CN109869195A - A kind of combined flow turbine shaft assembly - Google Patents
A kind of combined flow turbine shaft assembly Download PDFInfo
- Publication number
- CN109869195A CN109869195A CN201711252911.3A CN201711252911A CN109869195A CN 109869195 A CN109869195 A CN 109869195A CN 201711252911 A CN201711252911 A CN 201711252911A CN 109869195 A CN109869195 A CN 109869195A
- Authority
- CN
- China
- Prior art keywords
- impeller disk
- vertical section
- blade
- impeller
- disk
- 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.)
- Withdrawn
Links
Abstract
The present invention relates to a kind of combined flow turbine shaft assemblies, the combined flow turbine shaft assembly includes the impeller and turbine wheel shaft being fixedly linked, the impeller includes the blade of the impeller disk and multiple same structures, each blade includes vertical section and inverted sections, vertical section is perpendicular to the end face setting of the impeller disk and the bottom end of vertical section is connected with the impeller disk, along the edge of the impeller disk, setting is stretched out in oblique upper to the outer side edges of vertical section outward, included angle A between the vertical section outer side edges and impeller disk axial direction is 35 °, along the edge of the impeller disk, setting is stretched out in oblique upper to blade vertical section outward, the maximum outside diameter of the blade assembly of blade composition is greater than the diameter of the impeller disk, the outer side edges of blade vertical section are no longer normal to the impeller disk and are axially arranged, so that gas changes in the impeller disk and the flow direction of blade vertical section junction, compared to the arrangement of radial-flow turbine component, oblique There are guide functions to axial, improves turbine efficiency.
Description
Technical field
The present invention relates to turbocharger apparatus technical field, especially a kind of combined flow turbine shaft assembly.
Background technique
Turbocharger is to drive the turbine in turbine to rotate acting, turbine using the high-temp waste gas of engine discharge
Axis drives the impeller high speed rotation in coaxial connected compressor, and compressed air, is supplied to engine high pressure, height in eccentric fashion
Density air.To which we can spray more fuel oils to engine, reaches and improve engine power, torque and reduce discharge etc.
Purpose.
In the traditional structure of the central rotor assembly of turbocharger, turbine is the most important thing in mechanism, without whirlpool
Wheel cannot drive compressor, that entire turbocharging is gone also just without any effect.Turbine is produced in reject end by engine
Then raw exhaust gas high speed rotation is sucked air, is transported to engine by turbine wheel shaft band dynamic pressure impeller again.In existing market
It is all the radial-flow turbine used in mainstream booster, design and the specific speed run are high, cause impeller outlet discharge loss
Huge, impeller internal flow condition is bad, so that turbine performance sharply deteriorates.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of efficient combined flow turbine shaft assemblies of structure simple operation.
In order to solve the above technical problems, combined flow turbine shaft assembly provided by the invention, including the impeller that is fixedly linked and
Turbine wheel shaft, the impeller include the blade of the impeller disk and multiple same structures, and the center of the impeller disk side and the turbine wheel shaft are solid
Fixed to be connected, blade is placed in the other side of the impeller disk, and each blade includes vertical section and inverted sections, end of the vertical section perpendicular to the impeller disk
The bottom end of face setting and vertical section is connected with the impeller disk, and the outer side edges of vertical section along the edge of the impeller disk, stretch out outward by oblique upper
Setting, the included angle A between the vertical section outer side edges and impeller disk axial direction are 35 °, so that the outer side edges inclination of blade vertical section is set
It sets.
Further, the impeller disk is arranged in truncated cone-shaped, and the turbine wheel shaft and the center of the small head end side of the impeller disk are fixed
It is connected, the blade is placed in the stub end side of the impeller disk.
Further, taper platform is arranged in the junction of the turbine wheel shaft and the impeller disk, so that being between turbine wheel shaft and the impeller disk
Arc-shaped transition is conducive to fluid and is oriented to.
The technical effect of invention: combined flow turbine shaft assembly of the invention, compared with the existing technology, blade vertical section is along leaf
Setting is stretched out in oblique upper outward at the edge of wheel disc, and the maximum outside diameter of the blade assembly of blade composition is greater than the diameter of the impeller disk,
The outer side edges of blade vertical section are no longer normal to the impeller disk and are axially arranged, so that gas is in the impeller disk and blade vertical section junction
Flow direction change, compared to the arrangement of radial-flow turbine component, it is oblique and it is axial have guide functions, improve turbine effect
Rate；The impeller disk is arranged in truncated cone-shaped, while taper platform is arranged in the small head end of the impeller disk, so that gas flows through taper platform, the impeller disk
When equally there is guiding role.
Detailed description of the invention
Invention is further described in detail with reference to the accompanying drawings of the specification:
Fig. 1 is the schematic perspective view of combined flow turbine shaft assembly of the invention；
Fig. 2 is the front view of combined flow turbine shaft assembly of the invention；
Fig. 3 is the side view of combined flow turbine shaft assembly of the invention.
In figure: turbine wheel shaft 1, taper platform 11, the impeller disk 2, blade 3, inverted sections 31, vertical section 32, outer side edges 33.
