US1906132A - Turbo blower aggregate for internal combustion engines - Google Patents

Turbo blower aggregate for internal combustion engines Download PDF

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US1906132A
US1906132A US590483A US59048332A US1906132A US 1906132 A US1906132 A US 1906132A US 590483 A US590483 A US 590483A US 59048332 A US59048332 A US 59048332A US 1906132 A US1906132 A US 1906132A
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Prior art keywords
turbine
blower
inlet
aggregate
combustion engines
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US590483A
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Buchi Alfred
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    • 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
    • F02B37/02—Gas passages between engine outlet and pump drive, e.g. reservoirs
    • 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
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F02B39/005—Cooling of pump drives
    • 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 turboblower aggregates for internal-combustion engines and particularly to those actuated by the exhaust gases of the internal combustion engines.
  • the turboblower aggregate is of such design that the charge sucked in is not heated by the turbine part. Furthermore means are provided to prevent a heat flow either by convection or by conduction to the blower part of the exhaust turbo-aggregate. Furthermore by this invention neat piping arrangements between the exhaust turbo-aggregate and the internal combustion engine are provided.
  • the design of the air intake part may be such, that the suction noise of the blower part is effectively silenced, as hereinafter described.
  • the turbine may be of any design known in the art.
  • the preferred form shown in the embodiment of the invention is a turbine with a radial inlet for the exhaust gases and in which the inlet is provided on that part of the turbine which is nearer to the blower.
  • the outlet of the exhaust gases is remote from the blower part and preferably axial.
  • Fig. 1 is a vertical section through the axis of the exhaust turbo-aggregate.
  • Fig. 2 is a front view of the turbo-aggregate in the same position as in Fig. 1.
  • Fig. 3 is atop view of Fig. 2.
  • Fig. 4 is a section through the turbine inlet on the line 1-1 of Fig. 1 with the turbine rotor omitted.
  • Fig. 4a is a detail of partition between turbine Fig. 4 and shows the chambers 24 and Fig. 5 is a top view.
  • Fig. 6 is a section through the turbine inlet similar to line 1-1 in Fig. 1 but in a turbine with three turbine inlets.
  • Fig. 7 represents a horizontal section through the air intake of Fig. 1.
  • Fig. 8 shows two turbine rotors.
  • Fi s. 9 and 10 show the turbo-blower aggreg a te fitted to a six-cylinder internal-combustion engine.
  • Numeral 1 designates the blower part and 2 the turbine part of an exhaust turbo-blower.
  • 3 is the air inlet, l-indicates the blower wheels, and 23 the shaft.
  • Numeral 6 refers to a bearing of the thrust bearing type.
  • the rotor 7 of the turbine On the same shaft is mounted the rotor 7 of the turbine. 8 is the inlet and 9 the outlet of the gases. The inlet is radial and the outlet axial.
  • guide vanes 10 are provided in openings 11, to properly convey the exhaust gases to the rotor 7.
  • the air inlet 3 is situated towards the blower part and in order to avoid heating cooling medium jackets 12 and 13 are provided for whereby the cooling medium (which can be air, oil, water, etc.) is supplied by pipe 14 and carried away by pipe 15.
  • the cooling medium which can be air, oil, water, etc.
  • Jacket 17 may be empty or filled with a cooling medium, to cool t e exhaust gases leaving the turbine.
  • a bearing, preferably a journal bearing 16 supports the shaft 23 between the turbine rotor 7 and blower wheels 4.
  • the space 21 between blower part 1 and turbine part 2 may be of such design as to silence and effectively dampen the intake noise.
  • Blower part 1 and turbine part 2 may be integral with each other or may be connected to eachother by means of studs 27, bolts or the like or the intake silencer 18 may connect the two parts.
  • the intake silencer may be provided with baflles 18a. The compressed charge leaves the compressor through the pressure conduits 5 and 19 wherev as the exhaust gases are led to the turbine in conduits 20.
  • baflies 18 can bearings 28 or they may be made movable, so
  • bafiles may be vathat the free area between ried by a handle 22 and rod 22a, whereby part of the bafiles may be open or nearly open and part of them closed or nearly closed.
  • the annular space 24 may be one chamber, or may be subdivided into several chambers, for instance by means of plates 25 and bolts 26 (Fig. 4a). To each of the chambers lead one or more exhaust conduits 20. As shown in Fig. 6 plate 25 may be removed, so that spaces 24b and 240 act as one space and to which space two exhaust conduits 8 lead. The exhaust gases may pass through one or more turbine stages and the shaft may carry more than one turbine wheel 7, as shown in Fig. 8.
  • a turbo blower for internal-combus- 5 tion engines in combination an exhaust-gas turbine, a rotary blower, means to connect said turbine to said blower, an air inlet to said blower, said air inlet being between said turbine and said blower, a silencer for the blower inlet, said silencer being arranged in the space between said turbine and said blower, an outlet from said blower at one end of the turbo aggregate, inlet connections to said turbine, a separate inlet chamber for each inlet connection, said turbine inlets being towards the blower inlet, jackets between the turbine inlet and the blower inlet, means to supply a cooling medium to said jackets, and a common turbine outlet at the other end of the turbine aggregate.
  • a turbo blower for internal-combustion engines in combination an exhaust-gas turbine, a rotary blower, means to connect said turbine to said blower, an air inlet to said blower, said air inlet being located between said turbine and said blower, a silencer for the blower inlet, said silencer being arranged in the space between said turbine and said blower, an outlet from said blower at 1 one end of the turbo aggregate, inlet connections to said turbine, a separate inlet chamber for each inlet connection, said turbine inlet being towards the blower inlet, ackets between the turbine inlet and the blower inlet,
  • a turbo blower for internal-combustion engines in combination an exhaust-gas turbine, a rotary blower, means to connect said turbine to said blower, an air inlet to said blower, said air inlet being between said turbine and said blower, a silencer for the blower inlet, said silencer being arranged in the space between said turbine and said blower, an outlet from said blower at one end of the turbo aggregate, inlet connections to said turbine, a separate inlet chamber for each inlet connection, said turbine inlets being towards.
  • blower inlet jackets between the turbine inlet and the blower inlet, means to supply "a cooling medium to said jackets, one common turbine outlet at the other end of the turbine aggregate, said turbine inlets and said blower outlets being arranged radially, and said common turbine outlet being arranged axially.

