US1493157A - Propelling ejector - Google Patents

Propelling ejector Download PDF

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US1493157A
US1493157A US679785A US67978523A US1493157A US 1493157 A US1493157 A US 1493157A US 679785 A US679785 A US 679785A US 67978523 A US67978523 A US 67978523A US 1493157 A US1493157 A US 1493157A
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ejector
tubes
propelling
tube
following
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US679785A
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Melot Henri Fabrice
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/12—Injection-induction jet engines

Definitions

  • This invention relates to a propelling device of the hind described in Letters-Patent l@ of the United States No. 1,375,601 in which a motive tluid sent. through a plurality of ejector tubes in series draws atmospheric air and causes between the front and rear ends of the ejector tubesv a difference of pressure producing a thrust on the tubes, so that when the latter are mounted on a terrestrial vehicle, a marine vessel or an aircraft. the thrust causes propulsion thereof.
  • the first4 ejector tubes of the series areof greater length than the following ejector tubes so as to provide a suliicient distance way for the high speed mixture of motive liuidand a-,ir aspired to have proper timel to expand yand carry along the maximum Aamount of air.
  • the injection nozzle a receives ,motive Huid from any generatingvdevice such for as example that described in my application Serial No. 679,784, filed even date.' Said device is designated on the drawing by the letter A and is not claimed herein.
  • Each following ejector tube 19,112 - is of lesser length 49 than the preceding tube or of equal length.-
  • the air drawnig'in at c mixes with the 'motive' Huid injected through the nozzle a. and the mixture whosekinitial speed -is vry high is abley to apply itself against the in-f7 ner walls Vof the ejector tubel b and has time to expand ,properly owing to the great length of said tube.
  • the Huid reaches the second ejector tube I
  • its speed is slower and it is not necessary to have it 5 follow such a great axial distance as in the first tube -for it to have the requisite expansion and produce the maximum reaction on the surroundingatmospheric air.
  • rlhe same edeet occurs with the following ejector tubes.
  • a needle d having asuitableprofile is placed inside the ejector tubes and the nozzle it required, so as give them the proper passage areas.
  • Said needle may be made movable in vthe axiai direction so as to permit of regulating the areas.
  • the invention may also be applied to ejector tubes in series supplying gas tur-v bines or securing the blast of metallurgical apparatus.
  • i 4.v A propelling device with ejector tubes in series the first tubes having a greater length than the following, each tube having al convergent part and a divergent part, the corresponding parts of all the. tubes being parallel, and each tube having a stream- '.clined surface.

Description

May 6 1924. 1,493,157
H. F. MELOT l PROPELLIG EJEcToR Filed Dec. 1o'. 192:5
Patented Mey 6, 1924.
PROPELLING 'EJECTO Application led December 10, 1923. Serial No. 679,785.
T all whom z't may concern:
Be it lxnownV that l., HENRI FABRICE Miino'r, a citizen of the Republic of France, residing at Paris, France, 43 Avenue du Maine, have invented certain new anduseful improvements in Propelling `Ejeetors, of which the following is a specification.
This invention relates to a propelling device of the hind described in Letters-Patent l@ of the United States No. 1,375,601 in which a motive tluid sent. through a plurality of ejector tubes in series draws atmospheric air and causes between the front and rear ends of the ejector tubesv a difference of pressure producing a thrust on the tubes, so that when the latter are mounted on a terrestrial vehicle, a marine vessel or an aircraft. the thrust causes propulsion thereof. ln accordance with the present invention, in
order to improve the efiiciency of such devices, the first4 ejector tubes of the series areof greater length than the following ejector tubes so as to provide a suliicient distance way for the high speed mixture of motive liuidand a-,ir aspired to have proper timel to expand yand carry along the maximum Aamount of air.
The accompanying drawing shows diagrainmatically an axial section of an embodiment of the invention. l
The injection nozzle a receives ,motive Huid from any generatingvdevice such for as example that described in my application Serial No. 679,784, filed even date.' Said device is designated on the drawing by the letter A and is not claimed herein. Nozzle @opens into the first ejector tube b which is -open to the atmosphere at c. Each following ejector tube 19,112 -is of lesser length 49 than the preceding tube or of equal length.-
The air drawnig'in at c mixes with the 'motive' Huid injected through the nozzle a. and the mixture whosekinitial speed -is vry high is abley to apply itself against the in-f7 ner walls Vof the ejector tubel b and has time to expand ,properly owing to the great length of said tube. When the Huid reaches the second ejector tube I), its speed is slower and it is not necessary to have it 5 follow such a great axial distance as in the first tube -for it to have the requisite expansion and produce the maximum reaction on the surroundingatmospheric air. rlhe same edeet occurs with the following ejector tubes.
lt may happen that the passage areas in the last ejector tubes becomes too great with respect to their length. in such case, according to the invention, a needle d having asuitableprofile is placed inside the ejector tubes and the nozzle it required, so as give them the proper passage areas. Said needle may be made movable in vthe axiai direction so as to permit of regulating the areas. i
The invention may also be applied to ejector tubes in series supplying gas tur-v bines or securing the blast of metallurgical apparatus.
What l claimvis:
l.v A propelling device with ejector-tubes in overlapping series wherein the first tubes have a greater length than t-he following tubes and each tube has its outlet arranged at therestricted portion of the following tube, whereby sufficient distance of passage is provided for the expansion of the mixture of motive tiuid and air aspired.
2. A propelling device with ejector tubes in series wherein the first tubes are of greater length than the following tubes, and having a needle in the opening of said tubes for providing the proper free passage areas.
3. A propelling device with ejector tubes in series 'the irst tubes having a greater length than the following. each tube having a convergent part and a divergent part, the corresponding parts of all thetubes being parallel. i 4.v A propelling device with ejector tubes in series the first tubes having a greater length than the following, each tube having al convergent part and a divergent part, the corresponding parts of all the. tubes being parallel, and each tube having a stream- '.clined surface.
ln testimony whereofl have signed my name to this specification. j
HENRI FABRICE MLOT.
Venturi
US679785A 1923-12-10 1923-12-10 Propelling ejector Expired - Lifetime US1493157A (en)

