CN204921147U - Turbine engine is with expanding steady booster - Google Patents
Turbine engine is with expanding steady booster Download PDFInfo
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- CN204921147U CN204921147U CN201520684705.XU CN201520684705U CN204921147U CN 204921147 U CN204921147 U CN 204921147U CN 201520684705 U CN201520684705 U CN 201520684705U CN 204921147 U CN204921147 U CN 204921147U
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- turbine
- impeller
- pressurized machine
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- leading edge
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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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The utility model discloses a turbine engine is with expanding steady booster, including the turbine case, the one end of turbine is inserted turbine case, bearing body cup joint in on the turbine, the other end of turbine passes back of the body dish and is connected to the impeller, the fixed spiral case in the outside of back of the body dish, wherein, it has the circumference to lead to the groove to open on the air inlet inner wall of spiral case. The utility model discloses an open the technical scheme that the circumference leads to the groove on the air inlet inner wall of spiral case, can restrain the vortex that flow distortion that air inlet department produced leads to, improved emotionally condition of the inside air current of impeller, reached not that the outer spare part of the amount of disbursement expands steady effect, reduced the cost and the assembly degree of difficulty of booster.
Description
Technical field
The utility model relates to engine turbine supercharging technology field, especially, relates to a kind of turbogenerator and expands steady pressurized machine.
Background technique
The High Temperature High Pressure tail gas that turbocharging technology utilizes internal-combustion engine to discharge drives turbine acting, and turbine drives the coaxial compressor impeller High Rotation Speed connected, and increasing combustion engine air inflow improves HP, hp/litre.Turbosupercharging is the technical foundation that other energy-conserving and emission-cutting technologies (as reducing discharge capacity, high EGR rate) are implemented.Along with energy crisis and Abgasgesetz increasingly stringent, the engine energy-saving technology spring tide convexity that turbocharging technology is affording a magnificent spectacle shows uniqueness and the status that becomes more and more important.
In order to adapt to the requirement that engine energy-saving, reduction of discharging and high-altitude, plateau power recover, also more and more higher to the requirement of pressurized machine pressure ratio.The raising of pressure ratio will cause centrifugal compressor stable operation range sharply to reduce, and aerodynamic stability and the expansion of high pressure-charging centrifugal compressor surely become core and the difficult point of high pressure-charging technical research.The stability problem of gas compressor is mainly stall flutter phenomenon, and at present, use gas compressor comparatively widely to expand steady structure for secondary air inlet groove structure, this structure effectively can suppress the flow distortion of compressor impeller inlet, strengthens gas compressor stable operation; But this kind of structure can increase the annex such as air-ducting ring, back-up ring component, causes complete machine added cost, assembly process to increase.
Expand steady complex structure for pressurized machine in prior art, additional components causes cost and the problem of the raising of assembling difficulty, not yet has effective solution at present more.
Model utility content
Expand steady complex structure for pressurized machine in prior art, additional components causes cost and the problem of the raising of assembling difficulty more, the purpose of this utility model is that proposing a kind of turbogenerator expands steady pressurized machine, pressurized machine can be simplified and expand steady structure, avoid using unnecessary component, reduce cost and the assembling difficulty of pressurized machine.
Based on above-mentioned purpose, the technological scheme that the utility model provides is as follows:
According to an aspect of the present utility model, provide a kind of turbogenerator and expand steady pressurized machine.
Turbine box is comprised according to the steady pressurized machine of turbogenerator expansion that the utility model provides, described turbine box is inserted in one end of turbine, bearing support is socketed on described turbine, the other end of described turbine is connected to impeller through back of the body dish, spiral case is fixed in the outside of described back of the body dish, wherein, the suction port inwall of described spiral case has circumference groove.
Wherein, the position of circumference groove is opened in the upstream of described impeller splitterr vanes leading edge.
Further, circumference groove crosses over the leading edge of described impeller primary blades.
Further, initial position 2 to 15 millimeters of places before described impeller primary blades leading edge of circumference groove, final position is between described impeller primary blades leading edge and splitterr vanes leading edge.
Meanwhile, the sectional shape of circumference groove is one of following: quadrilateral, triangle, semicircle, fan-shaped.
Meanwhile, the groove maximum depth of circumference groove is 0.5 to 5 millimeters.
As can be seen from above, the technological scheme that the utility model provides by opening the technological scheme of circumference groove on the suction port inwall of spiral case, the vortex that the flow distortion that suction port place can be suppressed to produce causes, improve the air mobility status of impeller internal, reach and do not use additional elements to carry out expanding steady effect, reduce cost and the assembling difficulty of pressurized machine.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technological scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the principle assumption diagram of turbogenerator pressurized machine;
Fig. 2 is the structural drawing that in prior art, turbogenerator expands steady pressurized machine;
Fig. 3 is the structural drawing expanding steady pressurized machine according to the turbogenerator of the utility model embodiment.
Embodiment
Clearly understand for making the purpose of this utility model, technological scheme and advantage, below in conjunction with the accompanying drawing in the utility model embodiment, to the technological scheme in the utility model embodiment carry out further clear, complete, describe in detail, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, the every other embodiment that those of ordinary skill in the art obtain, belongs to the scope of the utility model protection.
