WO1980000594A1 - Compresseur a gaz sans huile - Google Patents

Compresseur a gaz sans huile Download PDF

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Publication number
WO1980000594A1
WO1980000594A1 PCT/US1979/000690 US7900690W WO8000594A1 WO 1980000594 A1 WO1980000594 A1 WO 1980000594A1 US 7900690 W US7900690 W US 7900690W WO 8000594 A1 WO8000594 A1 WO 8000594A1
Authority
WO
WIPO (PCT)
Prior art keywords
engine
air
supplying
exhaust
aircraft
Prior art date
Application number
PCT/US1979/000690
Other languages
English (en)
Inventor
I Orian
Original Assignee
Ormat Systems Inc
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 Ormat Systems Inc filed Critical Ormat Systems Inc
Publication of WO1980000594A1 publication Critical patent/WO1980000594A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • 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
    • F02B37/007—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel, e.g. at least one pump supplying alternatively
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5826—Cooling at least part of the working fluid in a heat exchanger
    • 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
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/08—Other arrangements or adaptations of exhaust conduits
    • F01N13/10—Other arrangements or adaptations of exhaust conduits of exhaust manifolds
    • F01N13/107—More than one exhaust manifold or exhaust collector
    • 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

  • a substantially liquid-free admixture which upon the addition of a liquid medium and foaming forms a stable foam suitable for dyeing, finishing or printing textile materials, said mixture including up to about 10 percent of a foaming system and having a ratio of active solids to that of said foaming system of at least 8:1, said foaming agent being a part of said foaming system which further includes a foam stabilizer and/or thickener therein.
  • a further object of the present invention concerns jet starting auxiliary equipment.
  • the following systems are, inter alia, bequired: a. power supply for the electric system of the aircraft; b. an air supply for ventilation of the aircraft; c. injection of compressed air into the engine for start.
  • the compressed air injector is a separate unit requiring its own engine and compressor. Such an arrangement is wasteful and it is thus a further object of the present invention to provide auxiliary equipment for the injection of compressed air into an aircraft jet engine for start, which can be coupled with either of the power supply and ventilation installation.
  • a gas compressor assembly comprising in combination:
  • a volumetric internal combustion engine having means for dividing the exhast gases into at least two parallel streams, and further having a corresponding number of exhaust gas delivery means; and (b) a multi-stage compressor unit the number of whose stages corresponds to the number of said exhaust gas delivery means with each stage being linked to one of said exhaust gas delivery means, each stage comprising a gas turbine as prime mover adapted for actuation by exhaust gases from said engine, and a turbocompressor coupled thereto.
  • a compressor assembly the turbocompressors are operated by the exhaust gases of the volumetric internal combustion engine and in consequence no engine oil can pass into the turbocompressors and the compressor gas delivered by the latter is oil-free.
  • the compressor assembly according to the invention may be used for the compression of air and the delivered oil-free compressed air is suitable for cooling electronic equipment, for use in various sensitive chemical and food industries and also for the starting of a jet engine.
  • a unit according to the invention is used for the starting of a jet engine the volumetric internal combustion engine thereof, having two or more exhaust gas delivery means as specified, will at the same time also serve for powering either or both of the power supply and ventilation installations.
  • an auxiliary, gas operated turbocompressor unit it is possible to link an auxiliary, gas operated turbocompressor unit to an existing power supply and/or ventilation installation.
  • the invention thus also provides for use in a gas compressor assembly as specified, a multi-stage compressor unit each of whose stages is adapted to be linked to exhaust delivery means of an internal combustion engine and each comprising a gas turbine as prime mover and a turbocompressor coupled thereto.
  • a multi-stage compressor unit each of whose stages is adapted to be linked to exhaust delivery means of an internal combustion engine and each comprising a gas turbine as prime mover and a turbocompressor coupled thereto.
  • the term "volumetric internal combustion engine” used herein denotes any sort of internal combustion engine in which a piston is displaced by internal combustion engines, diesel type internal combustion engines as well as rotary, Wankel type internal combustion engines.
  • the compression ratio of each compression stage in an assembly according to the invention is at least 2:1.
  • the overall compression ratio rises exponentially with the number of stages. For example, where a compressor unit in an assembly according to the invention comprises two stages each having a compression ratio of 2:1, the overall compression ratio will be 4:1, where the number of 2:1 compression stages is 3, the overall ratio will be 8:1, etc. It is thus easily understood that in accordance with the invention, the overall design compression ratio can be selected at will by selection of the design compression ratio of each stage and the provision of a desired number of stages.
  • cooling arrangements may be provided between stages. However, there may be cases where cooling is not desired.
  • the gas e.g. air
