CN213116453U - Turbocharger capable of cooling turbine - Google Patents
Turbocharger capable of cooling turbine Download PDFInfo
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- CN213116453U CN213116453U CN202020893384.5U CN202020893384U CN213116453U CN 213116453 U CN213116453 U CN 213116453U CN 202020893384 U CN202020893384 U CN 202020893384U CN 213116453 U CN213116453 U CN 213116453U
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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
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- Y02T10/12—Improving ICE efficiencies
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Abstract
The utility model provides a can be for turbo charger of turbine cooling, relates to turbo charger cooling apparatus technical field, includes and introduces the cooling gas to the turbine back of the body dish for carry out the heat sink of cooling to the turbine. The utility model provides a booster among the conventional art, introduce the cooling gas from the export of compressor, cool down turbine through-flow medium, lead to having reduced the preceding temperature of whirlpool, make turbine acting capacity descend, can not satisfy operation requirement's problem.
Description
Technical Field
The utility model relates to a turbo charger cooling apparatus technical field, concretely relates to can be for turbo charger of turbine cooling.
Background
The turbocharger utilizes waste gas generated during combustion of an engine to push a turbine so as to drive an impeller of a gas compressor to rotate and apply work, thereby achieving the purposes of increasing the air inlet pressure and the air inlet amount of the engine and further improving the power of the engine. The turbine of the turbocharger is one of the most important key parts, is acted by high-temperature and high-pressure gas, has severe working conditions and is one of the parts with the highest failure rate of the turbocharger. The failure mode of thermal-mechanical low-cycle fatigue fracture occupies more than 15% of the failure of the whole supercharger under the combined action of centrifugal force and thermal stress on the turbine back disc.
With the increasing strictness of the engine strengthening requirements and emission regulations, the exhaust temperature of the engine, namely the inlet temperature of the turbine, is increased continuously, so that the heat load of the turbine is increased continuously, the thermal stress is increased correspondingly, and the mechanical property of the material is greatly reduced due to the increase of the temperature of the turbine. On the basis of the existing structure, the low-cycle fatigue life of the turbine back plate is greatly reduced under the high-speed and high-load working condition of the engine.
In response to the new supercharging technical requirements, if the supercharger shafting and the turbine are redesigned, the large modification of the existing supercharger product platform is necessarily involved, a large amount of shafting verification work needs to be carried out again, and the development investment of a large amount of new dies is generated. Therefore, how to solve the reliability of the turbocharger turbine under the high-speed and high-load working condition of the engine on the platform of the existing supercharger product, particularly reduce the thermal stress of the turbine back plate under the high vortex front temperature, thereby improving the low-cycle fatigue life of the turbocharger turbine, and is a problem which needs to be solved by technical personnel in the field of the existing supercharging technology.
Through the search of the prior art documents, Chinese patent application No. 201910940721.3, the scheme comprises an engine exhaust manifold interface, a gas compressor gas outlet pipe, a turbine, a Venturi tube, a gas compressor gas outlet pipe branch pipe, a one-way valve, a gas compressor shell and a volute; the compressor is arranged in the compressor shell; the turbine is arranged in the volute and is coaxial with the compressor; one side of the compressor shell is provided with a compressor air inlet; the air outlet pipe of the compressor is communicated with the compressor shell; one side of the volute is provided with a turbine air outlet; the inner end of the Venturi tube is connected with the air inlet of the turbine, and the outer end of the Venturi tube is a Venturi tube throat; the engine exhaust manifold interface is connected with the venturi tube throat; one end of a branch pipe of a gas outlet pipe of the gas compressor is connected with the gas outlet pipe of the gas compressor, and the other end of the branch pipe of the gas outlet pipe of the gas compressor is connected with a throat pipe of the Venturi tube; the one-way valve is arranged on the air outlet pipe of the compressor, and the air flow flows to the venturi tube throat from the air outlet pipe of the compressor. The utility model discloses can cool down the overheated tail gas that gets into the turbine in pipeline inside, consequently can more effectively reduce the heat damage of turbine, prolong the working life of turbine, the device is along with using also gradual the weak point that has exposed this technique, mainly shows in following aspect:
the patent discloses that cooling gas is introduced from an outlet of a gas compressor to enter an inlet of a turbine, through-flow medium of the turbine is cooled by mixing cold gas and high-temperature gas, the purpose of reducing heat damage of a turbine rotor is achieved, but the temperature before a turbine is reduced, so that the work capacity of the turbine is reduced, and the use requirement cannot be met.
In summary, the prior art has obvious inconvenience and disadvantages in practical use, and needs to be improved.
SUMMERY OF THE UTILITY MODEL
To the defect among the prior art, the utility model provides a can be for turbo charger of turbine cooling for solve the booster among the conventional art, introduce the cooling gas from the export of compressor, cool down to turbine through-flow medium, lead to having reduced the preceding temperature of whirlpool, make turbine acting capacity descend, can not satisfy operation requirement's problem.
In order to solve the above problem, the utility model provides a following technical scheme:
a turbocharger capable of cooling a turbine comprises a cooling device for introducing cooling air to a turbine back plate to cool the turbine.
As an optimized scheme, the cooling device further comprises a heat shield arranged between the turbine and the middle shell.
As an optimized scheme, the middle shell is provided with a drainage groove for introducing cooling air to the area between the heat shield and the middle shell.
As an optimized scheme, a cooling cavity is further arranged between the turbine back plate and the heat shield, and a flow guide gap communicated with the cooling cavity is further arranged between the heat shield and the middle shell.
As an optimized scheme, the middle shell is also provided with an air-entraining port communicated with the drainage groove.
As an optimized scheme, a bleed air pipe is installed on the bleed air port, and the inlet end of the bleed air pipe is connected with an outlet of an intercooler.
As an optimized scheme, a switch control valve is further installed on the air guide pipe.
As an optimized scheme, the heat shield comprises an arc-shaped cylinder, one end of the arc-shaped cylinder is gathered towards the center of the arc-shaped cylinder and fixedly connected with a first end ring, and the other end of the arc-shaped cylinder is fixedly connected with a second end ring in a peripheral diffusion mode.
Preferably, the flow guide gap is formed between the inner ring of the first end ring and the intermediate shell.
Preferably, the second end ring is sandwiched between the intermediate shell and the turbine shell.
Compared with the prior art, the beneficial effects of the utility model are that:
the gas cooled by the intercooler enters the cooling cavity, and the temperature of the cooled gas is about 50 ℃ which is far lower than the temperature of the gas of the turbine, so that the temperature of the back plate of the turbine can be greatly reduced, and the aims of reducing the thermal stress of the turbine and prolonging the service life of the turbine can be fulfilled; the opening degree of the switch control valve is controlled by the engine control unit, so that the air inflow can be controlled according to the temperature before the turbine, the temperature of the turbine can be accurately controlled, and the loss of the air inflow of the engine is reduced; cooling gas is directly introduced into the turbine back disc to directly cool the turbine rotor, and the temperature before the turbine is not influenced by the cooling gas, so that the temperature of the turbine rotor is reduced and the reliability of the turbine rotor is improved on the premise of ensuring the working capacity of the turbine; the utility model realizes the great reduction of the temperature of the back plate turbine without changing the shafting structure and the mould of the prior turbocharger, and has simple structure, easy implementation and low product cost; the production cost is greatly reduced; and the problem that the traditional technology is constructed by complex parts is overcome; the structure is simple, and the assembly process steps are simple and convenient; the structure is simple, and the service life is long; simple structure and stable operation.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the cooling device of the present invention;
in the figure: 1. the gas turbine comprises an engine, 2, an exhaust manifold, 3, an air inlet pipe, 4, an intercooler, 5, a gas guide pipe, 6, an on-off control valve, 7, a middle shell, 71, a flow guide groove, 8, a compressor shell, 81, a compressor shell air outlet, 82, a compressor shell air inlet, 9, a turbine shell, 91, a turbine shell air outlet, 92, a turbine shell air inlet, 10, a turbine, 101, a turbine back plate, 102, a cooling cavity, 11, an impeller, 12, a heat insulation cover, 13, a first end ring, 14 and a second end ring.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.
As shown in fig. 1 and 2, the turbocharger capable of cooling the turbine includes a cooling device for introducing cooling air to a turbine back plate 101 to cool the turbine 10.
The cooling device further comprises a heat shield 12 arranged between the turbine 10 and the intermediate casing 7.
The intermediate case 7 is formed with a flow guide groove 71 for introducing cooling air to a region between the heat shield 12 and the intermediate case 7.
A cooling cavity 102 is further arranged between the turbine back disc 101 and the heat shield 12, and a flow guide gap communicated with the cooling cavity 102 is further arranged between the heat shield 12 and the middle shell 7.