In prior art, the theory structure of original pressurized machine as shown in Figure 1.As shown in Figure 1, pressurized machine by time, can there is flow distortion in impeller 5 place of spiral case 6 suction port, cause impeller 5 inside to produce flow separation zone, pressure gradient in impeller 5 disappears, and forms airflow breakaway and refluence, causes stall flutter phenomenon to occur.Flow distortion is in vortex shape in meridian plane, and along with the further reduction of gas compressor flow, vortex can constantly increase and extend to import border, causes flow distortion to affect increasing vicious circle, finally causes pressurized machine cisco unity malfunction.
On the other hand, shown in Fig. 2 is use secondary air inlet structure to assist the structural drawing expanding steady pressurized machine work.As shown in Figure 2, air-ducting ring 7 and back-up ring 8 are arranged at spiral case 6 suction port place in order to suppress flow distortion, but the method needs to use extra split component, improves cost and the assembling difficulty of pressurized machine.
According to an embodiment of the present utility model, provide a kind of turbogenerator and expand steady pressurized machine.
As shown in Figure 3, turbine box 1 is comprised according to the steady pressurized machine of turbogenerator expansion that embodiment of the present utility model provides, described turbine box 1 is inserted in one end of turbine 2, bearing support 3 is socketed on described turbine 2, the other end of described turbine 2 is connected to impeller 5 through back of the body dish 4, spiral case 6 is fixed in the outside of described back of the body dish 4, wherein, the suction port inwall of described spiral case 6 has circumference groove 9.
Wherein, the position of circumference groove 9 is opened in the upstream of described impeller 5 splitterr vanes leading edge.
Further, circumference groove 9 crosses over the leading edge of described impeller 5 primary blades.
Further, initial position 2 to 15 millimeters of places before described impeller 5 primary blades leading edge of circumference groove 9, final position is between described impeller 5 primary blades leading edge and splitterr vanes leading edge.
Meanwhile, the sectional shape of circumference groove 9 is one of following: quadrilateral, triangle, semicircle, fan-shaped.
Meanwhile, the groove maximum depth of circumference groove 9 is 0.5 to 5 millimeters.
Circumference groove 9 structure specific to the present invention can suppress impeller 5 inlet vortex, a part of eddy airstream is made to be divided in groove, the impact of flow distortion is suppressed a less scope, improve the airflow condition of impeller 5 inside, therefore prevent vortex further to import boundary expansion, reach the effect improving pressurized machine aerodynamic stability.
In sum, by means of technique scheme of the present utility model, by opening the technological scheme of circumference groove on the suction port inwall of spiral case, the vortex that the flow distortion that suction port place can be suppressed to produce causes, improve the air mobility status of impeller internal, reach and do not use additional elements to carry out expanding steady effect; Meanwhile, circumference groove realizes itself by machining or casting, is not load module, does not also need extra installation, because this reducing cost and the assembling difficulty of pressurized machine.
Those of ordinary skill in the field are to be understood that: the foregoing is only specific embodiment of the utility model; be not limited to the utility model; all within spirit of the present utility model and principle; any amendment of making, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (6)
1. a turbogenerator expands steady pressurized machine, it is characterized in that, comprise turbine box (1), described turbine box (1) is inserted in one end of turbine (2), bearing support (3) is socketed on described turbine (2), the other end of described turbine (2) is connected to impeller (5) through back of the body dish (4), spiral case (6) is fixed in the outside of described back of the body dish (4), wherein, the suction port inwall of described spiral case (6) has circumference groove (9).
2. a kind of turbogenerator according to claim 1 expands steady pressurized machine, it is characterized in that, opens the position of described circumference groove (9) in the upstream of described impeller (5) splitterr vanes leading edge.
3. a kind of turbogenerator according to claim 2 expands steady pressurized machine, and it is characterized in that, described circumference groove (9) crosses over the leading edge of described impeller (5) primary blades.
4. a kind of turbogenerator according to claim 3 expands steady pressurized machine, it is characterized in that, initial position 2 to 15 millimeters of places before described impeller (5) primary blades leading edge of described circumference groove (9), final position is between described impeller (5) primary blades leading edge and splitterr vanes leading edge.
5. a kind of turbogenerator according to claim 1 expands steady pressurized machine, it is characterized in that, the sectional shape of described circumference groove (9) is one of following: quadrilateral, triangle, semicircle, fan-shaped.
6. a kind of turbogenerator according to claim 1 expands steady pressurized machine, and it is characterized in that, the groove maximum depth of described circumference groove (9) is 0.5 to 5 millimeters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520684705.XU CN204921147U (en) | 2015-09-06 | 2015-09-06 | Turbine engine is with expanding steady booster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520684705.XU CN204921147U (en) | 2015-09-06 | 2015-09-06 | Turbine engine is with expanding steady booster |
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| Publication Number | Publication Date |
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| CN204921147U true CN204921147U (en) | 2015-12-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520684705.XU Active CN204921147U (en) | 2015-09-06 | 2015-09-06 | Turbine engine is with expanding steady booster |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113757176A (en) * | 2021-08-03 | 2021-12-07 | 中车大连机车研究所有限公司 | Supercharging shell structure with high inclusion capacity |
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2015
- 2015-09-06 CN CN201520684705.XU patent/CN204921147U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113757176A (en) * | 2021-08-03 | 2021-12-07 | 中车大连机车研究所有限公司 | Supercharging shell structure with high inclusion capacity |
| CN113757176B (en) * | 2021-08-03 | 2024-06-04 | 中车大连机车研究所有限公司 | Supercharging shell structure with high inclusion |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |