US2565907A - Apparatus for transfer of fluids - Google Patents
Apparatus for transfer of fluids Download PDFInfo
- Publication number
- US2565907A US2565907A US8627A US862748A US2565907A US 2565907 A US2565907 A US 2565907A US 8627 A US8627 A US 8627A US 862748 A US862748 A US 862748A US 2565907 A US2565907 A US 2565907A
- Authority
- US
- United States
- Prior art keywords
- chamber
- fluids
- pressure
- transfer
- inlet
- 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.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/42—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow characterised by the input flow of inducing fluid medium being radial or tangential to output flow
-
- 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
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M21/00—Apparatus for supplying engines with non-liquid fuels, e.g. gaseous fuels stored in liquid form
- F02M21/02—Apparatus for supplying engines with non-liquid fuels, e.g. gaseous fuels stored in liquid form for gaseous fuels
- F02M21/04—Gas-air mixing apparatus
- F02M21/045—Vortex mixer
-
- 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
- F02B43/00—Engines characterised by operating on gaseous fuels; Plants including such engines
-
- 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
-
- 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
- Y02T10/30—Use of alternative fuels, e.g. biofuels
Definitions
- This invention relates to an aerodynamic process for transferring fluids from a zone into another one wherein a higher presslu'e than in the first zone prevails.
- An apparatus adapted for carrying out this process may conveniently be used in any machine or plant wherein fluids are to be introduced into a chamber under a higher pressure, and it enables such an introduction to be efiected without having resort to any rotary or reciprocating mechanical device.
- Fig. 1 is a lengthwise section of said ejector.
- Fig. 2 is an elevation of the revolution chamber.
- Fig. 3 is a diagram illustrating how the pressure of the primary fluid employed as a prime mover for transfervaries, the specific volumes being plotted as abscissae, while pressures are plotted as ordinates.
- Fig. 4 is a similar diagram showing how the pressure of the secondary fluid to be transferred varies.
- Such primary air is discharged through an annular passage or outlet B after it has developed a strong swirling field in chamber K.
- a considerably lower pressure prevails than in passage B.
- a gas flow is thus set up from axial inlet C to annular passage B, and it proceeds as far as the pressure prevailing in the chamber (not shown) located upstream with respect to opening C and containing a fluid to be transferred to another chamber (not shown) located downstream with respect to passage B where a lighter pressure prevails, has dropped enough to assume a characteristic level which depends on the ratios between aperture radii:
- the pressure variation in the primary fluid flow from A to B is illustrated by the diagram of Fig. 3, while the pressure variation in the secondary or induced gas flow from C to B is shown on the diagram of Fig. 4.
- An apparatus for inducing a stream of secondary fluid by a stream of primary fluid which comprises a hollow body containing a chamber which has approximately a shape of revolution, means providing an axial inlet for conveying axially into said chamber a stream of secondary fluid, means providing, opposite to said inlet, an annular outlet for a mixture of primary and sec and a *4 ondary fluids, said outlet being coaxial with said REFERENCES CITED Inlet and havmg Inner and outer dlameters
- the following references are of record in the larger than that of said inlet, and a plurality of me of this patent:
- tangential inwardly convergent nozzle for directin said stream of primary fluid into said 5 UNITED STATES PATENTS chamber, said nozzles being rigid with said body Number Name Date and distributed around the periphery of said 334,597 Marsh Jan. 19, 1886 chamber to define a ring coaxial with the inlet TENT and outlet 'of said'chamber and of larger diam- .4 qg, PA S eter than the outer diameter of said'annular lO "country Date t t 5 794,512 France Feb. 19, 1936 JEAN H. BERTIN. RAYMONDJ-I. MARCHAL.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Oil, Petroleum & Natural Gas (AREA)
- Jet Pumps And Other Pumps (AREA)
Description
-28 1951" J. H. BERTIN Em 6 APPARATUs FOR TRANSFER OF FLUIDS Filed Feb. 16, 1948 INVEN TOR, gwm+mumw Patented Aug. 28, 1951 APPARATUS FOR TRANSFER OF FLUIDS Jean H. Bertin and Raymond H. Marchal, Paris, France, assignors to Societe Nationale dEtude et de Construction de Moteurs dAviation, Paris, France, a, company of France Application February 16, 1948, Serial No. 8,627 In France September 5, 1946 Section 1, Public Law 690, August 8, 1946 Patent expires September 5, 1966 1 Claim.