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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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Description

A. BUCHI 1,906,132
TURBO BLOWER AGGREGATE FOR INTERNAL COMBUSTION ENGINES April 25, 1933.
Filed Feb. 2, 1932 III Patented Apr. 25, 1933 UNITED STATES PATENT OFFICE ALFRED BUCHI, OF WINTERTHUR, SWITZERLAND rumso Application ma February 2, 1932, Serial No.
The present invention relates to turboblower aggregates for internal-combustion engines and particularly to those actuated by the exhaust gases of the internal combustion engines.
According to this invention the turboblower aggregate is of such design that the charge sucked in is not heated by the turbine part. Furthermore means are provided to prevent a heat flow either by convection or by conduction to the blower part of the exhaust turbo-aggregate. Furthermore by this invention neat piping arrangements between the exhaust turbo-aggregate and the internal combustion engine are provided. The design of the air intake part may be such, that the suction noise of the blower part is effectively silenced, as hereinafter described.
The turbine may be of any design known in the art. The preferred form shown in the embodiment of the invention is a turbine with a radial inlet for the exhaust gases and in which the inlet is provided on that part of the turbine which is nearer to the blower.
The outlet of the exhaust gases is remote from the blower part and preferably axial.
In the accompanying drawing a preferred embodiment of the invention is shown.
In the drawing:
Fig. 1 is a vertical section through the axis of the exhaust turbo-aggregate.
Fig. 2 is a front view of the turbo-aggregate in the same position as in Fig. 1.
Fig. 3 is atop view of Fig. 2.
Fig. 4 is a section through the turbine inlet on the line 1-1 of Fig. 1 with the turbine rotor omitted.
Fig. 4a is a detail of partition between turbine Fig. 4 and shows the chambers 24 and Fig. 5 is a top view.
Fig. 6 is a section through the turbine inlet similar to line 1-1 in Fig. 1 but in a turbine with three turbine inlets.
Fig. 7 represents a horizontal section through the air intake of Fig. 1.
Fig. 8 shows two turbine rotors.
Fi s. 9 and 10 show the turbo-blower aggreg a te fitted to a six-cylinder internal-combustion engine.
BLOWER AGGREGATE FOR INTERNAL COMBUSTION ENGINES 590,483, and in Switzerland February 5, 1981.
Numeral 1 designates the blower part and 2 the turbine part of an exhaust turbo-blower. 3 is the air inlet, l-indicates the blower wheels, and 23 the shaft. Numeral 6 refers to a bearing of the thrust bearing type. On the same shaft is mounted the rotor 7 of the turbine. 8 is the inlet and 9 the outlet of the gases. The inlet is radial and the outlet axial. In the turbine part 2 guide vanes 10 are provided in openings 11, to properly convey the exhaust gases to the rotor 7. The air inlet 3 is situated towards the blower part and in order to avoid heating cooling medium jackets 12 and 13 are provided for whereby the cooling medium (which can be air, oil, water, etc.) is supplied by pipe 14 and carried away by pipe 15. Jacket 17 may be empty or filled with a cooling medium, to cool t e exhaust gases leaving the turbine. A bearing, preferably a journal bearing 16 supports the shaft 23 between the turbine rotor 7 and blower wheels 4. The space 21 between blower part 1 and turbine part 2 may be of such design as to silence and effectively dampen the intake noise. Blower part 1 and turbine part 2 may be integral with each other or may be connected to eachother by means of studs 27, bolts or the like or the intake silencer 18 may connect the two parts. The intake silencer may be provided with baflles 18a. The compressed charge leaves the compressor through the pressure conduits 5 and 19 wherev as the exhaust gases are led to the turbine in conduits 20.
