CN115306491A - Radial flow turbocharger nozzle ring sealing structure - Google Patents
Radial flow turbocharger nozzle ring sealing structure Download PDFInfo
- Publication number
- CN115306491A CN115306491A CN202211119087.5A CN202211119087A CN115306491A CN 115306491 A CN115306491 A CN 115306491A CN 202211119087 A CN202211119087 A CN 202211119087A CN 115306491 A CN115306491 A CN 115306491A
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- China
- Prior art keywords
- nozzle ring
- turbine
- radial flow
- sealing
- flow turbocharger
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- 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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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- 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
- F02B37/12—Control of the pumps
- F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
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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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a nozzle ring sealing structure of a radial-flow turbocharger, which comprises a nozzle ring, a heat shield and a support body which are sequentially arranged on a turbine shell, and the nozzle ring, the heat shield and the support body are pressed and fixed by a pressure plate; one end of the nozzle ring, which is close to the pressure plate, is compressed and sealed through a matching surface, the other end of the nozzle ring is provided with a labyrinth seal groove structure and a seal elastic sheet, a seal boss corresponding to the seal elastic sheet is arranged on the turbine shell, and when the nozzle ring is installed in the turbine shell, the seal elastic sheet and the seal boss are in interference fit to form a second seal structure. The radial flow turbocharger nozzle ring sealing structure disclosed by the invention is sealed by compressing the end surface of the turbine shell and the thin sheet, so that not only is good sealing property ensured, but also the whole structure is simpler and more compact, and the purpose of eliminating gaps is achieved.
Description
Technical Field
The invention relates to the technical field of nozzle sealing of superchargers, in particular to a nozzle ring sealing structure of a radial flow turbocharger.
Background
Turbochargers are widely used on locomotive diesel engines to increase the power density and economy of the locomotive diesel engine. The radial flow turbocharger of the locomotive adopts a turbine structure with a nozzle ring to improve the expansion ratio and the efficiency. The leakproofness of booster nozzle cascade department is one of the main index that influences overall performance, and the seal structure of current turbo charger nozzle cascade department mainly adopts labyrinth seal, installs the graphite gasket additional in the axial, installs forms such as lamination sealing ring additional radially. The sealing structure of this form has that the structure is complicated, whole size is great, and simultaneously, the gasket loss is great under the condition of often dismantling, and is inefficacy easily.
Disclosure of Invention
The invention provides a radial flow turbocharger nozzle ring sealing structure aiming at the problems.
The technical means adopted by the invention are as follows:
a radial flow turbocharger nozzle ring sealing structure comprises a supporting body, a pressure plate, a heat shield, a nozzle ring and a turbine shell;
the nozzle ring, the heat shield and the support body are sequentially arranged on the turbine shell and are pressed and fixed by the pressure plate;
a turbine shell matching surface is arranged at one end, close to the pressure plate, of the turbine shell, a nozzle ring matching surface is arranged at one end, close to the pressure plate, of the nozzle ring, and when the nozzle ring is installed in a turbine cavity of the turbine shell, the turbine shell matching surface is abutted to the nozzle ring matching surface to form a first sealing structure;
a nozzle ring accommodating groove is formed in one end, away from the pressure plate, of the turbine cavity, and when the nozzle ring is installed in the turbine cavity, one end, away from the pressure plate, of the nozzle ring is placed in the nozzle ring accommodating groove;
the nozzle ring is arranged in be equipped with labyrinth seal groove structure on the one end lateral wall of nozzle ring holding tank, be equipped with sealed shell fragment on its inner wall, be equipped with on the inside wall of nozzle ring holding tank with the corresponding sealed boss of sealed shell fragment, the nozzle ring is installed when the turbine intracavity, sealed shell fragment with follow between the sealed boss the axial direction of nozzle ring is interference fit, makes the side of sealed shell fragment with the terminal surface butt of sealed boss is in order to form second seal structure.
Furthermore, when the radial flow turbocharger is in a non-working state, the interference magnitude between the sealing elastic sheet and the sealing boss is 0-0.05 mm;
when the radial flow turbocharger is in a working state, the interference magnitude increment between the sealing elastic sheet and the sealing boss is not more than 0.01mm.
