CN110541753A - Turbo charger turbine cooling device that admits air - Google Patents

Turbo charger turbine cooling device that admits air Download PDF

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Publication number
CN110541753A
CN110541753A CN201910940721.3A CN201910940721A CN110541753A CN 110541753 A CN110541753 A CN 110541753A CN 201910940721 A CN201910940721 A CN 201910940721A CN 110541753 A CN110541753 A CN 110541753A
Authority
CN
China
Prior art keywords
compressor
turbine
outlet pipe
venturi tube
air
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.)
Pending
Application number
CN201910940721.3A
Other languages
Chinese (zh)
Inventor
赵国昌
张文明
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Civil Aviation University of China
Original Assignee
Civil Aviation University of China
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Civil Aviation University of China filed Critical Civil Aviation University of China
Priority to CN201910940721.3A priority Critical patent/CN110541753A/en
Publication of CN110541753A publication Critical patent/CN110541753A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)

Abstract

A turbocharger turbine inlet air cooling device. The engine exhaust manifold 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 invention can cool the overheated tail gas entering the turbine in the pipeline, thereby effectively reducing the thermal damage of the turbine and prolonging the service life of the turbine.

Description

Turbo charger turbine cooling device that admits air
Technical Field
The invention belongs to the technical field of turbochargers, and particularly relates to a turbocharger turbine inlet air cooling device.
Background
The turbocharger utilizes waste gas generated during combustion of the engine to push the turbine so as to drive the compressor to rotate, thereby achieving the purpose of increasing the air input of the engine and the power of the engine. In order to meet the increasingly strict emission regulations and achieve the best emission effect, for a gasoline supercharged engine, it is always desirable to control the air-fuel ratio of the engine to the optimum exhaust gas conversion air-fuel ratio when closed-loop control conditions are met. However, as engine load and speed increase, the exhaust temperature may increase beyond or near the tolerance of the turbine if controlled at the optimum exhaust gas conversion air-fuel ratio at all times. The prior turbocharger cooling method mainly cools a volute and a turbocharger bearing, but the prior turbocharger cooling method can cause thermal damage to a turbine, so that the service life of the turbine is shortened.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a turbocharger turbine inlet air temperature reducing device.
In order to achieve the purpose, the turbocharger turbine inlet air cooling device provided by the invention comprises an engine exhaust manifold interface, a compressor air outlet pipe, a turbine, a venturi tube, a compressor air outlet pipe branch pipe, a one-way valve, a compressor shell and a volute; the compressor is arranged in the compressor shell; the turbine is arranged in the volute, and the compressor and the turbine are coaxially arranged; one side of the compressor shell is provided with a compressor air inlet; the inner end of the gas outlet pipe of the gas compressor is communicated with the gas compressor shell; one side of the volute is provided with a turbine air outlet; the inner end of the Venturi tube is connected with a turbine air inlet positioned on the volute, and the outer end of the Venturi tube is a Venturi tube throat; the inner end of the engine exhaust manifold interface is connected with the outer end of the venturi tube throat; one end of a branch pipe of the 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 to the side surface of the 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 one side of the throat pipe of the Venturi tube from one side of the air outlet pipe of the compressor.
the check valve is a pneumatic or electric check valve.
The turbocharger turbine air inlet cooling device provided by the invention has the beneficial effects that: the temperature of the overheated tail gas entering the turbine can be reduced in the pipeline, so that the thermal damage of the turbine can be effectively reduced, and the service life of the turbine is prolonged.
Drawings
FIG. 1 is a schematic structural diagram of a turbocharger turbine inlet air temperature reduction device provided by the invention.
Detailed Description
The invention is further described below with reference to the figures and examples.
As shown in fig. 1, the turbocharger turbine inlet air cooling device provided by the invention comprises an engine exhaust manifold interface 1, a compressor 2, a compressor outlet pipe 4, a turbine 5, a venturi tube 8, a compressor outlet pipe branch pipe 10, a one-way valve 11, a compressor shell 12 and a volute 13; wherein, the compressor 2 is arranged inside the compressor shell 12; the turbine 5 is arranged inside the volute 13, and the compressor 2 and the turbine 5 are coaxially arranged; one side of the compressor shell 12 is provided with a compressor air inlet 3; the inner end of the gas outlet pipe 4 of the compressor is communicated with the compressor shell 12; a turbine air outlet 7 is arranged on one side of the volute 13; the inner end of the Venturi tube 8 is connected with the turbine air inlet 6 on the volute 13, and the outer end of the Venturi tube 8 is a Venturi tube throat 9; the inner end of the engine exhaust manifold interface 1 is connected with the outer end of the venturi tube throat 9; one end of a compressor air outlet pipe branch pipe 10 is connected with a compressor air outlet pipe 4, and the other end is connected to the side surface of a venturi tube throat pipe 9; the one-way valve 11 is arranged on the compressor air outlet pipe 4, and the air flow flows from the compressor air outlet pipe 4 side to the venturi tube throat 9 side.
The check valve 11 is a pneumatic or electric check valve.
The working principle of the turbocharger turbine inlet air cooling device provided by the invention is explained as follows:
In the working process of the turbocharger, waste gas flows into a Venturi tube 8 from an engine exhaust manifold interface 1 through a Venturi tube throat 9, then enters the inner part of a volute 13 through a turbine air inlet 6, then drives a turbine 5 and a coaxially arranged compressor 2 to rotate together, and then flows out through a turbine air outlet 7; meanwhile, air enters the interior of the compressor shell 12 through the compressor air inlet 3, is pressurized by the compressor 2, and then flows into the compressor air outlet pipe 4 to be discharged outwards. When the exhaust gas flows through the venturi throat 9, the pressure drops below the pressure in the compressor outlet duct 4 due to the increased flow velocity. When the temperature of the exhaust gas exceeds a set value, the one-way valve 11 is opened, and then the air flow in the compressor air outlet pipe 4 flows into the venturi tube throat 9 through the one-way valve 11, then flows into the upper part of the venturi tube 8, is mixed with the exhaust gas from the engine exhaust manifold interface 1, and then enters the interior of the volute 13 through the turbine air inlet 6. Because the temperature of the air flow in the air outlet pipe 4 of the compressor is far lower than that of the exhaust gas flow, the temperature of the exhaust gas at the inlet of the turbine can be reduced. The air flow passing through the valve can be controlled by adjusting the opening size of the valve on the one-way valve 11, so that the air-entraining quantity from the air compressor 2 can meet the requirement of the turbine 5 on air intake cooling, and the loss of the air intake quantity of the engine can be reduced as much as possible.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.

