WO2013120449A1 - Appareil composite comprenant des turbines contrarotatives et système de moteur comprenant cet appareil - Google Patents

Appareil composite comprenant des turbines contrarotatives et système de moteur comprenant cet appareil Download PDF

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Publication number
WO2013120449A1
WO2013120449A1 PCT/CN2013/071577 CN2013071577W WO2013120449A1 WO 2013120449 A1 WO2013120449 A1 WO 2013120449A1 CN 2013071577 W CN2013071577 W CN 2013071577W WO 2013120449 A1 WO2013120449 A1 WO 2013120449A1
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WO
WIPO (PCT)
Prior art keywords
turbine
engine
power turbine
power
counter
Prior art date
Application number
PCT/CN2013/071577
Other languages
English (en)
Chinese (zh)
Inventor
张扬军
赵荣超
诸葛伟林
郑新前
张俊跃
胡力峰
Original Assignee
清华大学
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 清华大学 filed Critical 清华大学
Publication of WO2013120449A1 publication Critical patent/WO2013120449A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N5/00—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy
    • F01N5/04—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy the devices using kinetic energy
    • 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
    • F02B37/004—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust drives arranged in series
    • 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
    • F02B41/00—Engines characterised by special means for improving conversion of heat or pressure energy into mechanical power
    • F02B41/02—Engines with prolonged expansion
    • F02B41/10—Engines with prolonged expansion in exhaust turbines
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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

Definitions

  • the present invention relates to the field of exhaust gas recovery systems for internal combustion engines, and more particularly to a counter-rotating turbine composite device and an engine system having the same. Background technique
  • a turbo compound In an internal combustion engine, a turbo compound is used to recover exhaust gas energy of an internal combustion engine, thereby improving the efficiency of the internal combustion engine.
  • a turbocharger and a power turbine are connected in series in the exhaust pipe of the turbo compound engine.
  • the turbocharger is used to drive the compressor to increase the intake density and increase the engine cylinder lift power.
  • the power turbine is used to recover the exhaust energy and convert it into a mechanical machine. Power output to improve total engine power and fuel economy.
  • Power turbines are typically installed downstream of the booster turbine, and the overall efficiency of the booster turbine and power turbine has a significant impact on engine performance.
  • the matching between the supercharged turbine and the power turbine is mainly based on flow matching.
  • the design of the supercharged turbine and the power turbine is relatively independent.
  • the coupling between the supercharged turbine outlet flow field and the power turbine inlet flow field is not considered, so the inlet of the power turbine needs to be installed.
  • the guide vanes adjust the air flow at the outlet of the booster turbine to ensure that the airflow enters the rotor of the power turbine at a suitable angle for work.
  • the present invention is based on the discovery by the inventors of the fact that the guide vanes between the outlet of the supercharged turbine and the inlet of the power turbine increase the axial length of the turbocompound system, resulting in a larger volume of the turbocompound system; Loss and reduce the efficiency of the turbocompound system; The installation angle of the guide vanes is fixed, which can only meet the matching requirements of the turbocharger and the power turbine of a specific operating condition of the engine, resulting in poor adaptability of the turbine composite system.
  • Another object of the present invention is to provide an engine system having the above-described counter-rotating turbo compounding device.
  • a counter-rotating turbo compound device includes: a turbocharger; and a power turbine, the power turbine being coupled to the booster turbine, and the power turbine and the turbocharger
  • the axes of rotation are the same and the directions of rotation are opposite, the blade inlet angle of the power turbine rotor being configured to match the blade exit angle of the boost turbine such that the outlet airflow of the boost turbine directly enters the power turbine at a predetermined angle Work inside the rotor.
  • a counter-rotating turbocombiner by configuring a blade inlet angle of a power turbine rotor to match a blade exit angle of a boost turbine such that an outlet flow of the boost turbine directly enters the rotor of the power turbine at a predetermined angle Work, compared with the traditional turbo composite device, the guide vanes between the supercharged turbine and the power turbine are eliminated, the structure is more compact, and the flow loss caused by the guide vanes is avoided, thereby improving the overall efficiency of the turbo compound device and the engine row.
  • the utilization of gas energy improves the fuel economy of the engine.
  • the counter-rotating turbo compounding device has the following additional technical features:
  • the booster turbine is a radial turbine.
  • the booster turbine is a mixed flow turbine.
  • the power turbine is an axial flow turbine.
  • the blade exit angle of the power turbine is configured to cause the outlet airflow of the power turbine to flow at a speed close to the axial direction. Thereby, the kinetic energy loss of the power turbine is reduced.
  • An engine system comprising: an engine; a counter-rotating turbo compound device according to an embodiment of the first aspect of the present invention, wherein the booster turbine is installed downstream of an exhaust manifold of the engine Receiving a flow of air exhausted by the engine, and the power turbine is disposed downstream of the booster turbine; a compressor that is coupled to the booster turbine and driven by the booster turbine to enter The air flow is supercharged; an intercooler connected between the compressor and the cylinder of the engine to cool and feed the supercharged airflow into the cylinder of the engine; and hydraulic a coupler, an input shaft of the fluid coupling and the power turbine according to an embodiment of the present invention, by providing a counter-rotating turbo compound device, making the engine system compact, fully utilizing waste energy, and improving engine fuel economy , reduce harmful gas emissions and improve the overall performance of the engine system.
  • the engine system further includes: a first transmission assembly coupled between the input shaft of the fluid coupling and the power turbine.
  • the engine system further includes: a second transmission assembly coupled between the output shaft of the fluid coupling and the crankshaft.
  • the first transmission component and the second transmission component are respectively a primary gear transmission component.
  • the turbocharger is coaxially connected with the compressor, and the turbocharger drives the compressor to pressurize the airflow entering the compressor, and the supercharged airflow is cooled by the intercooler and then enters the engine.
  • the turbocharger drives the compressor to pressurize the airflow entering the compressor, and the supercharged airflow is cooled by the intercooler and then enters the engine.
  • the exhaust gas after the engine works enters the blades of the supercharged turbine, and then flows out of the supercharged turbine in the axial direction. After passing through the cavity formed by the body and the outer wall, it enters the power turbine axially, and the power turbine will exhaust the energy of the exhaust gas.
  • the power turbine Converting to mechanical work, the power turbine is connected to the input shaft of the fluid coupling via the first transmission component, and the output shaft of the fluid coupling is connected to the crankshaft of the engine via the second transmission component, and finally the recovery work of the power turbine is transmitted to the crankshaft.
  • the total engine power and fuel economy are improved, and the conventional guide vanes are eliminated, the flow loss is reduced, the efficiency of the turbo compound device is improved, and the overall performance of the engine system is improved, and the engine system structure is more compact.
  • FIG. 1 is a cross-sectional view of a counter-rotating turbo compounding device in accordance with an embodiment of the present invention
  • FIG. 2 is a schematic view showing the blade shape of the counter-rotating turbo compound device of the radial turbine shown in FIG. 1;
  • FIG. 3 is a blade type of the counter-rotating turbo compound device of the turbo turbine shown in FIG. Schematic;
  • Figure 4 is a schematic illustration of an engine system in accordance with an embodiment of the present invention. detailed description
  • first and second are used for descriptive purposes only, and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defining “first” and “second” may explicitly or implicitly include one or more of the features. Further, in the description of the present invention, “multiple” means two or more unless otherwise stated.
  • the structure of the first feature described below "on" the second feature may include embodiments in which the first and second features are formed in direct contact, and may include additional features formed between the first and second features. The embodiment, such that the first and second features may not be in direct contact.
  • a counter-rotating turbo compound device 100 which is disposed in an engine system 200 for recovering engine exhaust energy, that is, exhaust gas, is described below with reference to FIGS. The energy that it has.
  • the counter-rotating turbo compound device 100 includes: a turbocharger 1 and a power turbine 2, wherein the power turbine 2 is coupled with the turbocharger 1 and the power turbine 2 is supercharged
  • the rotation axes of the turbine 1 are the same and the rotation directions are opposite, and the blade inlet angle (not shown) of the power turbine 2 rotor is configured to match the blade exit angle (not shown) of the turbocharger 1 to make the turbocharger 1
  • the outlet airflow directly enters the rotor of the power turbine 2 at a predetermined angle to perform work. As shown by the arrows in Fig.
  • the exhaust gas first enters into the vane 10 of the supercharged turbine 1, and then flows out of the supercharging turbine 1 in the axial direction, passes through the cavity 22 formed by the crucible 20 and the outer wall 21, and enters in the axial direction.
  • the power turbine 2 finally flows out of the power turbine 2.
  • the counter-rotating turbo compound device 100 configures the blade inlet angle of the power turbine 2 rotor to match the blade exit angle of the turbocharger 1 such that the outlet airflow of the turbocharger 1 directly enters the power at a predetermined angle
  • the work in the rotor of the turbine 2 eliminates the guide vanes between the supercharged turbine and the power turbine compared to the conventional turbo composite device, the structure is more compact, and the flow loss caused by the guide vanes is avoided, thereby improving the turbo compound device 100.
  • the overall efficiency increases the utilization of engine exhaust energy and improves the fuel economy of the engine.
  • the boost turbine 1 is a radial turbine and the power turbine 2 is an axial turbine.
  • the blade 10 linear velocities U0 and U1 of the turbomachine 1 are vertically upward, and the blade 23 linear velocities U2 and U3 of the power turbine 2 are vertically downward.
  • the engine 3 exhaust enters the vane 10 of the supercharged turbine 1 at a relative speed W0 and flows out of the vane 10 of the supercharged turbine 1 at a relative speed W1.
  • the installation angle (angle with the axial direction) of the vane 10 at the outlet of the turbocharger 1 is designed to be larger (greater than 50°), so that the vane 10 exit
  • the airflow absolute speed C1 has a large angle with the axial direction and is biased to the same side as the direction of rotation of the power turbine 2. After passing through the cavity 22 formed by the body 20 and the outer wall 21, the airflow reaches the leading edge of the blade 23 of the power turbine 2 at an absolute speed C2.
  • the boost turbine 1 may also be a mixed flow turbine, and the power turbine 2 is an axial flow turbine.
  • the blade shape of the inlet of the blade 10 of the turbocharger 1 is at an angle to the axial direction, and the airflow is deflected at a larger angle in the mixed flow turbocharger 1 than the radial turbine, thereby increasing the gas pressure increase.
  • the amount of work of the turbine 1 distributes more energy into the turbocharger 1.
  • the angle of the airflow entering the supercharging turbine 1 is different, that is, as shown in FIG. 1, when the turbocharger 1 is a radial turbine, the exhaust gas discharged from the engine 3 enters into the vane 10 of the turbocharger 1 from the radial direction.
  • the supercharged turbine 1 When the supercharged turbine 1 is a mixed flow turbine, the exhaust gas discharged from the engine 3 enters into the vane 10 of the supercharged turbine 1 at a predetermined inclination angle, and the flow principle of the exhausted exhaust gas in the turbocompound device 100 and the turbocharger 1 are radial flow type.
  • the flow principle of the turbine is the same and will not be described in detail here.
  • the blade exit angle of the power turbine 2 is configured such that the outlet airflow of the power turbine 2 flows out at a speed close to the axial direction, thereby minimizing the loss of the exit kinetic energy.
  • An engine system 200 includes: an engine 3, a counter-rotating turbo The device 100, the compressor 4, the intercooler 5, and the fluid coupling device 6, wherein the counter-rotating turbo compound device 100 is the counter-rotating turbo compound device 100 according to the embodiment of the first aspect of the present invention, wherein the turbocharger 1 is installed Downstream of the exhaust manifold 31 of the engine 3 to receive the airflow exhausted by the engine 3, and the power turbine 2 is arranged downstream of the boost turbine 1.
  • the compressor 4 is connected to the booster turbine 1 and is driven by the booster turbine 1 to pressurize the airflow entering it.
  • the intercooler 5 is connected between the compressor 4 and the cylinder 32 of the engine 3 to cool and feed the supercharged airflow into the cylinder 32 of the engine 3.
  • the input shaft 60 of the fluid coupling 6 is coupled to the power turbine 2, and the output shaft 61 is coupled to the crankshaft 30 of the engine 3 to transfer the recovered work of the power turbine 2 to the crankshaft 30.
  • the engine 3 includes a crankshaft 30, an exhaust manifold 31, a cylinder 32, and an intake manifold 33 for inputting power to the engine 3, and an intake manifold 33 for use in the plurality of cylinders 32.
  • the air supply, the exhaust manifold 31 is used to exhaust the exhaust gas after the engine 3 is operated.
  • the exhaust gas enters the supercharger turbine 1 from the exhaust manifold 31, and pushes the turbocharger 1 to rotate.
  • the turbocharger 1 drives the compressor 4 to pressurize the airflow entering the compressor 4, after pressurization.
  • the air flow enters the intercooler 5, and the intercooler 5 cools the supercharged airflow, and the cooled airflow is sent to the cylinder 32 of the engine 3 through the intake manifold 33.
  • the exhaust gas enters from the turbocharger 1 into the power turbine 2 coupled to the turbocharger 1, and the power turbine 2 converts the energy of the exhaust gas into mechanical power output to the fluid coupling 6.
  • the fluid coupling 6 transfers the recovered work to the crankshaft 30 to power the engine 3.
  • the engine system 200 of the embodiment of the present invention by providing the counter-rotating turbo compound device 100, the engine system 200 is compact, fully utilizes exhaust gas energy, improves engine fuel economy, and reduces harmful gas emissions, improving the overall engine system 200. performance.
  • the engine system 200 further includes: a first transmission assembly 7 and a second transmission assembly 8, wherein the first transmission assembly 7 is coupled between the input shaft 60 of the hydrodynamic coupler 6 and the power turbine 2
  • the second transmission assembly 8 is coupled between the output shaft 61 of the fluid coupling 6 and the crankshaft 30.
  • first transmission component 7 and the second transmission component 8 are respectively a primary gear transmission assembly.
  • first transmission assembly 7 and the second transmission assembly 8 may also be secondary, tertiary or multi-stage gear transmission assemblies, such as planetary gear mechanisms.
  • the turbocharger 1 is coaxially connected with the compressor 4, and the turbocharger 1 drives the compressor 4 to pressurize the airflow entering the compressor 4, and the supercharged airflow passes through the intercooler. 5 After cooling, it enters the cylinder 32 of the engine 3, increasing the intake air density, and increasing the power of the cylinder 32 of the engine 3. At the same time, the exhaust gas after the operation of the engine 3 enters the blade 10 of the turbocharger 1, and then flows out of the turbocharger 1 in the axial direction, passes through the cavity 22 formed by the body 20 and the outer wall 21, and then enters the power turbine 2 in the axial direction. The power turbine 2 converts the energy of the exhaust gas into mechanical work.
  • the power turbine 2 is connected to the input shaft 60 of the fluid coupling 6 via the first transmission assembly 7, and the output shaft 61 of the fluid coupling 6 is passed through the second transmission assembly 8. It is connected to the crankshaft 30 of the engine 3, and finally transfers the recovered work of the power turbine 2 to the crankshaft 30, thereby improving the total power and fuel economy of the engine 3. At the same time, the flow loss is reduced and the turbo compound is improved due to the elimination of the conventional guide vanes.
  • the device 100 is efficient, thereby improving the overall performance of the engine system 200 while making the engine system 200 more compact.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