  • the desired sterilization is then simply achieved by allowing the air to heat up through all compression stages. Where the compression in each stage is 2:1 the gas is heated in each stage by about 100 degrees Centigrade so that in a unit comprising two such stages without interstage cooling, the compressed gas is delivered at a temperature of about 200 degrees Centigrade which is sufficient for sterilization.
  • turbocompressor having a gas turbine as prime mover by a means of exhaust gases from an associated internal combustion engine
  • superchargers in which the compressed air delivered by the turbocompressor is injected into the engine.
  • Schwitzer Turboconveyors trade mark
  • the exhaust gases from a diesel engine are used to actuate a gas turbine driven turbocompressor and the compressed air delivered by the latter is used for conveying, e.g. for discharging a liquid or free-flowing bulk material from a container tank.
  • none of these known devices comprises an arrangement by which the exhaust gases from the combyustion engine are separated into two or more parallel flows and a corresponding number of turbocompressor stages is provided, each being actuated by one of said exhaust streams.
  • the present invention for the first time provides a compact assembly of the kind specified comprising two or more compression stages and a corresponding number of parallel exhaust streams from the engine, each actuating one of said stages.
  • Fig. 1 is a diagrammatic illustration of one embodiment of the invention
  • Fig. 2 is a diagrammatic illustration of a similar embodiment as in Fig 1 comprising in addition a super-charger for the engine;
  • Fig. 3 is a diagrammatic illustration of yet another embodiment, again similar to that of Fig. 1, comprising a multi-stage turbo-supercharger.
  • Fig. 1 comprises a four-cylinder internal combustion engine 1 having two exhaust gas collectors 2' and 2" each linked to two out of the four cylinders of engine 1.
  • Two gas turbines 3' and 3" are linked to the associated exhaust gas collectors through pipes 4', 4" respectively.
  • Gas turbine 3' is coupled to and serves as prime mover for a turbocompressor 5' and likewise turbine 3" is coupled to and serves as prime mover for a second turbocompressor 5".
  • Compressors 5' , 5" are connected in series with interposition of a cooler 6 and couplings 7' and 7".
  • the compressors 3', 3" and turbines 5', 5" are parts of a two-stage compressor unit 3", 5" constituting the first and 3' , 5' the second compression stage.
  • Air intake is through pipe 8 fitted with a filter unit 9 and compressed air delivery is through pipe 10.
  • the expanded exhaust gases from gas turbine 3' are discharged through exhaust pipe 11' fitted with a silencer 12' and likewise the expanded exhaust gases from gas turbine 3" and discharged through exhaust pipe 11" fitted with a silencer 12".
  • the combustion engine 1 comprises an air intake arrangement 13 and manifold 14 for the delivery of air into each of the engine cylinders.
  • the engine further comprises a shaft 15 which, if desired, may be coupled to a driven unit.
  • a driven unit For example, where the arrangement according to Fig. 1 is used as jet starting auxiliary equipment for the injection of compressed air into the jet engine of an aircraft during start, engine 1 may be common to this equipment and to an electric power supply; and/or ventilation equipment and in such a case shaft 15 will be coupled to a generator and/or a fan.
  • Fig. 2 The embodiment of Fig. 2 is essentially similar to that of Fig. 1 and similar parts are indicated by the same numeral. It comprises in addition a supercharging arrangement for engine 1 comprising a supercharger 16 coupled with the shaft 15 of engine 1 through a clutch 17 and fitted with an air intake 18 and an air delivery pipe 19 connected to the air intake manifold 14.
  • Air is sucked in through filter 9 and pipe 8 and is subjected to a first stage compression stage in the sub-unit 3", 5".
  • the compressed air from this sub-unit is delivered through the cooler 6 into the second sub-unit 3', 5' where it is subjected to the second stage compression.
  • the so-compressed air is delivered through auxiliary pipes 10.
  • the expanded exhaust gases from the two stages are discharged through exhaust pipes 11', 11" and the silencers 12' and 12", respectively.
  • Fig. 3 The installation of Fig. 3 is again basically similar to that of Fig. 1 and again similar components are designated by the same numerals.
  • this installation comprises a multi-stage turbo-supercharger arrangement comprising a first gas turbine 21' located between exhaust pipe 4' and gas turbine 3' and linked to the latter through a pipe 22'; and a second auxiliary gas turbine 21" located between exhaust pipe 4" and gas turbine 3" and linked to the latter through a pipe 22".
  • auxiliary turbines 21' and 21" Associated with the auxiliary turbines 21' and 21" are turbocompressors 23' and 23" respectively, fitted respectively with air intakes 24' and 24" and linked to manifold 14 of engine 1 through, respectively, delivery pipes 25' and 25".
  • auxiliary gas turbines 21' and 21" In operation the compressed exhaust gases form engine 1 are first injected into auxiliary gas turbines 21' and 21" where they are partly expanded and the so partly expanded exhaust gases are then delivered into gas turbines 3' and 3" whereupon the operation is as before.
  • the auxiliary turbine 21' and 21'' operate the turbocompressor 23' and 23 which deliver compressed air through pipes 25' and 25'' into manifold 14 from where it is injected into the various cylinders of the combustion engine 1. It is thus seen that each of units 21' , 23' and 21'' , 23'' acts as supercharger the two superchargers being connected in parallel to engine 1 which is tantamount to one single compression stage.
  • Fig. 3 operates as those of Figs. 1 and 2.