This invention relates to an aerodynamic process for transferring fluids from a zone into another one wherein a higher presslu'e than in the first zone prevails.
According to this invention, for effecting such a transfer, use is made of the pressure distribution which is produced as a function of radius, by swirling axipetal flow of a primary fluid within a cylindrical chamber.
An apparatus adapted for carrying out this process may conveniently be used in any machine or plant wherein fluids are to be introduced into a chamber under a higher pressure, and it enables such an introduction to be efiected without having resort to any rotary or reciprocating mechanical device.
It is possible in particular, although this example is not restrictive, to employ the process according to one invention for completing exhaust from internal combustion engine cylinders into an exhaust manifold where a pressure higher than inlet pressure prevails; which is particularly desirable where an exhaust gas turbine is provided since further expansion of gas is permissible.
Further advantages and features of our invention will become apparent from the following description thereof with reference to the appended drawing which shows diagrammatically and solely by way of example, form of construction of an aerodynamic ejector according to our invention.
Fig. 1 is a lengthwise section of said ejector.
Fig. 2 is an elevation of the revolution chamber.
Fig. 3 is a diagram illustrating how the pressure of the primary fluid employed as a prime mover for transfervaries, the specific volumes being plotted as abscissae, while pressures are plotted as ordinates.
Fig. 4 is a similar diagram showing how the pressure of the secondary fluid to be transferred varies.
Primary air is let into the periphery A of a cylindrical chamber K through apertures 01 preceded by tangential nozzles T which taper into said chamber, converting the pressure of primary fluid into velocity.
Such primary air is discharged through an annular passage or outlet B after it has developed a strong swirling field in chamber K. Next to the axis of said chamber, a considerably lower pressure prevails than in passage B. A gas flow is thus set up from axial inlet C to annular passage B, and it proceeds as far as the pressure prevailing in the chamber (not shown) located upstream with respect to opening C and containing a fluid to be transferred to another chamber (not shown) located downstream with respect to passage B where a lighter pressure prevails, has dropped enough to assume a characteristic level which depends on the ratios between aperture radii:
and on the rate of flow of primary air.
The pressure variation in the primary fluid flow from A to B is illustrated by the diagram of Fig. 3, while the pressure variation in the secondary or induced gas flow from C to B is shown on the diagram of Fig. 4.
We have thus actually provided a compressor borrowing energy from expansion to which primary fluid is subjected. Its efiiciency is in some cases lower than that of a conventional mechanical compressor, but it meets a number of essential objects, particularly:
1. It comprises no moving mechanical member so that it is long lasting and quite simple in its construction.
2. It is very light.
3. It always operates under optimum conditions even where it is applied with flows varying at very high frequencies, having regard to the very small inertia of gas therein.
It should further be understood that our invention is not restricted to the form of construction above described, and many modifications relying on the same principle may be provided without departing from the scope of this invention.
What we claim is:
An apparatus for inducing a stream of secondary fluid by a stream of primary fluid, which comprises a hollow body containing a chamber which has approximately a shape of revolution, means providing an axial inlet for conveying axially into said chamber a stream of secondary fluid, means providing, opposite to said inlet, an annular outlet for a mixture of primary and sec and a *4 ondary fluids, said outlet being coaxial with said REFERENCES CITED Inlet and havmg Inner and outer dlameters The following references are of record in the larger than that of said inlet, and a plurality of me of this patent:
tangential inwardly convergent nozzle for directin said stream of primary fluid into said 5 UNITED STATES PATENTS chamber, said nozzles being rigid with said body Number Name Date and distributed around the periphery of said 334,597 Marsh Jan. 19, 1886 chamber to define a ring coaxial with the inlet TENT and outlet 'of said'chamber and of larger diam- .4 qg, PA S eter than the outer diameter of said'annular lO "country Date t t 5 794,512 France Feb. 19, 1936 JEAN H. BERTIN. RAYMONDJ-I. MARCHAL.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2565907X | 1946-09-05 |