L'invention porte sur un appareil composite possédant des turbines contrarotatives (100), qui comprend une turbine de charge (1) et une turbine de puissance (2). La turbine de puissance (2) et la turbine de charge (1) sont accouplées et les axes de rotation de la turbine de puissance (2) et de la turbine de charge (1) sont les mêmes, mais le sens de rotation est inversé. L'angle d'entrée d'une aube de rotor de la turbine de puissance (2) est accordé à l'angle de sortie d'une aube de la turbine de charge (1), de telle sorte que le flux d'air provenant de la sortie de la turbine de charge (1) entre directement dans le rotor de la turbine de puissance (2) à un angle prédéterminé pour agir sur ce rotor. En outre, l'invention décrit aussi un système de moteur (200) comprenant l'appareil composite à turbines contrarotatives (100). Les aubes de guidage entre la turbine de charge (1) et la turbine de puissance (2) sont supprimées dans l'appareil composite à turbines contrarotatives (100), ce qui rend la structure plus dense et évite la perte de flux due aux aubes de guidage.
PCT/CN2013/071577 2012-02-13 2013-02-08 Appareil composite comprenant des turbines contrarotatives et système de moteur comprenant cet appareil WO2013120449A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN2012100318636A CN102536432A (zh) 2012-02-13 2012-02-13 对转涡轮复合装置及具有该装置的发动机系统
CN201210031863.6 2012-02-13

