US2508396A - Rotary air intake valve for reso-jet motors - Google Patents

Rotary air intake valve for reso-jet motors Download PDF

Info

Publication number
US2508396A
US2508396A US60855445A US2508396A US 2508396 A US2508396 A US 2508396A US 60855445 A US60855445 A US 60855445A US 2508396 A US2508396 A US 2508396A
Authority
US
United States
Prior art keywords
reso
valve
air intake
jet
motor
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
Application number
Inventor
Henry R Jordan
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to US60855445 priority Critical patent/US2508396A/en
Application granted granted Critical
Publication of US2508396A publication Critical patent/US2508396A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • F02K7/02—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 the jet being intermittent, i.e. pulse-jet
    • F02K7/06—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 the jet being intermittent, i.e. pulse-jet with combustion chambers having valves
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/8593—Systems
    • Y10T137/86389—Programmer or timer
    • Y10T137/86405—Repeating cycle

Definitions

  • 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.
  • 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.
  • valve embodied in this invention eliminates this difficulty to such an extent as to make burning of the valves negligible.
  • 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;
  • Fig. 3 is an end plan view of a. modification of the rotary valve embodied in 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.
  • 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.
  • 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.
  • a slid-- ing tail pipe or trombone I6 is provided on the end of the exhaust tube 5.
  • 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
  • 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.

Description

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
US60855445 1945-08-02 1945-08-02 Rotary air intake valve for reso-jet motors Expired - Lifetime US2508396A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US60855445 US2508396A (en) 1945-08-02 1945-08-02 Rotary air intake valve for reso-jet motors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US60855445 US2508396A (en) 1945-08-02 1945-08-02 Rotary air intake valve for reso-jet motors

Publications (1)

Publication Number Publication Date
US2508396A true US2508396A (en) 1950-05-23

Family

ID=24437012

Family Applications (1)

Application Number Title Priority Date Filing Date
US60855445 Expired - Lifetime US2508396A (en) 1945-08-02 1945-08-02 Rotary air intake valve for reso-jet motors

Country Status (1)

Country Link
US (1) US2508396A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2683961A (en) * 1949-05-27 1954-07-20 Phillips Petroleum Co Variable frequency pulse jet engine
US2712387A (en) * 1950-10-19 1955-07-05 Frank W Young Rotary filter with pulsating blowback means
US2715390A (en) * 1950-07-18 1955-08-16 Tenney Resonant intermittent combustion heater and system
US2761283A (en) * 1951-07-23 1956-09-04 Robert E Houle Resonant type jet propulsion engines
US2806350A (en) * 1951-08-02 1957-09-17 George R Hoffmann Air flow control for jet propelled craft
US2888803A (en) * 1954-08-30 1959-06-02 Pon Lemuel Intermittent combustion turbine engine
US2924071A (en) * 1960-02-09 de paravicini
US2984304A (en) * 1954-11-24 1961-05-16 Charles W Ranson Helicopter lifting rotor having a propulsion unit at the blade tip
US2990848A (en) * 1955-07-19 1961-07-04 Norgren Co C A Fluid pressure differential control
US3188804A (en) * 1962-10-19 1965-06-15 Melenric John Alden Turbo supercharged valveless pulse jet engine
US4397103A (en) * 1981-07-27 1983-08-09 American Artos Corporation Textile fabric dryer with rotary damper arrangement

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR412478A (en) * 1909-02-17 1910-07-13 Georges Marconnet Thruster for aerial locomotion and other applications
US2102559A (en) * 1933-08-01 1937-12-14 Kadenacy Michel Explosion or internal combustion engine
FR844442A (en) * 1938-04-02 1939-07-25 Method for increasing the energy of a column of moving fluid and industrial production devices
GB525420A (en) * 1938-02-23 1940-08-28 Luigi Stipa An improved reaction propeller

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR412478A (en) * 1909-02-17 1910-07-13 Georges Marconnet Thruster for aerial locomotion and other applications
US2102559A (en) * 1933-08-01 1937-12-14 Kadenacy Michel Explosion or internal combustion engine
GB525420A (en) * 1938-02-23 1940-08-28 Luigi Stipa An improved reaction propeller
FR844442A (en) * 1938-04-02 1939-07-25 Method for increasing the energy of a column of moving fluid and industrial production devices

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2924071A (en) * 1960-02-09 de paravicini
US2683961A (en) * 1949-05-27 1954-07-20 Phillips Petroleum Co Variable frequency pulse jet engine
US2715390A (en) * 1950-07-18 1955-08-16 Tenney Resonant intermittent combustion heater and system
US2712387A (en) * 1950-10-19 1955-07-05 Frank W Young Rotary filter with pulsating blowback means
US2761283A (en) * 1951-07-23 1956-09-04 Robert E Houle Resonant type jet propulsion engines
US2806350A (en) * 1951-08-02 1957-09-17 George R Hoffmann Air flow control for jet propelled craft
US2888803A (en) * 1954-08-30 1959-06-02 Pon Lemuel Intermittent combustion turbine engine
US2984304A (en) * 1954-11-24 1961-05-16 Charles W Ranson Helicopter lifting rotor having a propulsion unit at the blade tip
US2990848A (en) * 1955-07-19 1961-07-04 Norgren Co C A Fluid pressure differential control
US3188804A (en) * 1962-10-19 1965-06-15 Melenric John Alden Turbo supercharged valveless pulse jet engine
US4397103A (en) * 1981-07-27 1983-08-09 American Artos Corporation Textile fabric dryer with rotary damper arrangement

Similar Documents

Publication Publication Date Title
US2508396A (en) Rotary air intake valve for reso-jet motors
US2446266A (en) Jet propelled helicopter rotor
US2659198A (en) Explosion-cycle inducer-disk valve turbojet engine for aircraft propulsion
US2486990A (en) Jet propulsion motor
US3702746A (en) Rotary free piston gas generator
US2573697A (en) Multitube mosaic reso-jet motor
US2517822A (en) Intermittent explosion gas turbine plant with dilution air
US2628471A (en) Synchronous augmenter for resojet motors
US1314801A (en) hahzlik
US4288981A (en) Turbine-type engine
US1282824A (en) Internal-combustion engine.
US3175359A (en) Rotary combustion engine
US1038537A (en) Gas-engine.
US2443186A (en) Jet propulsion fuel feeding and exhaust control device
US1874239A (en) Rotary internal combustion engine
US2581669A (en) Gas turbine power plant with tank supplied by long conduit having volume over six times that of the intermittent combustion gas generator
US2391636A (en) Gun
RU165003U1 (en) DEVICE FOR STABILIZING A FLAME IN AN AFTER CHAMBER OF A TURBO-REACTIVE ENGINE
US3008292A (en) Wave engines
US2547560A (en) Cup-shaped valve closure for combustion chambers
US2320928A (en) Engine
US2526645A (en) Intermittent-firing thermal air jet motor with oscillating flapper valve control
US2856753A (en) Internal-combustion turbine engine
US3362157A (en) Gas turbine engine with rotary regenerator and rotating constant volume combustion chambers
US2531581A (en) Internal-combustion turbine engine