Claims (2)

1. The utility model provides a turbo charger turbine cooling device that admits air which characterized in that: the turbocharger turbine inlet air cooling device comprises an engine exhaust manifold interface (1), a compressor (2), a compressor outlet pipe (4), a turbine (5), a Venturi tube (8), a compressor outlet pipe branch pipe (10), a one-way valve (11), a compressor shell (12) and a volute (13); the compressor (2) is arranged inside the compressor shell (12); the turbine (5) is arranged inside the volute (13), and the compressor (2) and the turbine (5) are coaxially arranged; one side of the compressor shell (12) is provided with a compressor air inlet (3); the inner end of the gas outlet pipe (4) of the gas compressor is communicated with the gas compressor shell (12); a turbine air outlet (7) is arranged on one side of the volute (13); the inner end of the Venturi tube (8) is connected with a turbine air inlet (6) on the volute (13), and the outer end of the Venturi tube is a Venturi tube throat (9); the inner end of the engine exhaust manifold interface (1) is connected with the outer end of the venturi tube throat (9); one end of a compressor air outlet pipe branch pipe (10) is connected with a compressor air outlet pipe (4), and the other end of the compressor air outlet pipe branch pipe is connected to the side surface of a venturi tube throat (9); the one-way valve (11) is arranged on the air outlet pipe (4) of the compressor, and the air flow flows to one side of the venturi tube throat (9) from one side of the air outlet pipe (4) of the compressor.
2. The turbocharger turbine inlet air temperature reduction device according to claim 1, characterized in that: the check valve (11) is a pneumatic or electric check valve.
CN201910940721.3A 2019-09-30 2019-09-30 Turbo charger turbine cooling device that admits air Pending CN110541753A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910940721.3A CN110541753A (en) 2019-09-30 2019-09-30 Turbo charger turbine cooling device that admits air

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910940721.3A CN110541753A (en) 2019-09-30 2019-09-30 Turbo charger turbine cooling device that admits air

Publications (1)

Publication Number Publication Date
CN110541753A true CN110541753A (en) 2019-12-06

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Family Applications (1)

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Country Status (1)

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CN (1) CN110541753A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT6106U1 (en) * 2002-03-14 2003-04-25 Avl List Gmbh INTERNAL COMBUSTION ENGINE WITH TWO-STAGE CHARGING
US20040006978A1 (en) * 2002-07-11 2004-01-15 Clean Air Products, Inc. EGR control system and method for an internal combustion engine
JP2005299618A (en) * 2004-04-16 2005-10-27 Hino Motors Ltd Turbocharger control mechanism
DE102011010742A1 (en) * 2011-02-09 2012-08-09 Daimler Ag Internal combustion engine i.e. petrol engine, for e.g. passenger car, has turbine drivable by exhaust gas of engine, where air is guided upstream to turbine from air-intake by cooling device for partially cooling exhaust gas tract
CN103306858A (en) * 2013-05-31 2013-09-18 潍柴动力股份有限公司 EGR (exhaust gas recirculation) air mixing device and fuel engine with EGR system
CN210564755U (en) * 2019-09-30 2020-05-19 中国民航大学 Turbo charger turbine cooling device that admits air

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT6106U1 (en) * 2002-03-14 2003-04-25 Avl List Gmbh INTERNAL COMBUSTION ENGINE WITH TWO-STAGE CHARGING
US20040006978A1 (en) * 2002-07-11 2004-01-15 Clean Air Products, Inc. EGR control system and method for an internal combustion engine
JP2005299618A (en) * 2004-04-16 2005-10-27 Hino Motors Ltd Turbocharger control mechanism
DE102011010742A1 (en) * 2011-02-09 2012-08-09 Daimler Ag Internal combustion engine i.e. petrol engine, for e.g. passenger car, has turbine drivable by exhaust gas of engine, where air is guided upstream to turbine from air-intake by cooling device for partially cooling exhaust gas tract
CN103306858A (en) * 2013-05-31 2013-09-18 潍柴动力股份有限公司 EGR (exhaust gas recirculation) air mixing device and fuel engine with EGR system
CN210564755U (en) * 2019-09-30 2020-05-19 中国民航大学 Turbo charger turbine cooling device that admits air

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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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