SU609484A3 - Internal combustion engine - Google Patents

Internal combustion engine

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Publication number
SU609484A3
SU609484A3 SU731945916A SU1945916A SU609484A3 SU 609484 A3 SU609484 A3 SU 609484A3 SU 731945916 A SU731945916 A SU 731945916A SU 1945916 A SU1945916 A SU 1945916A SU 609484 A3 SU609484 A3 SU 609484A3
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SU
USSR - Soviet Union
Prior art keywords
expansion
turbine
turbines
pressure compressor
internal combustion
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SU731945916A
Other languages
Russian (ru)
Inventor
Боцунг Ханнс-Гюнтер
Манн Альбрехт
Original Assignee
Машиненфабрик Аугсбург-Нюрнберг Аг (Фирма)
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Application filed by Машиненфабрик Аугсбург-Нюрнберг Аг (Фирма) filed Critical Машиненфабрик Аугсбург-Нюрнберг Аг (Фирма)
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Publication of SU609484A3 publication Critical patent/SU609484A3/en

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Classifications

    • 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
    • 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
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/013—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps 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
    • F02B67/00—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for
    • F02B67/10—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for of charging or scavenging apparatus
    • 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)

Description

(54) ДВИГАТЕЛЬ ВНУТРЕННЕГО СГОРАНИЯ(54) INTERNAL COMBUSTION ENGINE

1one

Изобретение относитс  к области машиностроени , в частности к двигател м внутреннего сгорани .The invention relates to the field of mechanical engineering, in particular to internal combustion engines.

Известны двигатели внутреннего сгорани ; содержащие остов и блок агрегатов наддува, снабженные установленными на общей горизонтальной оси компрессорами двух последователь ных стуненей сжати  и турбннами двух последовательных ступеней расширени , у которых компрессор низкого давлени  дополннтельно св зан при помощи механической передачи с коленчатым валом двигател  внутреннего сгорани  {I .Known engines of internal combustion; containing a skeleton and a unit of pressurization units equipped with compressors of two successive compression stages installed on a common horizontal axis and turbines of two successive expansion stages, in which a low pressure compressor is additionally connected by means of a mechanical transmission to the crankshaft of an internal combustion engine {I.

Наличие механнческой передачи усложн ет компоновку агрегатов наддува в блоке и компоновку блока агрегатов на остове.The presence of a mechanical transmission complicates the layout of the pressurized aggregates in the block and the layout of the aggregate block on the skeleton.

. Известны также двигатели внутреннего сгоранн , содержащие остов, блок агрегатов наддува , снабженный установленными на общей горизонтальной оси компрессорами двух последовательных ступеней сжати  и турбинами двух последовательных ступеней расширени , из которых компрессор высокого давлени  соединен с консольным колесом турбины первой ступени расширени , а к выпускному сечению последнего примыкает консольное колесо турбины второй ступени расширени , соединенное с компрессором низкого давлени , н воздухоохладитель , включенный в воздушный тракт между компрессорами 2.. Also known are internal burned engines containing a skeleton, a unit of boosting units equipped with two successive compression stages installed on a common horizontal axis and two successive expansion turbines with turbines, of which a high-pressure compressor is connected to the cantilever wheel of the first expansion turbine and adjoins a cantilevered turbine wheel of the second expansion stage, connected to a low pressure compressor, and an air cooler included in air path between compressors 2.

В известных двигател х механическа  передача отсутствует, но направление вращени  турбокомпрессоров не ограничено, поэтому между 5 рабочими колесами турбин предусмотрена возможность размещени  промежуточного направл ющего аппарата. В св йи с этим габариты блока агрегатов наддува достаточно велики.In the known engines, there is no mechanical transmission, but the direction of rotation of the turbochargers is not limited, therefore the possibility of placing an intermediate guide vane is provided between the 5 impellers of the turbines. In connection with this, the dimensions of the supercharging unit are large enough.

Целью изобретени   вл етс  уменьшение Q габаритов путем исключени  промежуточного направл ющего аппарата.The aim of the invention is to reduce the Q dimensions by eliminating an intermediate guide vane.

