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Publication numberUS2508396 A
Publication typeGrant
Publication dateMay 23, 1950
Filing dateAug 2, 1945
Priority dateAug 2, 1945
Publication numberUS 2508396 A, US 2508396A, US-A-2508396, US2508396 A, US2508396A
InventorsJordan Henry R
Original AssigneeJordan Henry R
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Rotary air intake valve for reso-jet motors
US 2508396 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

May 23, 1950 H. R. JORDAN 2,503,396

ROTARY AIR INTAKE VALVE FOR RESO-JET MOTORS Filed Aug. 2, 1945 *1 N g a m if Q i m R: h

Patented May 23, 1950 ROTARY AIR INTAKE VALVE-Fox BESO-JET MOTORS Henry RQJordan, United States Navy. I l I Application August 2,1345, Serial najsqajss r I v onnn. (o1. Gil-35.6)

(Granted under the act of March 188 amended April 30, 1928; 370 0.

This invention relates to an improvement in valves for *reso-jet motors or let motors that operate in resonance-or cyclically.

An object of this invention is to provide a rotary air intake valve for a reso-jet motor that is positively phased with the cyclical operation of the motor.

Another object of this invention is to provide a valve for a reso-jet motor that reduces failure, due to burning, to amlnimum.

A further object of this invention is to provide a rotary air intake valve for a reso-jet motor that will give an increased efficiency to the motor.

At the present time reso-jet motors, such as operate in resonance or cyclically, have a reed or resilient valve that opens to admit air into the combustion chamber when a low pressure area is created within the explosion chamber, due to the mass movement of gases out the tail pipe and close when the pressure within the chamber builds up during the explosion. This type of motor has frequently been referred to as the V-l or buzz bomb. Valves of the resilient or reed type used in these motors heretofore have been found to burn out after relatively short periods of operation. In some instances the valves being burned, after only a few minutes of operation, to such a degree that the efficiency of the motor would fall off as much as 50 per cent. The valve embodied in this invention eliminates this difficulty to such an extent as to make burning of the valves negligible. A careful examination of a valve, embodied in this invention in use on a resojet motor after almost a hundred hours of operation, showed no indication of burning whatsoever.

Other objects and advantages of thi invention will become apparent as the specification proceeds and is considered in connection with the accompanying claim and drawing wherein like characters designate like parts throughout, and wherein:

Fig. 1 is a cross sectional view of a conventional reso -jet motor with the conventional reed or resilient valve replaced by the rotary valve em" bodied in this invention;

Fig. 2 is an end plan View of the explosion chamber of a conventional reso-jet motor showing the rotary valve embodied in this invention affixed thereto; and

Fig. 3 is an end plan view of a. modification of the rotary valve embodied in this invention.

Referring now to the drawing, wherein for the purpose of illustration, is shown a. preferred embodiment of this invention, the numeral 5 designates a tail pipe or'resonant exhaust tube of the conventional reso jet, motor and the numeral 6 designates a'. combustion chamber in communication with the said ex aust.tube. A spark lu or other electrical charge firingfldclice 1 is ,PIQ- vided in the combustion: chamber. as shown. An end plate 8 is provided overfthe"end.,of the said combustion chamber- 6,oppositetheiexhaust tube 5. Communicating with thecombustiori chamber 6 and rigidly affixed; thereto,- in. any suitable means or cast integral therewithfis an air intake manifold 9. A fuel intake manifold l0 having spray nozzles or jets it-lisrqvided in the front end of the said nipple, as show'rnadmits fuel into the said explosion chamber.

Bearings l2, of the highspeed type, such as high speed roller or carbon bearings, are affixed to the nipple 9 as shown and rotatably carry ashaft l3 having a pulley I4 or other suitable driving mechanism affixed to one thereof. Asynchronous electric motor MA drives the pulley M at a predetermined positive rate. Carried by. and rotating with the shaft 13 within the nipple 9 is an S shaped butterfly valve l5. The circumferential configuration of the said-valve may be round, square, or rectangular depending on the shape of the air intake manifold. (In the illustration shown by Fig. 1 the valve rotate counterclockwise.) A trombone or sliding sleeve l6 provided on the end of the exhaust tube 5, as shown, permits varying of the frequency at which the exhaust tube 5 resonates, by increasing or decreasing the length of the said exhaust tube 5.