Publications (1)
Publication Number | Publication Date |
---|---|
US2565907A true US2565907A (en) | 1951-08-28 |
Family
ID=9686576
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US8627A Expired - Lifetime US2565907A (en) | 1946-09-05 | 1948-02-16 | Apparatus for transfer of fluids |
Country Status (1)
Country | Link |
---|---|
US (1) | US2565907A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3046732A (en) * | 1956-06-20 | 1962-07-31 | Research Corp | Method of energy exchange and apparatus for carrying out the same |
US3063223A (en) * | 1958-11-12 | 1962-11-13 | Arbisi Dominic | Vacuum device |
US3796046A (en) * | 1970-05-02 | 1974-03-12 | Kuehnle Kopp Kausch Ag | Process for detoxicating exhaust gases from otto-combustion engines and apparatus for carrying out such process |
US4070131A (en) * | 1975-01-20 | 1978-01-24 | Grumman Aerospace Corporation | Tornado-type wind turbine |
US4245961A (en) * | 1978-09-08 | 1981-01-20 | Martin Marietta Corporation | Ejector utilizing a vortex flow |
US4388045A (en) * | 1976-01-30 | 1983-06-14 | Martin Marietta Corporation | Apparatus and method for mixing and pumping fluids |
US20130283785A1 (en) * | 2012-04-28 | 2013-10-31 | Timothy E. Coulter | Coulter Compressor an exhaust removal driven compressor |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US334597A (en) * | 1886-01-19 | Steam-jet pump | ||
FR794512A (en) * | 1934-08-31 | 1936-02-19 | Device for extracting exhaust gases from two-stroke internal combustion engines |
-
1948
- 1948-02-16 US US8627A patent/US2565907A/en not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US334597A (en) * | 1886-01-19 | Steam-jet pump | ||
FR794512A (en) * | 1934-08-31 | 1936-02-19 | Device for extracting exhaust gases from two-stroke internal combustion engines |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3046732A (en) * | 1956-06-20 | 1962-07-31 | Research Corp | Method of energy exchange and apparatus for carrying out the same |
US3063223A (en) * | 1958-11-12 | 1962-11-13 | Arbisi Dominic | Vacuum device |
US3796046A (en) * | 1970-05-02 | 1974-03-12 | Kuehnle Kopp Kausch Ag | Process for detoxicating exhaust gases from otto-combustion engines and apparatus for carrying out such process |
US4070131A (en) * | 1975-01-20 | 1978-01-24 | Grumman Aerospace Corporation | Tornado-type wind turbine |
US4388045A (en) * | 1976-01-30 | 1983-06-14 | Martin Marietta Corporation | Apparatus and method for mixing and pumping fluids |
US4245961A (en) * | 1978-09-08 | 1981-01-20 | Martin Marietta Corporation | Ejector utilizing a vortex flow |
US20130283785A1 (en) * | 2012-04-28 | 2013-10-31 | Timothy E. Coulter | Coulter Compressor an exhaust removal driven compressor |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2404334A (en) | Aircraft propulsion system and power unit | |
US3643431A (en) | Flow control devices | |
GB622181A (en) | Improvements relating to gas-turbine-engines | |
GB1427146A (en) | Combustion apparatus for gas turbine engines | |
US2912821A (en) | Valveless inlet for pulse jet | |
JPH09500439A (en) | Air injection type fuel injection valve mounted in radial direction | |
US2565907A (en) | Apparatus for transfer of fluids | |
US3483699A (en) | Fuel injector for a gas turbine engine | |
US2632299A (en) | Precombustion chamber | |
GB1127651A (en) | Flameholder assembly for a jet propulsion engine afterburner | |
US2114285A (en) | Diffuser for centrifugal compressors | |
GB809300A (en) | Improvements relating to combustion chambers for combustion turbines, jet propulsionengines and the like | |
US11536456B2 (en) | Fuel and air injection handling system for a combustor of a rotating detonation engine | |
US2667033A (en) | Combustion apparatus for operation in fast-moving air streams | |
US3379011A (en) | Energy exchange device and separator | |
GB751098A (en) | Improvements in combustion devices particularly applicable to aircraft jet propulsion units | |
US2079923A (en) | Thermal power plant | |
US2540526A (en) | Internal-combustion turbine power plant | |
GB918778A (en) | Improvements in or relating to gas-turbine engines | |
US2752753A (en) | Air swirler surrounding fuel nozzle discharge end | |
GB1435820A (en) | Gas turbine combustion apparatus liner | |
US3774398A (en) | Gas generator | |
GB1118569A (en) | Mechanical energy exchange between two fluid media | |
US2830439A (en) | Combustion equipment for gas turbines with hot gas extraction and mixing means | |
GB887829A (en) | Improvements relating to flame tubes for combustion systems |