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Publication numberUS2647365 A
Publication typeGrant
Publication dateAug 4, 1953
Filing dateFeb 19, 1946
Priority dateFeb 19, 1946
Publication numberUS 2647365 A, US 2647365A, US-A-2647365, US2647365 A, US2647365A
InventorsMyers Elman B
Original AssigneeMyers Elman B
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Reso-jet motor
US 2647365 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

Aug. 4, 1953 E. B. MYERS RESO-JET MOTOR Fi1ed`Feb- 19. 194e lll/l ril Il l l/ fr!!! Il Xl f l l r r r l l lill/l IIJ l l 1rd/ fr lr l l A irri/frbt ELMAN. s. MYERSv Patented Aug. 4, 1953 UNITED STATES PTlll-*ITf 'l OFFICE v l .2,647,365'7* j Raso-JET Mo'iolt Elman B..Myers,'Pompton`Blailns, i' vv lApplication February 19, 1946,*seria1N`o. 648.790 f 4 Claims.

'This .invention relates to a new'and improved cyclically operating jet or reaction motor.

An object of this invention is to provide a jet or reaction motor that has an increased eiiiciency and thrust.

A further objective of this invention is to provide a cyclically operating jet or reaction motor that has an increased pressure on the compression or positive phase of the cycle and increased vacuum on the suction or negative phase of the 1 cycle inlet passage 3 and a conventional fuel inlet 4 as shown. Carried by the mixing chamber 2 is a combustion tube 5 having a conventional electric ignition means 6, such as high voltage spark plugs or the like, located adjacent the exhaust end of the said tube 5. The number of plugs and distance from the end of the tube 5 may be varied for each specific motor, but it is recommended that a plurality of plugs be used and that they be located approximately four inches from the exhaust or the open end of said tube.

In the intake portion of the exhaust tube 5, and preferably at the junction of the tube 5 and the mixing chamber 2, as shown, is a constriction 'l in the form of a sharp edged venturi, welded into or cast integral with the inner walls of the combustion tube 5. The said constriction 1 is in the form of a Venturi with a shoulder 8, provided at the throlat 9 of the venturi, as shown, facing into or toward the mixing chamber 2. The said constriction outwardly diverges away from the shoulder into a bell l0 opening down stream of the tube 5. Precise dimensions of the constriction 1, such as the ratio of the mouth and the throat and the length of the constriction to the length of the combustion tube etc., are omitted from this specification because they will vary with each different design of motor.

In operation, air is introduced into the mixing chamber during the negative or low pressure cycle of the motor. Fuel is injected into the chamber 2, continuously through the inlet 4.

The mixed -air-,fuel then enters the combustion tube 5 through constriction T. Initially the charge is fired by the spark plugs 6, then after motor is firing in resonance, the spark plugs are disconnected and subsequent ignition of the motor follows from the flash back of each preceding explosion. The mixed fuel-air burns backward from the spark or exhaust end of the combustion tube 5, building up pressure progressively until it reaches the constriction 'l where the wave front then reverses its direction and moves forward again through the tube toward the exhaust end, creating a low pressure area in the mixing chamber thus completing the combustion cycle.

It is to be understood that the form of this invention, herewith shown and described, is to be taken yas a preferred example of the same, and

that various changes in the shape. size and arrangement of parts may be resorted to, without departing from the spirit of this invention, or the scope of the subjoined claims.

What I claim is:

1. In a cyclically operating reaction motor having a fuel-air mixing chamber, an axially aligned air inlet means communicating with said chamber at one end, and having a peripheral shoulder normal thereto and facing said chamber, fuel inlet means in said chamber, and a combustion tube axially coextensive with said chamber and having intake and exhaust ends, the said intake end being in open communication with the said mixing chamber at its other end; ignition means in said combustion tube adjacent the exhaust end of said tube, and a sleeve forming a constriction in said combustion tube adjacent the said intake end, the inside of said sleeve being in the form of a venturi having a sharp edge with a shoulder normal to said venturi at its throat facing the said mixing chamber.

2. A reso-jet engine comprising an air inlet, a fuel-air mixing chamber connected thereto, la fuel nozzle in said chamber, a combustion tube open at both ends and axially aligned with said chamber, ignition means in said combustion tube, said combustion tube having a Venturi throat at its inner end adjacent said chamber with a normal peripheral shoulder forming a sharp inner edge at the chamber end of the throat, whereby a resonating pressure wave is produced in said combustion tube between the ignition mean-s and said Venturi throat.

3. A reso-jet engine comprising an air inlet, a fuel-air mixing dhamber connected thereto, a fuel nozzle in said chamber, a combustion tube open at both ends and axially aligned with said chamber, ignition means at one end of said combustion tube, said tube having a restricted passage- Way at the chamber end, said passageway characterized by having a sharply edged normal peripheral face toward said chamber and a bellshaped face opening toward the other end of said combustion tube, whereby a. resonating pressure Wave is producedinsaid` combustiomtube between the end. having. the ignition means'and the rias"- sageway.

4. In a reso-jet motor having means defining.

ing chamber, said restriction device including' a' narrow throat having walls tapering outwardly to the walls or said tailfplpe, said throat further characterized by having the end thereof facing said mixing chamber cut off squarely to form an inner peripheral shoulder in said mixing chamber with a sharp internal edge, and ignition means in said tail pipe rearwardly of said restriction device whereby the wave fronts of explosions of fuel-air mixtures initiated by said ignition means are reflected by the tapering walls of said-.tailpipa ELMAN B; MYERS.

References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 1,369,672 Koenig Feb. 22, 1921 1,852164 Holzwarth Apr. 5, 1932 FOREIGN PATENTS Number Country Date 11,526 GreatBritam'- June 13; 1894

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1369672 *Jun 17, 1919Feb 22, 1921Koenig JosephPropelling device
US1852164 *Jan 28, 1929Apr 5, 1932Holzwarth Gas Turbine CoPressure damping mechanism
GB189411526A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4173122 *Feb 9, 1978Nov 6, 1979The United States Of America As Represented By The Secretary Of The Air ForceIntermittent burning jet engine
US4472132 *May 19, 1982Sep 18, 1984Tokyo Shibaura Denki Kabushiki KaishaPulse combustor
US4671056 *Aug 6, 1986Jun 9, 1987Genz Matthew L RPulse-sonic jet nozzle
US6375454Nov 12, 1999Apr 23, 2002Sarcos, L.C.Controllable combustion device
US6876094Feb 28, 2002Apr 5, 2005Sarcos, LcResonant electrical generation system
US6938588Apr 23, 2002Sep 6, 2005Sarcos Investments, LcControllable combustion method and device
US6983586 *Dec 8, 2003Jan 10, 2006General Electric CompanyTwo-stage pulse detonation system
EP0066203A2 *May 19, 1982Dec 8, 1982Kabushiki Kaisha ToshibaPulse combustor
EP0256711A2 *Jul 29, 1987Feb 24, 1988Matthew Lewis Reginald GenzPulse jet combustor
U.S. Classification60/767, 60/39.77
International ClassificationF02K7/00, F02K7/04
Cooperative ClassificationF02K7/04
European ClassificationF02K7/04