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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2475022A (en) * 1942-06-09 1949-07-05 Tresham D Gregg Fluid reaction propulsive device
US2479776A (en) * 1944-04-15 1949-08-23 Lockheed Aircraft Corp Turbo-jet power plant with fuel vaporizer for afterburners
US2487588A (en) * 1943-05-22 1949-11-08 Lockheed Aircraft Corp Variable area propulsive nozzle means for power plants
US2563745A (en) * 1942-03-06 1951-08-07 Lockheed Aircraft Corp Variable area nozzle for power plants
US2587073A (en) * 1949-08-24 1952-02-26 Robert H Swartz Compound reciprocating-pulse jet aircraft power plant
US2633699A (en) * 1945-05-21 1953-04-07 Daniel And Florence Guggenheim Propulsion apparatus actuated by successive charges of detonating materials
US2651171A (en) * 1945-05-21 1953-09-08 Daniel And Florence Guggenheim Propulsion apparatus actuated by successive charges of detonating materials
US3049873A (en) * 1958-02-04 1962-08-21 Westinghouse Electric Corp Exhaust nozzle having a flow area of variable convergency and divergency
US3051148A (en) * 1955-05-31 1962-08-28 Douglas K Warner Two cycle-radial, high-supercharge engines
US3187501A (en) * 1960-12-19 1965-06-08 Thomas E Quick Method of and apparatus for augmenting thrust and suppressing sound in aircraft, rockets, and the like
US3401885A (en) * 1966-03-22 1968-09-17 Bertin & Cie Jet deflector
US3447324A (en) * 1967-10-18 1969-06-03 Howard V French Water jet propulsion means
US3938742A (en) * 1973-02-13 1976-02-17 The United States Of America As Represented By The United States National Aeronautics And Space Administration Office Of General Counsel-Code Gp Cascade plug nozzle
WO2006001927A2 (en) * 2004-05-17 2006-01-05 Marius Paul A Carnot cycle jet and rocket engine configurations
US20090217643A1 (en) * 2008-02-29 2009-09-03 Sokhey Jagdish S Gas discharge device for a vehicle engine

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2563745A (en) * 1942-03-06 1951-08-07 Lockheed Aircraft Corp Variable area nozzle for power plants
US2475022A (en) * 1942-06-09 1949-07-05 Tresham D Gregg Fluid reaction propulsive device
US2487588A (en) * 1943-05-22 1949-11-08 Lockheed Aircraft Corp Variable area propulsive nozzle means for power plants
US2479776A (en) * 1944-04-15 1949-08-23 Lockheed Aircraft Corp Turbo-jet power plant with fuel vaporizer for afterburners
US2633699A (en) * 1945-05-21 1953-04-07 Daniel And Florence Guggenheim Propulsion apparatus actuated by successive charges of detonating materials
US2651171A (en) * 1945-05-21 1953-09-08 Daniel And Florence Guggenheim Propulsion apparatus actuated by successive charges of detonating materials
US2587073A (en) * 1949-08-24 1952-02-26 Robert H Swartz Compound reciprocating-pulse jet aircraft power plant
US3051148A (en) * 1955-05-31 1962-08-28 Douglas K Warner Two cycle-radial, high-supercharge engines
US3049873A (en) * 1958-02-04 1962-08-21 Westinghouse Electric Corp Exhaust nozzle having a flow area of variable convergency and divergency
US3187501A (en) * 1960-12-19 1965-06-08 Thomas E Quick Method of and apparatus for augmenting thrust and suppressing sound in aircraft, rockets, and the like
US3401885A (en) * 1966-03-22 1968-09-17 Bertin & Cie Jet deflector
US3447324A (en) * 1967-10-18 1969-06-03 Howard V French Water jet propulsion means
US3938742A (en) * 1973-02-13 1976-02-17 The United States Of America As Represented By The United States National Aeronautics And Space Administration Office Of General Counsel-Code Gp Cascade plug nozzle
WO2006001927A2 (en) * 2004-05-17 2006-01-05 Marius Paul A Carnot cycle jet and rocket engine configurations
WO2006001927A3 (en) * 2004-05-17 2006-07-20 Marius A Paul Carnot cycle jet and rocket engine configurations
US20090217643A1 (en) * 2008-02-29 2009-09-03 Sokhey Jagdish S Gas discharge device for a vehicle engine

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