Specific embodiment
Embodiment 1 is as shown in Figure 1 to Figure 3, the combined flow turbine shaft assembly of the present embodiment, including the impeller being fixedly linked
With turbine wheel shaft 1, which includes the blade 3 of the impeller disk 2 and 11 piece same structure, and the impeller disk 2 is arranged in truncated cone-shaped, turbine wheel shaft 1
It is fixedly linked with the center of the small head end side of the impeller disk 2, taper platform 11 is arranged in the junction of turbine wheel shaft 1 and the impeller disk 2, so that whirlpool
Arc-shaped transition between wheel shaft 1 and the impeller disk 2, each blade 3 are placed in the stub end side of the impeller disk 2；Each blade 3 includes one casting
Make molding vertical section 32 and inverted sections 31, vertical section 32 perpendicular to the impeller disk 2 end face setting and vertical section 32 bottom end with
The impeller disk 2 is connected, and inverted sections 31 are turned down along the top of vertical section 32 to same direction；The outer side edges 33 of vertical section 32 are along the impeller disk
Setting is stretched out in oblique upper outward at 2 edge, and the included angle A between 2 axial direction of the vertical section outer side edges 33 and the impeller disk is 35 °, is made
32 outer side edges 33 for obtaining blade vertical section are obliquely installed.
Obviously, the above embodiment is merely an example for clearly illustrating the present invention, and is not to of the invention
The restriction of embodiment.For those of ordinary skill in the art, it can also be made on the basis of the above description
Its various forms of variation or variation.There is no necessity and possibility to exhaust all the enbodiments.And these belong to this hair
Bright spiritual changes and variations that derived from are still in the protection scope of this invention.
Claims (3)
1. a kind of combined flow turbine shaft assembly characterized by comprising the impeller and turbine wheel shaft being fixedly linked, the impeller include
The blade of the impeller disk and multiple same structures, the center of the impeller disk side are fixedly linked with the turbine wheel shaft, and blade is placed in leaf
The other side of wheel disc, each blade include vertical section and inverted sections, end face setting and vertical section of the vertical section perpendicular to the impeller disk
Bottom end is connected with the impeller disk, and the outer side edges of vertical section are outside the edge of the impeller disk setting of oblique upper stretching outward, the vertical section
Included angle A between side and impeller disk axial direction is 35 °, so that the outer side edges of blade vertical section are obliquely installed.
2. combined flow turbine shaft assembly according to claim 1, which is characterized in that the impeller disk is arranged in truncated cone-shaped,
The turbine wheel shaft and the center of the small head end side of the impeller disk are fixedly linked, and the blade is placed in the stub end one of the impeller disk
Side.
3. combined flow turbine shaft assembly according to claim 1 or 2, which is characterized in that the turbine wheel shaft and the impeller disk
Taper platform is arranged in junction, so that arc-shaped transition between turbine wheel shaft and the impeller disk.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711252911.3A CN109869195A (en) | 2017-12-01 | 2017-12-01 | A kind of combined flow turbine shaft assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711252911.3A CN109869195A (en) | 2017-12-01 | 2017-12-01 | A kind of combined flow turbine shaft assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109869195A true CN109869195A (en) | 2019-06-11 |
Family
ID=66914719
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711252911.3A Withdrawn CN109869195A (en) | 2017-12-01 | 2017-12-01 | A kind of combined flow turbine shaft assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109869195A (en) |
-
2017
- 2017-12-01 CN CN201711252911.3A patent/CN109869195A/en not_active Withdrawn
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104929953B (en) | Vibration and noise reducing centrifugal pump with biomimetic features | |
| CN104895841B (en) | Rectifier, flow passage structure, combined compressor, aero gas turbine engine | |
| CN202284569U (en) | Improved fan blade structure of centrifugal fan | |
| CN105909320A (en) | Wastegate with injected flow | |
| CN105909319A (en) | Turbocharger diffuser center body | |
| US8480351B2 (en) | Compressor unit | |
| CN204312394U (en) | With the turbosupercharger of diagonal impeller of compressor | |
| CN103573469A (en) | Fan pneumatic layout structure and method of turbofan engine | |
| CN110081026B (en) | Inlet guide vane for weakening leakage flow at blade top of centrifugal compressor and adjusting method | |
| CN208456914U (en) | A kind of turbocharger and its centrifugal compressor | |
| CN207499906U (en) | A kind of combined flow turbine shaft assembly | |
| CN109869195A (en) | A kind of combined flow turbine shaft assembly | |
| CN207499988U (en) | A kind of combined flow turbine booster | |
| CN206338121U (en) | Radial-flow turbocharger | |
| CN102588296B (en) | Turbo-type pneumatic submersible pump with multiple nozzles | |
| CN109869223A (en) | A kind of combined flow turbine booster | |
| CN109113870A (en) | A kind of diffuser, compressor and combustion gas turbine | |
| CN208749451U (en) | A kind of diffuser, compressor and combustion gas turbine | |
| CN104279183A (en) | Turbocharger gas compressor vane wheel with combined runoff flow and oblique flow | |
| CN204312395U (en) | The turbosupercharger of axially wearing and tearing can be reduced | |
| CN204312393U (en) | With the turbosupercharger of gas compressor arc diagonal impeller | |
| CN202493444U (en) | Multi-nozzle turbine type pneumatic submersible pump | |
| CN109869203A (en) | A kind of mixed-flow volute | |
| CN204200671U (en) | The turbo-charger blower impeller that runoff and oblique flow combine | |
| CN206429440U (en) | One kind is without spiral case air-conditioning draught fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190611 |
|
| WW01 | Invention patent application withdrawn after publication |