Furthermore, the thickness of the sealing elastic sheet is 0.5-0.6 mm, and the length is 1.8-2.2 mm.
Further, the surface roughness of the abutting surface of the sealing elastic sheet and the sealing boss is not more than Ra0.8.
Further, the nozzle ring is made of high-temperature alloy K418.
Furthermore, the labyrinth seal groove structure comprises two annular seal grooves, and the width and the depth of the annular seal groove close to one end of the nozzle ring accommodating groove opening are larger than those of the other annular seal groove.
Further, still be equipped with in the nozzle ring holding groove and be used for right the nozzle ring carries out a plurality of locating pins of circumference location.
Compared with the prior art, the radial flow turbocharger nozzle ring sealing structure disclosed by the invention has the following beneficial effects: because be equipped with labyrinth seal groove structure on the one end lateral wall of nozzle ring holding tank is arranged in to the nozzle ring, be equipped with sealed shell fragment on its inner wall, be equipped with sealed boss on the inside wall of nozzle ring holding tank, sealed shell fragment with be interference fit along the axial direction of nozzle ring between the sealed boss for the side of sealed shell fragment and the terminal surface butt of sealed boss are in order to form second seal structure, this application is through setting up the thin slice structure on the nozzle ring promptly, compress tightly through turbine shell terminal surface and thin slice and seal, good leakproofness has not only been guaranteed, make whole structure simpler, compact, and reached the purpose of eliminating the clearance.
Drawings
FIG. 1 is a partial schematic view of a nozzle ring seal structure of a radial flow turbocharger disclosed by the invention;
FIG. 2 is an enlarged partial schematic view of the dotted box of FIG. 1;
FIG. 3 is an enlarged view of a portion of a labyrinth seal groove configuration;
FIG. 4 is a schematic view showing the relationship between the sealing spring and the sealing boss in a cold state;
FIG. 5 is a schematic view showing the relationship between the sealing spring and the sealing boss in a hot state;
fig. 6 is a schematic view of gas flow when the radial flow turbocharger nozzle ring sealing structure disclosed by the invention works.
In the figure: 1. the nozzle ring comprises a support body, 2, a pressure plate, 3, a heat shield, 4, a nozzle ring, 40, a nozzle ring matching surface, 41, a labyrinth seal structure, 42, a seal elastic sheet, 43, an annular seal groove, 5, a turbine shell, 50, a turbine shell matching surface, 51, a turbine cavity, 52, a nozzle ring accommodating groove, 53, a seal boss, 54 and a positioning pin.
Detailed Description
Fig. 1 and 2 show a nozzle ring seal structure of a radial-flow turbocharger disclosed by the invention, which comprises a support body 1, a pressure plate 2, a heat shield 3, a nozzle ring 4 and a turbine shell 5;
the nozzle ring 4, the heat shield 3 and the support body 1 are sequentially mounted on the turbine shell 5 and are pressed and fixed by the pressure plate 2;
specifically, the turbine shell 5 mainly functions to collect and guide exhaust gas, a turbine cavity 51 is arranged in the turbine shell 5, the nozzle ring 4 is arranged in the turbine cavity 51, the nozzle ring 4 mainly functions to increase the flow rate of the exhaust gas to increase the rotation speed of a turbine arranged in the turbine cavity 51, the heat shield 3 is arranged between the nozzle ring 4 and the support body 1, the heat shield 3 mainly functions to isolate high-temperature exhaust gas entering the turbine shell 5 from the support body 1 and prevent the internal temperature of the support body 1 from being too high, the support body 1 mainly functions to connect a compressor housing and a turbine housing of a supercharger and is responsible for connection of oil inlet and return interfaces of a diesel engine, the end face of the support body 1 mounted on the turbine shell 5 is slightly higher than the flange face of the turbine shell by 0.1mm to 0.4mm, the pressure plate 2 is fixed on the flange face of the turbine shell 5 through bolts, and the pressure plate 2 mainly functions to compress the support body 1 and the turbine shell 5;
a turbine shell matching surface 50 is arranged at one end, close to the pressure plate 2, of the turbine shell 5, a nozzle ring matching surface 40 is arranged at one end, close to the pressure plate 2, of the nozzle ring 4, and when the nozzle ring 4 is installed in a turbine cavity 51 of the turbine shell 5, the turbine shell matching surface 50 is abutted to the nozzle ring matching surface 40 to form a first sealing structure;