The middle shell 7 is also provided with a bleed port communicated with the drainage groove 71.
The air-entraining port is provided with an air-entraining pipe 5, and the inlet end of the air-entraining pipe 5 is connected with the outlet of the intercooler 4.
The bleed air pipe 5 is also provided with a switch control valve 6.
The heat shield 12 includes an arc-shaped tube, one end of the arc-shaped tube is fixedly connected with a first end ring 13 in a gathering manner toward the center, and the other end of the arc-shaped tube is fixedly connected with a second end ring 14 in a diffusing manner toward the periphery.
A flow guiding gap is formed between the inner ring of the first end ring 13 and the middle shell 7.
The second end ring 14 is clamped between the intermediate shell 7 and the turbine shell 9.
The turbocharger with the turbine 10 further comprises a compressor shell 8, an intermediate shell 7, a turbine 10, an impeller 11, a turbine shell 9, a heat shield 12, a bleed air pipe 5 and a switch control valve 6; the turbine 10 is mounted inside the turbine housing 9,
the turbine 10 is provided with a turbine back disc 101 structure, a heat shield 12 is arranged between the turbine 10 and the intermediate shell 7, a cooling cavity 102 is arranged in the area between the turbine back disc 101 and the heat shield 12 and the intermediate shell 7, the impeller 11 is arranged inside the compressor casing 8, the turbine 10 and the impeller 11 are connected through a shaft, and when the turbine 10 rotates, the impeller 11 also rotates; the side of the compressor shell 8, which is far away from the middle shell 7, is provided with a compressor air inlet, and the side of the compressor shell, which is close to the middle shell 7, is provided with a compressor air outlet; have drainage groove 71 structure on the middle casing 7, the compressor gas outlet passes through the pipeline with 4 one end of intercooler and communicates, the 4 other end of intercooler links to each other with 3 one end of intake pipe, the intake pipe 3 other end links to each other with engine 1, bleed pipe 5 one end is connected to on the intake pipe 3 lateral wall, the other end and drainage groove 71 intercommunication, install on the bleed pipe 5 on the on-off control valve 6, on-off control valve 6 opens when the temperature surpasses the setting value before the whirlpool of turbine casing 9, the air current gets into drainage groove 71 through bleed pipe 5 from intake pipe 3, the air current that comes out from drainage groove 71 gets into cooling cavity 102 through the space between heat exchanger 12 and middle casing 7, cool off turbine dorsal disk 101.
The on-off control valve 6 is an electromagnetic check valve, and can be controlled by the control unit of the engine 1.
The bleed air pipe 5 is connected with the drainage groove 71 through threads.
The working principle is as follows:
in the working process of the turbocharger, exhaust gas exhausted from the engine 1 reaches a turbine shell air inlet 92 through an exhaust manifold 2, enters the turbine shell 9 from the turbine shell air inlet 92 to blow the turbine 10 to rotate, further drives an impeller 11 coaxially connected with the turbine 10 to rotate, and then is exhausted from a turbine shell air outlet 91; meanwhile, air enters the compressor housing 8 from the compressor housing air inlet 82, the air is discharged out of the compressor housing 8 from the compressor housing air outlet 81 due to the rotation of the impeller 11, and the discharged air enters the air inlet pipe 3 after being cooled by the intercooler 4; meanwhile, if the turbine front temperature of the turbine shell 9 reaches a set value, the engine control unit controls the on-off control valve 6 to be opened, part of the airflow in the air inlet pipe 3 flows into the diversion groove 71 through the air guide pipe 5, and the airflow coming out of the diversion groove 71 enters the cooling cavity 102 through a gap between the heat shield 12 and the middle shell 7; because the temperature of the gas from the flow guide groove 71 is far lower than the temperature of the gas of the turbine, the temperature of the turbine back plate 101 can be greatly reduced, and the gap between the heat shield 12 and the middle shell 7 is far away from the gas inlet 92 of the turbine shell, the cold gas can not reduce the temperature before the turbine, so that the thermal stress of the turbine 10 can be reduced, the service life of the turbine 10 can be prolonged, and the working capacity of the turbine can not be reduced; the opening degree of the on-off control valve 6 is controlled by the engine control unit, and the size of the air inflow can be controlled by the temperature before the vortex, so that the loss of the air inflow of the engine 1 is reduced.
The patent has the advantages over the patent publication that: according to the working principle of the turbine, the temperature before the vortex is important for the working of the turbine, so the main purpose of improving the temperature before the vortex of the turbine is to improve the working capacity of the turbine, and the disadvantages of increased thermal load of a turbine rotor and reduced reliability are brought. The patent publication makes use of the compressor outlet bleed air to mix with the turbine main flow, which, although it is possible to reduce the thermal load on the turbine rotor, also reduces the pre-vortex temperature, thus adversely affecting the increase in the work capacity of the turbine. The patent of this application-simulating has avoided the disadvantage of disclosing the patent, directly introduces the turbine back of the body dish with the cooling gas and directly cools off turbine rotor, and the temperature does not receive the influence of cooling gas before the whirlpool to under the prerequisite of guaranteeing higher temperature before the whirlpool, guarantee promptly under the prerequisite of turbine working capacity, reduce turbine rotor temperature, improve its reliability.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the scope of the embodiments of the present invention, and are intended to be covered by the claims and the specification.
Claims (9)
1. A turbocharger capable of cooling a turbine, characterized in that: comprises a cooling device which introduces cooling gas into a turbine back disc (101) and is used for cooling the turbine (10);
the cooling device further comprises a heat shield (12) arranged between the turbine (10) and the middle shell (7).
2. A turbocharger according to claim 1, wherein the turbine is cooled by: the middle shell (7) is provided with a drainage groove (71) used for introducing cooling air to the area between the heat shield (12) and the middle shell (7).
3. A turbocharger according to claim 1, wherein the turbine is cooled by: a cooling cavity (102) is further arranged between the turbine back plate (101) and the heat shield (12), and a flow guide gap communicated with the cooling cavity (102) is further arranged between the heat shield (12) and the middle shell (7).
4. A turbocharger according to claim 2, wherein the turbine is cooled by: and the middle shell (7) is also provided with an air-entraining port communicated with the drainage groove (71).
5. A turbocharger according to claim 4, wherein the turbine is cooled by: the air entraining port is provided with an air entraining pipe (5), and the inlet end of the air entraining pipe (5) is connected with the outlet of the intercooler (4).
6. A turbocharger according to claim 5, wherein the turbine is cooled by: and the air guide pipe (5) is also provided with a switch control valve (6).
7. A turbocharger according to claim 3, wherein the turbine is cooled by: the heat shield (12) comprises an arc-shaped cylinder, one end of the arc-shaped cylinder is gathered towards the center of the arc-shaped cylinder and fixedly connected with a first end ring (13), and the other end of the arc-shaped cylinder is fixedly connected with a second end ring (14) towards the periphery in a diffusion mode.
8. A turbocharger according to claim 7, wherein the turbine is cooled by: the flow guiding gap is formed between the inner ring of the first end ring (13) and the middle shell (7).
9. A turbocharger according to claim 7, wherein the turbine is cooled by: the second end ring (14) is clamped between the intermediate shell (7) and the turbine shell (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020893384.5U CN213116453U (en) | 2020-05-25 | 2020-05-25 | Turbocharger capable of cooling turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020893384.5U CN213116453U (en) | 2020-05-25 | 2020-05-25 | Turbocharger capable of cooling turbine |
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| CN213116453U true CN213116453U (en) | 2021-05-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020893384.5U Active CN213116453U (en) | 2020-05-25 | 2020-05-25 | Turbocharger capable of cooling turbine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113741580A (en) * | 2021-07-14 | 2021-12-03 | 潍坊科技学院 | Gas-liquid cooperative temperature control system and temperature control method for turbocharger |
| CN113738517A (en) * | 2021-10-12 | 2021-12-03 | 上海交通大学 | Real-time state diagnosis-based adaptive control method for variable-altitude supercharging system |
-
2020
- 2020-05-25 CN CN202020893384.5U patent/CN213116453U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113741580A (en) * | 2021-07-14 | 2021-12-03 | 潍坊科技学院 | Gas-liquid cooperative temperature control system and temperature control method for turbocharger |
| CN113738517A (en) * | 2021-10-12 | 2021-12-03 | 上海交通大学 | Real-time state diagnosis-based adaptive control method for variable-altitude supercharging system |
| CN113738517B (en) * | 2021-10-12 | 2022-08-09 | 上海交通大学 | Real-time state diagnosis-based adaptive control method for variable-altitude supercharging system |
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