Это достигаетс  тем, что лопатки колес турбин двух последовательных ступеней расширени  ориентированы в противоположных направлени х.This is achieved in that the blades of the turbine wheels of two successive expansion stages are oriented in opposite directions.

5 Кроме того, блок агрегатов наддува расположён на .торце остова и его горизонтальна  ось перпендикул рна к продольной оси последнего .5 In addition, the unit of pressurization units is located on the end face of the core and its horizontal axis is perpendicular to the longitudinal axis of the latter.

На фиг. изображен двигатель, вид сверху; на фиг. 2 - блок агрегатов наддува в продольном разрезе; на фиг. 3 - компоновка блока агрегатов наддува на двигателе; на фиг. 4 - принципиальна  схема двигател  и системы его наДдува.FIG. depicts the engine, top view; in fig. 2 — block of pressurized aggregates in longitudinal section; in fig. 3 - layout of the unit of supercharging on the engine; in fig. 4 - a schematic diagram of the engine and its system nadduva.

Двигатель внутреннего сгорани  содержит остов 1 с цилиндрами 2, каждый из которыхThe internal combustion engine contains a core 1 with cylinders 2, each of which

снабжен впускным 3 и выпускным 4 каналами. в которых расположены соотпотстпепно linycKной 5 .и выпускной б клапаны.it is supplied with inlet 3 and final 4 channels. in which are located sootpotppepno linycKnoy 5. and exhaust b valves.

Блок агрегатов наддува включает в себ  два последовательно включенных турбокомирессора 7 и 8, расположенных соосно и обрашенных один к другому консольными колесами турбин . Турбина 9 первой ступени расширени  и компрессор 10 образуют ступень высокого давлени , а турбина 1 второй ступени расширени  и компрессор 2 - ступень низкого давлени .The block of pressurization units includes two successively connected turbo-compressors 7 and 8, which are located coaxially and cantilevered to one another by cantilever wheels of turbines. The turbine 9 of the first expansion stage and the compressor 10 form a high pressure stage, and the turbine 1 of the second expansion stage and the compressor 2 form a low pressure stage.

К турбине 9 первой ступени расчниреии  примыкает газоподвод щий трубопровод 13, канчивающийс  впускным патрубком 14 турбины . Кроме этого патрубка турбина первой ступени расширени  содержит улитку. 15 и конкольное рабочее колесо 16, размешенное на валу 17, который, установлен в подшипниках 18, закрепленных в корпусе (не показан). К выпускному сечению колеса турбинь 9 первой ступени расширени  примыкает консольное колесо 19 турбины II второй ступени расширени , установленное на валу 20. Лопатки 21 колеса турбины первой ступени расширени  ориентированы навстречу потоку выхлойных газов в противоположность лопаткам 22 колеса турбины второй ступени расширени . Колеса турбин обеих ступеней соединены проставкой 23.A first-stage gas turbine pipe 13 adjoins the turbine 9, which can be fed by the turbine inlet 14. In addition to this nozzle, the turbine of the first expansion stage contains a cochlea. 15 and a konkolny impeller 16 placed on the shaft 17, which is mounted in bearings 18 fixed in a housing (not shown). A first expansion stage turbine 9 adjoins a second stage expansion turbine wheel 19 mounted on a shaft 20. The first expansion stage turbine blades 21 are oriented towards the exhaust gas flow in contrast to the second stage expansion turbine blades. The wheels of the turbines of both stages are connected by a spacer 23.

Кроме колеса турбина второй ступени расширени  содержит газосбориик 24 и выпускной патрубок 25, соединенный трубопроводом 26 с глушителем (не показан). Компрессор 12 низкого давлени  содержит входной патрубок 27 дл  впуска воздуха, в котором расположен глушитель шума и воздушный фильтр, и рабочее колесо 28.In addition to the wheel, the turbine of the second expansion stage contains a gas receptacle 24 and an outlet 25, connected by a pipe 26 with a silencer (not shown). The low pressure compressor 12 comprises an inlet 27 for air intake, in which a noise silencer and an air filter are located, and an impeller 28.