a nozzle ring accommodating groove 52 is formed in one end, away from the pressure plate 2, of the turbine cavity 51, and when the nozzle ring 4 is installed in the turbine cavity 51, one end, away from the pressure plate 2, of the nozzle ring 4 is placed in the nozzle ring accommodating groove 52;
the nozzle ring 4 is arranged in be equipped with labyrinth seal groove structure 41 on the one end lateral wall of nozzle ring holding groove 52, be equipped with sealed shell fragment 42 on its inner wall, preferably, sealed shell fragment 42 and nozzle ring 4 structure as an organic whole, process out radial inside convex annular thin slice structure promptly on the inside wall of nozzle ring, be equipped with on the inside wall of nozzle ring holding groove 52 with the corresponding sealed boss 53 of sealed shell fragment 42, nozzle ring 4 is installed when in turbine chamber 51, sealed shell fragment 42 with follow between the sealed boss 53 the axial direction of nozzle ring 4 is interference fit, makes the side of sealed shell fragment 42 with the terminal surface butt of sealed boss 53 is in order to form second seal structure.
According to the radial flow turbocharger nozzle ring sealing structure, the sealing elastic sheet arranged on the nozzle ring and the sealing boss arranged in the nozzle ring accommodating groove are directly adopted for sealing, namely high-temperature gas is sealed through deformation of the sheet structure, so that the number of parts is reduced, other auxiliary sealing elements are not used, and the sealing effect is directly realized through structural matching of the parts; meanwhile, only the matching space of one slice is needed in the axial direction, so that the axial size is greatly saved, and the overall structure is simpler and more compact; the thin sheet is deformable, so that the matching can be ensured to be tightly attached, the sealing reliability is ensured, and the sealing performance at high temperature is better.
Further, as shown in fig. 4 and 5, when the radial flow turbocharger is in a non-working state (during cold assembly), the interference between the sealing elastic sheet 42 and the sealing boss 53 is 0mm to 0.05mm; when the radial-flow turbocharger is in a working state (a thermal state), the interference increment between the sealing elastic sheet 42 and the sealing boss 53 is not more than 0.01mm. The thickness of the sealing elastic sheet 42 is 0.5-0.6 mm, and the length is 1.8-2.2 mm; the surface roughness of the abutting surface of the sealing elastic sheet 42 and the sealing boss 53 is not more than Ra0.8; the nozzle ring 4 is made of high-temperature alloy K418, has good temperature resistance, still has low elastic limit at high temperature, and can generate reversible elastic deformation. In this way, it is ensured that after assembly in the cold state, a certain amount of elastic deformation of the lamellae is achieved, but that they do not break. In a hot state, the interference magnitude can be increased by calculation according to the matching size and the linear expansion coefficient of the material, but the interference magnitude is not more than 0.01mm, so that in a working state, the sealing performance can be kept well, and meanwhile, the sealing performance is guaranteed without fracture.
Further, as shown in fig. 3, the labyrinth seal groove structure 41 includes two annular seal grooves 43, the width and depth of the annular seal groove near the opening end of the nozzle ring receiving groove 52 are both greater than the width and depth of another annular seal groove, the width and depth of the front end seal groove are greater, sufficient labyrinth space is utilized to reduce the pressure of gas, the width and depth of the rear end seal groove are smaller, the axial space of the nozzle ring is shortened, the structure is compact, the purpose of optimizing the structural layout in a limited space is achieved, and the sealing performance at the nozzle ring is further improved. Specifically, as shown in fig. 6, the booster that this application discloses during operation, high temperature gas passes through the turbine shell, the nozzle ring enters into the turbine, for the turbine provides power, the gas flow says that the left side is to utilize the clamp plate to compress tightly the fitting surface of nozzle ring and turbine shell, the terminal surface press fit that utilizes nozzle ring and turbine shell seals the gas, the gas flow says that the right side at first seals through turbine shell and the radial complex twice labyrinth seal groove of nozzle ring, get into the clearance fit of the big terminal surface in nozzle ring right side and turbine shell terminal surface behind the seal groove, last nozzle ring below thin slice and turbine shell step face interference fit are in order to realize sealing on gas flow says the right side.