Landscapes

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

Abstract

Un compresseur a gaz sans huile utilise une paire d'appareils compresseurs entraines par les gaz d'echappement d'un moteur a combustion interne Un moteur a combustion interne a quatre cylindres (1) possede une paire de tubes d'echappement (4' et 4''), chacun d'eux etant connecte a deux cylindres differents du moteur (1). Les gaz dans les tubes (4' et 4'') sont appliques sur des turbines a gaz respectives (3' et 3'') qui sont accouplees individuellement a une paire de compresseurs connectes en serie (5' et 5'') pourvus d'un refroidisseur interetage (6). L'air comprime resultant peut etre utilise pour le service au sol d'un avion a reaction pour l'approvisionnement en air d'aeration ou pour la mise en marche des moteurs.
PCT/US1979/000690 1978-09-06 1979-09-06 Compresseur a gaz sans huile WO1980000594A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IL7855520A IL55520A0 (fr) 1978-09-06 1978-09-06
IL55520 1978-09-06

Publications (1)

Publication Number Publication Date
WO1980000594A1 true WO1980000594A1 (fr) 1980-04-03

Family

ID=11050549

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1979/000690 WO1980000594A1 (fr) 1978-09-06 1979-09-06 Compresseur a gaz sans huile

Country Status (3)

Country Link
EP (1) EP0016834A4 (fr)
IL (1) IL55520A0 (fr)
WO (1) WO1980000594A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2375006A (en) * 1942-07-13 1945-05-01 Gen Electric Supercharged combustion engine arrangement
US2484851A (en) * 1944-11-02 1949-10-18 Joy Mfg Co Pressure controlling apparatus
US3016227A (en) * 1959-03-16 1962-01-09 Gen Electric Removable fluid impingement starter nozzle construction for turbo-engine
US3204859A (en) * 1964-01-06 1965-09-07 Cooper Bessemer Corp Gas compressor system
US3232042A (en) * 1963-03-25 1966-02-01 Daytona Marine Engine Corp Engine turbocharging systems
US4169354A (en) * 1976-12-27 1979-10-02 Cummins Engine Company, Inc. Exhaust gas and turbine compressor system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1261335A (en) * 1969-04-16 1972-01-26 Tzadok Zakon Improvement in supercharged two stroke diesel engines
SE350800B (fr) * 1971-04-23 1972-11-06 Goetaverken Ab
DE2429976A1 (de) * 1974-06-21 1976-01-02 Tamrock Maschinenbau Gmbh Kompressor
US4008572A (en) * 1975-02-25 1977-02-22 Cummins Engine Company, Inc. Turbine housing

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2375006A (en) * 1942-07-13 1945-05-01 Gen Electric Supercharged combustion engine arrangement
US2484851A (en) * 1944-11-02 1949-10-18 Joy Mfg Co Pressure controlling apparatus
US3016227A (en) * 1959-03-16 1962-01-09 Gen Electric Removable fluid impingement starter nozzle construction for turbo-engine
US3232042A (en) * 1963-03-25 1966-02-01 Daytona Marine Engine Corp Engine turbocharging systems
US3204859A (en) * 1964-01-06 1965-09-07 Cooper Bessemer Corp Gas compressor system
US4169354A (en) * 1976-12-27 1979-10-02 Cummins Engine Company, Inc. Exhaust gas and turbine compressor system

Also Published As

Publication number Publication date
EP0016834A4 (fr) 1981-02-24
EP0016834A1 (fr) 1980-10-15
IL55520A0 (fr) 1978-12-17

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