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WO2013120449A1 true WO2013120449A1 (fr) 2013-08-22

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CN (1) CN102536432A (fr)
WO (1) WO2013120449A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018109138A1 (de) * 2018-04-17 2019-10-17 Abb Turbo Systems Ag Turbolader mit integrierter Nutzturbine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102536432A (zh) * 2012-02-13 2012-07-04 清华大学 对转涡轮复合装置及具有该装置的发动机系统
CN104533620B (zh) * 2014-10-30 2016-06-08 西安交通大学 一种采用低燃值气体燃料的紧凑型燃气轮机装置
CN106948926A (zh) * 2017-05-11 2017-07-14 大连依勒斯涡轮增压技术有限公司 一种紧凑型两级涡轮机
CN109113792A (zh) * 2018-10-30 2019-01-01 常胜 复合加力涡轮
WO2021032210A1 (fr) * 2019-08-22 2021-02-25 上海必修福企业管理有限公司 Transducteur à double flux, son système de production d'énergie, et procédé de production d'énergie

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US5138840A (en) * 1988-04-08 1992-08-18 Kabushiki Kaisha Komatsu Seisakusho Power transmission apparatus for internal combustion engine including supercharger
JPH11257011A (ja) * 1998-03-16 1999-09-21 Ishikawajima Harima Heavy Ind Co Ltd タービンのノズル構造
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CN101915126A (zh) * 2010-06-04 2010-12-15 清华大学 串列叶型混流或径流涡轮
CN102536432A (zh) * 2012-02-13 2012-07-04 清华大学 对转涡轮复合装置及具有该装置的发动机系统

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US2552138A (en) * 1945-04-21 1951-05-08 Gen Electric Dual rotation turbine
US5138840A (en) * 1988-04-08 1992-08-18 Kabushiki Kaisha Komatsu Seisakusho Power transmission apparatus for internal combustion engine including supercharger
JPH11257011A (ja) * 1998-03-16 1999-09-21 Ishikawajima Harima Heavy Ind Co Ltd タービンのノズル構造
CN1791738A (zh) * 2003-05-15 2006-06-21 沃尔沃拉斯特瓦格纳公司 用于内燃机的涡轮压缩机系统
JP2006258108A (ja) * 2006-07-04 2006-09-28 Mitsubishi Heavy Ind Ltd 可変容量タービン及びこれを備えた可変容量ターボチャージャ
CN101915126A (zh) * 2010-06-04 2010-12-15 清华大学 串列叶型混流或径流涡轮
CN102536432A (zh) * 2012-02-13 2012-07-04 清华大学 对转涡轮复合装置及具有该装置的发动机系统

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Publication number Priority date Publication date Assignee Title
DE102018109138A1 (de) * 2018-04-17 2019-10-17 Abb Turbo Systems Ag Turbolader mit integrierter Nutzturbine

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