Further, as shown in fig. 1, a plurality of positioning pins for circumferentially positioning the nozzle ring are further arranged in the nozzle ring accommodating groove, in this embodiment, the nozzle ring is circumferentially positioned by 3 uniformly distributed pins to prevent the nozzle ring from rotating, and a gap of 0.1mm to 0.3mm is reserved between the nozzle ring and the fitting surface of the turbine shell to ensure that the fitting surface 50 of the turbine shell and the fitting surface 40 of the nozzle ring can be effectively abutted to form a first sealing structure.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (7)
1. The utility model provides a radial flow turbocharger nozzle ring seal structure which characterized in that: the turbine nozzle ring comprises a support body, a pressure plate, a heat shield, a nozzle ring and a turbine shell;
the nozzle ring, the heat shield and the support body are sequentially arranged on the turbine shell and are pressed and fixed by the pressure plate;
a turbine shell matching surface is arranged at one end, close to the pressure plate, of the turbine shell, a nozzle ring matching surface is arranged at one end, close to the pressure plate, of the nozzle ring, and when the nozzle ring is installed in a turbine cavity of the turbine shell, the turbine shell matching surface is abutted to the nozzle ring matching surface to form a first sealing structure;
a nozzle ring accommodating groove is formed in the end, far away from the pressure plate, of the turbine cavity, and when the nozzle ring is installed in the turbine cavity, the end, far away from the pressure plate, of the nozzle ring is arranged in the nozzle ring accommodating groove;
the nozzle ring is arranged in be equipped with labyrinth seal groove structure on the one end lateral wall of nozzle ring holding tank, be equipped with sealed shell fragment on its inner wall, be equipped with on the inside wall of nozzle ring holding tank with the corresponding sealed boss of sealed shell fragment, the nozzle ring is installed when the turbine intracavity, sealed shell fragment with follow between the sealed boss the axial direction of nozzle ring is interference fit, makes the side of sealed shell fragment with the terminal surface butt of sealed boss is in order to form second seal structure.
2. The radial flow turbocharger nozzle ring seal structure of claim 1, wherein:
when the radial flow turbocharger is in a non-working state, the interference magnitude between the sealing elastic sheet and the sealing boss is 0-0.05 mm;
when the radial flow turbocharger is in a working state, the interference magnitude increment between the sealing elastic sheet and the sealing boss is not more than 0.01mm.
3. The radial flow turbocharger nozzle ring seal structure according to claim 1 or 2, characterized in that: the thickness of the sealing elastic sheet is 0.5-0.6 mm, and the length of the sealing elastic sheet is 1.8-2.2 mm.
4. The radial flow turbocharger nozzle ring seal structure of claim 3, wherein: the surface roughness of the abutting surface of the sealing elastic sheet and the sealing boss is not more than Ra0.8.
5. The radial flow turbocharger nozzle ring seal structure of claim 4, wherein: the material of nozzle ring is superalloy K418.
6. The radial flow turbocharger nozzle ring seal structure of claim 1, wherein: the labyrinth seal groove structure comprises two annular seal grooves, and the width and the depth of the annular seal groove close to one end of the nozzle ring accommodating groove opening are both larger than those of the other annular seal groove.
7. The radial flow turbocharger nozzle ring seal structure of claim 1, wherein: still be equipped with in the nozzle cascade holding tank and be used for right the nozzle cascade carries out a plurality of locating pins of circumference location.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211119087.5A CN115306491A (en) | 2022-09-13 | 2022-09-13 | Radial flow turbocharger nozzle ring sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211119087.5A CN115306491A (en) | 2022-09-13 | 2022-09-13 | Radial flow turbocharger nozzle ring sealing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115306491A true CN115306491A (en) | 2022-11-08 |
Family
ID=83867281
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211119087.5A Pending CN115306491A (en) | 2022-09-13 | 2022-09-13 | Radial flow turbocharger nozzle ring sealing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115306491A (en) |
-
2022
- 2022-09-13 CN CN202211119087.5A patent/CN115306491A/en active Pending
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