotating shaft are between 60 degree to 70 degree.
Further, described stator is for becoming geometry stator, and this stator is arranged on the inwall of described volute air-inlet mouth, and along with the flowing of air-flow, certain form occurs or position changes, under the design conditions of motor, the exit flow of this stator and the axial angle of rotating shaft are between 45 degree to 80 degree.
Further, the front end of described rotor is entrance, and rear end is outlet, and under the design conditions of motor, the angle of attack of described rotor inlet is zero substantially, and the angle of air-flow in outlet port is zero substantially.
Further, the radial dimension of described Diffuser is 1.0 to 1.2 times of described root diameter.
Further, described spiral case is also provided with whirlpool tongue, the shape near described whirlpool tongue and this whirlpool tongue and the structural similarity of physical dimension and centrifugal-flow compressor spiral case.
Further, the sublingual Flow area in whirlpool is the cross-sectional area of described spiral case, and the sublingual Flow area in this whirlpool is not less than 10% of the maximum cross section area of described spiral case.
Further, described Diffuser is arranged on the rear end of described spiral case.
Further, described Diffuser and described spiral case integrally casting shaping.
Relative to prior art, the novel axial-flow turbine of applicable pulse pressure-charging of the present invention has following advantage:
(1) the novel axial-flow turbine of applicable pulse pressure-charging of the present invention, the work of stators and rotators closer to pseudo steady, thus improves the efficiency of rotor.
(2) the novel axial-flow turbine of applicable pulse pressure-charging of the present invention, because rotor outlet flowing is circumferentially comparatively even, the mixing loss produced because circumferential asymmetry is even in rotor downstream also declines to some extent.
(3) the novel axial-flow turbine of applicable pulse pressure-charging of the present invention, due to shaft flow rotor rotary inertia compared with runoff and mixed flow turbine little, make turbine of the present invention have the advantage having transient state to accelerate.
Accompanying drawing explanation
The accompanying drawing forming a part of the present invention is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
The novel axial flow turbine structure schematic diagram that Fig. 1 is the applicable pulse pressure-charging described in the embodiment of the present invention;
Fig. 2 is the gas expansion deflection in the stator schematic diagram described in the embodiment of the present invention;
Fig. 3 is the worm frame schematic diagram described in the embodiment of the present invention.
Description of reference numerals:
1-spiral case; 11-suction port; 12-Diffuser; 13-relief opening; 2-stator; 3-rotor; 4-rotating shaft; 5-seal ring; 6-bearing.
Embodiment
It should be noted that, when not conflicting, the embodiment in the present invention and the feature in embodiment can combine mutually.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.In addition, term " first ", " second " etc. only for describing object, and can not be interpreted as instruction or hint relative importance or imply the quantity indicating indicated technical characteristics.Thus, one or more these features can be expressed or impliedly be comprised to the feature being limited with " first ", " second " etc.In describing the invention, except as otherwise noted, the implication of " multiple " is two or more.
In describing the invention, it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, above-mentioned term concrete meaning in the present invention can be understood by concrete condition.
Below with reference to the accompanying drawings and describe the present invention in detail in conjunction with the embodiments.
As shown in Figures 1 to 3, the present invention includes spiral case 1, stator 2, rotor 3, rotating shaft 4, seal ring 5 and bearing 6;
The front end of spiral case 1 is provided with a suction port 11, and rear end is provided with a Diffuser 12, and the upper end of this Diffuser 12 is installed with a relief opening 13;
Stator 2 in the form of a ring, is positioned on the inwall of spiral case 1 suction port 11, and the rear sidewall of this stator 2 and the central axis of rotating shaft 4 are at an angle;
The front end of rotating shaft 4 is arc-shaped, and the position of rear side is partial in the front end of this rotating shaft 4 between stator 2, and the rear end of this rotating shaft 4 is fixed on by bearing 6 on the rear sidewall of spiral case 1, and bearing 6 is for support rotor 2 and rotate;
Rotor 3 is fixed on position rotating shaft 4 being partial to front end, and the angle of inclination of the front panel of this rotor 3 and the rear sidewall of stator 2 is suitable;
The front end of Diffuser 12 is positioned at the rear side of rotor 3 rear sidewall, and the rear end of this Diffuser 12 is tightly connected by seal ring 5 and rotating shaft 4, and seal ring 5 to be fixed in rotating shaft 4 and to be positioned at the front of bearing 6, for separating of exhaust and the lubricating oil that occurs from bearing 6 end.