In operation, the reso-jet motor operating with the rotary valve embodied by this invention, fires synchronously as does the conventional reed or resilient type valve or motor. Fuel and air are mixed and burned in the combustion chamber, forward thrust of the motor is created by this burning and the escaping gases escaping through the exhaust tube create a low pressure area as the gas mass moves within the tail pipe to scav- 4 enge the explosion chamber. The exhaust tube is constructed so that the gases in motion within the said tube are caused to resonate ata certain fixed frequency. The returning wave front, during the oscillation of the said gas mass, builds up the pressure in the combustion chamber for the next succeeding explosion.

The rotating valve I5 is phased to rotate as nearly at the same frequency as the gas mass is resonating in the exhaust tube, and consequently rotating at the same frequency at which the explosion chamber is firing, as is possible.

It has been found by experimentation that it is extremely difiicult to phase this valve during assembly in exact resonance with the exhaust tube and so to bring the two, the valve and the ex haust tube, into a more perfect resonance, a slid-- ing tail pipe or trombone I6 is provided on the end of the exhaust tube 5. By sliding the trombone in or out (that is "to sayilay leng'thening or shortening the exhaust tube or tail pipe) the 1 for rotating said valve at a constant speed apfrequency of the exhaust tube can be varied to I j bring the said tube into phase with the rotating valve l5. The valve is phased to be :in 1a ing the scavenge and intake portion of "thlicyiiib. 1 I

It is to be understood thatirheromor myjin vention, herewith shown and described, is .to b'e proximating the speed of resonance of said motor, whereby the wave reaction in said combustion chamber will effectively assist in the rotation of said valve thereby reducing the required power in the rotating means, and an axially adjustable telescoping sleeve on the end of said tail ipipe.for accurately adjusting the length therestantially closed position during the compression and firing of the gas and air and to be open durtaken as a preferred example of the 'sama and i that various changes in the shape,r-sim :and arrangement of parts may beresortefl to, without departing from the spirit of my invention, or the scope of the subjoinedclaim.

"The invention described "herein maybe manufacturedand used by 'orf'fortire Government of thereon or therefor.

What'I claim'is: I Areso-jet motor comprising an "inlet, a combustion chamber anil-a' tail pipe-arranged in norof tothe speed of said constant speed rotating means for optimum eificiency.

HENRY R. JORDAN.

REFERENCES CITED The following references are of record in the me of this patent:

UNITED STATES PATENTS Number Name Date 2,102,559 Kadenaoy Dec. 14, 1937 FOREIGNPAI'ENTS Country .Date 625,420 GreatZBritain Aug. 28, 1940 412,478 France May 3, 1910 844,442 France. Apr. 24, 1939

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2102559 *Aug 1, 1934Dec 14, 1937Kadenacy MichelExplosion or internal combustion engine
FR412478A * Title not available
FR844442A * Title not available
GB525420A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2683961 *May 27, 1949Jul 20, 1954Phillips Petroleum CoVariable frequency pulse jet engine
US2712387 *Oct 19, 1950Jul 5, 1955Frank W YoungRotary filter with pulsating blowback means
US2715390 *Jul 18, 1950Aug 16, 1955TenneyResonant intermittent combustion heater and system
US2761283 *Jul 23, 1951Sep 4, 1956Houle Robert EResonant type jet propulsion engines
US2806350 *Aug 2, 1951Sep 17, 1957Hoffmann George RAir flow control for jet propelled craft
US2888803 *Aug 30, 1954Jun 2, 1959Pon LemuelIntermittent combustion turbine engine
US2924071 *Feb 23, 1955Feb 9, 1960 de paravicini
US2984304 *Nov 24, 1954May 16, 1961Ranson Charles WHelicopter lifting rotor having a propulsion unit at the blade tip
US2990848 *Jul 19, 1955Jul 4, 1961Norgren Co C AFluid pressure differential control
US3188804 *Oct 19, 1962Jun 15, 1965Melenric John AldenTurbo supercharged valveless pulse jet engine
US4397103 *Jul 27, 1981Aug 9, 1983American Artos CorporationTextile fabric dryer with rotary damper arrangement
Classifications
U.S. Classification60/247, 60/39.77, 137/624.13, 251/305
International ClassificationF02K7/00, F02K7/06
Cooperative ClassificationF02K7/06
European ClassificationF02K7/06