Рабочее колесо 29 компрессора JO высокого давлени  открываетс  в воздушный тракт 30 между компрессорами, в который включен воздухоохладитель 31.The impeller 29 of the high-pressure compressor JO opens into the air path 30 between the compressors, into which the air cooler 31 is connected.

Другой воздухоохладитель 32 может быть размеш,еи за компрессором 10 высокого давлени  перед впускным трубопроводом. Блок агрегатов на.адувг расположен на торце 33 осто и его горизонтальна  ось перпендикул рна к продоль.ной оси последнего. Отработавшие газы, выход щие из цилиндра 2 при открьь том клапане 6 в выпускной канал 4, поступают по газоподвод ш.ему трубопроводу 13 к колесу 16 турбины 9 первой ступени расширени  и далее - к колесу 19 турбины П второй ступени pacmnpeHfrs. Затем выхлопные газы поступают S газосборник 24 и через выпускной патрубок 25 выход т в трубопровод 26, соединенный с глушителем.The other air cooler 32 may be placed behind the high-pressure compressor 10 in front of the intake manifold. The block of units on the flange is located at the end of 33 osto and its horizontal axis is perpendicular to the longitudinal axis of the latter. The exhaust gases leaving cylinder 2 when the valve 6 is opened into the exhaust channel 4 are supplied via gas supply w. To its pipeline 13 to the wheel 16 of the turbine 9 of the first expansion stage and then to the wheel 19 of the turbine II of the second stage pacmnpeHfrs. Then, the exhaust gases enter the S gas collector 24 and out through the outlet 25 and out into the pipe 26 connected to the silencer.

Воздух, всасываемый через патрубок 27 компрессора 12 низкого давлени , сжимаетс  в рабочем колесе 28 и подаетс  через воздушный тракт 30 с установленным в нем воздухоохладителем 31 в компрессор 10 высокого давлени . Рабочее колесо 29 компрессора 10 высокого давлени  нагнетает возду.ч через воздухоохладитель в цилиндры 2 двигател .The air drawn in through the low-pressure compressor nozzle 27 is compressed in the impeller 28 and supplied through the air path 30 with air cooler 31 installed in it to the high-pressure compressor 10. The impeller 29 of the high-pressure compressor 10 pumps air through the air cooler into the cylinders 2 of the engine.

Лопатки 21 и 22 колес 16 и 19 соответственно турбин периой и второй ступеней расширени  ориентированы в противоположных направлени х , т. е. колеса турбин обеих ступеней имеют противоположные направлени  вращени . В результате этого отпадает необходимость 3 установке промежуточного направл ющего аппарата.The blades 21 and 22 of the wheels 16 and 19, respectively, of the turbines of the first and second stages of expansion are oriented in opposite directions, i.e. the wheels of the turbines of both stages have opposite directions of rotation. As a result, there is no need for 3 installation of an intermediate guide vane.

Размешение блока агрегатов наддува на торце остова позвол ет разместить агрегаты наддува без существенного увеличени  ширины двигател .Placing the block of boost units at the end of the skeleton allows placing the boost units without a significant increase in engine width.

Кроме того, колеса турбин примыкают друг к другу, т. е. ступени давлени  .следуют одна за другой, что позвол ет избавитьс  от длинных трубопроводов.In addition, the turbine wheels are adjacent to each other, i.e., the pressure stages follow one after the other, which makes it possible to get rid of long pipelines.

Таким образом, такое выполнение двигател  обеспечивает уменьшение .его габаритов.Thus, such an engine provides a reduction in its dimensions.

Согласно описываемому изобретению блок агрегатов наддува может быть расположен и на торце остова V-образного двигател  (фиг. 1). Выпускное отверстие патрубка 14 турбины высокого давлени  размеш,ено иа оси между блоками цилиндров, что позвол ет разместить газоподвод щий трубопровод 3 в развале между блоками. Если разместить одинаковые агрегаты на двух торцах остова, можно к каждому торцу подвести вьтхлопной коллектор , объедин ющий цилиндры только одного блока, т. е. имеютс  дополнительные компоновочные преимущества.According to the described invention, a unit of pressurization units can also be located at the end of the core of a V-engine (Fig. 1). The outlet of the nozzle 14 of the high-pressure turbine is placed between the cylinder blocks, which allows the gas supply line 3 to be placed in the camber between the blocks. If you place the same units at the two ends of the skeleton, you can bring a flotation collector to each end that connects the cylinders of only one block, i.e., there are additional layout advantages.