Gas enters turbine by the suction port 11 of spiral case 1 front end, by creating deflection along the circumferential direction during stator 2, and acceleration of expanding, air-flow after acceleration continues to expand and drive rotor 3 rotation acting at rotor 3, Fig. 2 is gas expansion deflection in the stator schematic diagram, and the direction of arrow is gas flow.
Air-flow after workmanship rises along Diffuser 12, and its remaining speed circumferential component reduces further, and pressure obtains ging up in a small amount simultaneously.
From Diffuser 12 air-flow out, circumferentially collected by spiral case 1, finally discharged by relief opening 13.
Stator 2 is fixed stator, this stator 2 is fixed on the inwall of spiral case 1 suction port 11, under the design conditions of motor, the exit flow of this stator 2 and the axial angle of rotating shaft 4 are between 60 degree to 70 degree, and the design conditions of motor are when being generally maximum engine torque point, suction pulsation reach namely arrive moment maximum time.
Stator 2 is for becoming geometry stator, this stator 2 is arranged on the inwall of spiral case 1 suction port 11, and there is certain form along with the flowing of air-flow or position changes, under the design conditions of motor, the exit flow of this stator 2 and the axial angle of rotating shaft 4 are between 45 degree to 80 degree.
The front end of rotor 3 is entrance, rear end is outlet, under the design conditions of motor, the angle of attack of rotor 3 entrance is zero substantially, the angle of air-flow in outlet port is zero substantially, the design of this kind of rotor 3 is irrotationality exit design, and the angle of attack of rotor 3 entrance is zero is substantially considering the result after entrance slippage.
Consider the impact on turbo machine overall dimensions, the radial dimension of Diffuser 12 is 1.0 to 1.2 times of rotor 3 diameter.
The design of spiral case 1 will consider that Diffuser 12 goes out stream and may have rotation, and there is the possibility that both direction rotates, although similar to common spiral case in the design principle of thus spiral case 1, but spiral case 1 is also provided with whirlpool tongue, the shape near whirlpool tongue and this whirlpool tongue and the structural similarity of physical dimension and centrifugal-flow compressor spiral case.
The sublingual Flow area in whirlpool is the cross-sectional area of spiral case 1, and the sublingual Flow area in this whirlpool is not less than 10% of the maximum cross section area of spiral case 1.
Spiral case 1 in the present invention adopts the structure of similar centrifugal compressor spiral case to process whirlpool tongue and neighbouring shape and physical dimension, strengthens the area of spiral case minimum cross-section simultaneously.Spiral case cross-section area circumferentially growing direction, should be consistent with gas sense of rotation in most cases.
Diffuser 12 is arranged on the rear end of spiral case 1.
Diffuser 12 is shaping with spiral case 1 integrally casting.
Spiral case 1 is preferably a gas collector, and this gas collector comprises a spherical Diffuser and is positioned at the relief opening of this spherical Diffuser upper end, and this gas collector allows the flow rotation of both direction.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (9)
1. a novel axial-flow turbine for applicable pulse pressure-charging, is characterized in that: comprise spiral case, stator, rotor, rotating shaft, seal ring and bearing;
The front end of described spiral case is provided with a suction port, and rear end is provided with a Diffuser, and the upper end of this Diffuser is installed with a relief opening;
Described stator in the form of a ring, is positioned on the inwall of described volute air-inlet mouth, and the rear sidewall of this stator and the central axis of described rotating shaft are at an angle;
The front end of described rotating shaft is arc-shaped, and the position of rear side is partial in the front end of this rotating shaft between described stator, and the rear end of this rotating shaft is fixed on by bearing on the rear sidewall of described spiral case;
Described rotor is fixed on the position described rotating shaft being partial to front end, and the angle of inclination of the front panel of this rotor and the rear sidewall of described stator is suitable;
The front end of described Diffuser is positioned at the rear side of described rotor rear sidewall, and the rear end of this Diffuser is connected with described rotating shaft sealing by described seal ring, and described seal ring to be fixed in described rotating shaft and to be positioned at the front of described bearing.
2. the novel axial-flow turbine of applicable pulse pressure-charging according to claim 1, it is characterized in that: described stator is fixed stator, this stator is fixed on the inwall of described volute air-inlet mouth, under the design conditions of motor, the exit flow of this stator and the axial angle of rotating shaft are between 60 degree to 70 degree.