be rigidly held in their The baflies 18 can bearings 28 or they may be made movable, so
them may be vathat the free area between ried by a handle 22 and rod 22a, whereby part of the bafiles may be open or nearly open and part of them closed or nearly closed.
The annular space 24 may be one chamber, or may be subdivided into several chambers, for instance by means of plates 25 and bolts 26 (Fig. 4a). To each of the chambers lead one or more exhaust conduits 20. As shown in Fig. 6 plate 25 may be removed, so that spaces 24b and 240 act as one space and to which space two exhaust conduits 8 lead. The exhaust gases may pass through one or more turbine stages and the shaft may carry more than one turbine wheel 7, as shown in Fig. 8.
' I claim:
1. In a turbo blower for internal-combus- 5 tion engines in combination an exhaust-gas turbine, a rotary blower, means to connect said turbine to said blower, an air inlet to said blower, said air inlet being between said turbine and said blower, a silencer for the blower inlet, said silencer being arranged in the space between said turbine and said blower, an outlet from said blower at one end of the turbo aggregate, inlet connections to said turbine, a separate inlet chamber for each inlet connection, said turbine inlets being towards the blower inlet, jackets between the turbine inlet and the blower inlet, means to supply a cooling medium to said jackets, and a common turbine outlet at the other end of the turbine aggregate.
2. In a turbo blower for internal-combustion engines in combination an exhaust-gas turbine, a rotary blower, means to connect said turbine to said blower, an air inlet to said blower, said air inlet being located between said turbine and said blower, a silencer for the blower inlet, said silencer being arranged in the space between said turbine and said blower, an outlet from said blower at 1 one end of the turbo aggregate, inlet connections to said turbine, a separate inlet chamber for each inlet connection, said turbine inlet being towards the blower inlet, ackets between the turbine inlet and the blower inlet,
means to supply a cooling medium to said jackets, one common turbine outlet at the other end of the turbine aggregate, said turbine inlets and said blower outlets being arranged radially.
1 3. A turbo blower for internal-combustion engines in combination an exhaust-gas turbine, a rotary blower, means to connect said turbine to said blower, an air inlet to said blower, said air inlet being between said turbine and said blower, a silencer for the blower inlet, said silencer being arranged in the space between said turbine and said blower, an outlet from said blower at one end of the turbo aggregate, inlet connections to said turbine, a separate inlet chamber for each inlet connection, said turbine inlets being towards. the blower inlet, jackets between the turbine inlet and the blower inlet, means to supply "a cooling medium to said jackets, one common turbine outlet at the other end of the turbine aggregate, said turbine inlets and said blower outlets being arranged radially, and said common turbine outlet being arranged axially.
In testimony whereof I have signed my name to this specification.
ALFRED BUCHI.
US590483A 1931-02-05 1932-02-02 Turbo blower aggregate for internal combustion engines Expired - Lifetime US1906132A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE975375C (en) * 1941-07-30 1961-11-16 Margarete Leist Exhaust turbine system for internal combustion engines

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE975375C (en) * 1941-07-30 1961-11-16 Margarete Leist Exhaust turbine system for internal combustion engines

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