Таким образом, описываемое техническое решение позвол ет уменьшить габариты двигател  в целом.Thus, the described technical solution allows to reduce the overall dimensions of the engine.

Claims (2)

1.Двигатгть внутреннего сгорани , содержащий остов, блок агрегатов наддува, снабженный установленными на общей горизонтальной оси компрессорами двух последовательных ступеней сжати  и турбинами двух последовательных ступеней расширени , из которых компрессор высокого Давлени  соединен с консольным колесом турбины первой ступени расширени , а к выпускному сечению последнего примыкает консольное колесо турбины второй ступени расширени , соединенное с компрессором низкого давлени , и воздухоохладитель, включенный в воздушный тракт между компрессорами , отличающийс  тем, что, с уменьшени  габаритов путем исключени  промежуточного направл ющего аппарата, лопатки, колес турбин двух последовате,пьных ступеней расширени  ориентированы в противоположныхн- правлени х .1. An internal combustion engine containing a skeleton, a unit of pressurization units equipped with two successive compression stages installed on a common horizontal axis and two successive expansion turbines with turbines, of which a high pressure compressor is connected to a cantilever wheel of a first expansion turbine turbine and adjoins a cantilevered turbine wheel of the second expansion stage, connected to a low pressure compressor, and an air cooler included in the air inlet kt between the compressors, characterized in that, with the decreasing size by eliminating intermediate guide apparatus, vane turbines two wheels Sequence, pnyh expansion stages oriented in protivopolozhnyhn- Regents of x. 2.Двигатель по п. I, отличающийс  тем, что блок агрегатов наддува расположен на торце остЬна и его горизонта-1ьна  ось перпендикул рна к продольной оси последнего.2. The engine according to claim I, characterized in that the block of the charge aggregates is located at the end of the axle and its horizon-1na on the axis perpendicular to the longitudinal axis of the latter. Источники информации, прин тьте во внимание при экспертизе:Sources of information, take into account in the examination: 1.Авторское свидетельство СССР № 382835, кл. F 02 В 39/02, 1971., .1. USSR author's certificate number 382835, cl. F 02 B 39/02, 1971.,. 2.Патент 3257797, кл, 60-13, 1966.2. Patent 3257797, class 60-13, 1966. Put.JPut.J .f.f
SU731945916A 1972-07-11 1973-07-11 Internal combustion engine SU609484A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2233970A DE2233970C2 (en) 1972-07-11 1972-07-11 TWO-STAGE CHARGED PISTON COMBUSTION MACHINES

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SU609484A3 true SU609484A3 (en) 1978-05-30

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JP (2) JPS4957218A (en)
CH (1) CH565941A5 (en)
DD (1) DD105651A1 (en)
DE (1) DE2233970C2 (en)
DK (1) DK139988C (en)
FR (1) FR2192603A5 (en)
GB (1) GB1438172A (en)
IT (1) IT989725B (en)
PL (1) PL85430B1 (en)
SE (1) SE402323B (en)
SU (1) SU609484A3 (en)
YU (1) YU35389B (en)

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DK139988B (en) 1979-05-28
GB1438172A (en) 1976-06-03
DD105651A1 (en) 1974-05-05
DE2233970C2 (en) 1975-03-13
JPS5847226Y2 (en) 1983-10-28
JPS4957218A (en) 1974-06-04
JPS53101108U (en) 1978-08-15
SE402323B (en) 1978-06-26
IT989725B (en) 1975-06-10
DE2233970B1 (en) 1973-11-22
DK139988C (en) 1979-10-29
YU152973A (en) 1980-06-30
YU35389B (en) 1980-12-31
PL85430B1 (en) 1976-04-30
FR2192603A5 (en) 1974-02-08
CH565941A5 (en) 1975-08-29

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