3. the novel axial-flow turbine of applicable pulse pressure-charging according to claim 1, it is characterized in that: described stator is for becoming geometry stator, this stator is arranged on the inwall of described volute air-inlet mouth, and there is certain form along with the flowing of air-flow or position changes, under the design conditions of motor, the exit flow of this stator and the axial angle of rotating shaft are between 45 degree to 80 degree.
4. the novel axial-flow turbine of applicable pulse pressure-charging according to claim 1, it is characterized in that: the front end of described rotor is entrance, rear end is outlet, under the design conditions of motor, the angle of attack of described rotor inlet is zero substantially, and the angle of air-flow in outlet port is zero substantially.
5. the novel axial-flow turbine of applicable pulse pressure-charging according to claim 1, is characterized in that: the radial dimension of described Diffuser is 1.0 to 1.2 times of described root diameter.
6. the novel axial-flow turbine of applicable pulse pressure-charging according to claim 1, is characterized in that: described spiral case is also provided with whirlpool tongue, the shape near described whirlpool tongue and this whirlpool tongue and the structural similarity of physical dimension and centrifugal-flow compressor spiral case.
7. the novel axial-flow turbine of applicable pulse pressure-charging according to claim 6, is characterized in that: the sublingual Flow area in whirlpool is the cross-sectional area of described spiral case, and the sublingual Flow area in this whirlpool is not less than 10% of the maximum cross section area of described spiral case.
8. the novel axial-flow turbine of applicable pulse pressure-charging according to claim 1, is characterized in that: described Diffuser is arranged on the rear end of described spiral case.
9. the novel axial-flow turbine of applicable pulse pressure-charging according to claim 1, is characterized in that: described Diffuser and described spiral case integrally casting shaping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510931846.1A CN105464711A (en) | 2015-12-14 | 2015-12-14 | Novel axial flow turbine suitable for pulse pressure charging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510931846.1A CN105464711A (en) | 2015-12-14 | 2015-12-14 | Novel axial flow turbine suitable for pulse pressure charging |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105464711A true CN105464711A (en) | 2016-04-06 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510931846.1A Pending CN105464711A (en) | 2015-12-14 | 2015-12-14 | Novel axial flow turbine suitable for pulse pressure charging |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105464711A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111042869A (en) * | 2019-12-24 | 2020-04-21 | 哈尔滨工程大学 | A small centripetal turbine with axial air intake using straight guide vanes |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2172340A (en) * | 1985-03-08 | 1986-09-17 | Hitachi Shipbuilding Eng Co | Turbocharger for diesel engine and method of controlling same |
| CN1429311A (en) * | 2000-03-17 | 2003-07-09 | Abb涡轮系统有限公司 | Distributor for exhaust gas turbine with axial flow |
| US20070204615A1 (en) * | 2006-03-06 | 2007-09-06 | Honeywell International, Inc. | Two-shaft turbocharger |
| US20090301085A1 (en) * | 2005-04-23 | 2009-12-10 | Francis Heyes | Turbocharger for an internal combustion engine |
| US20120051885A1 (en) * | 2009-05-11 | 2012-03-01 | Francois Danguy | Double exhaust centrifugal pump |
-
2015
- 2015-12-14 CN CN201510931846.1A patent/CN105464711A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2172340A (en) * | 1985-03-08 | 1986-09-17 | Hitachi Shipbuilding Eng Co | Turbocharger for diesel engine and method of controlling same |
| CN1429311A (en) * | 2000-03-17 | 2003-07-09 | Abb涡轮系统有限公司 | Distributor for exhaust gas turbine with axial flow |
| US20090301085A1 (en) * | 2005-04-23 | 2009-12-10 | Francis Heyes | Turbocharger for an internal combustion engine |
| US20070204615A1 (en) * | 2006-03-06 | 2007-09-06 | Honeywell International, Inc. | Two-shaft turbocharger |
| US20120051885A1 (en) * | 2009-05-11 | 2012-03-01 | Francois Danguy | Double exhaust centrifugal pump |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111042869A (en) * | 2019-12-24 | 2020-04-21 | 哈尔滨工程大学 | A small centripetal turbine with axial air intake using straight guide vanes |
| CN111042869B (en) * | 2019-12-24 | 2022-06-21 | 哈尔滨工程大学 | Small centripetal turbine adopting axial air inlet mode with straight guide vanes |
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Application publication date: 20160406 |
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