[go: up one dir, main page]

US2528134A - Circuit closing device for fuel feed apparatus and having quick-acting thermal control - Google Patents

Circuit closing device for fuel feed apparatus and having quick-acting thermal control Download PDF

Info

Publication number
US2528134A
US2528134A US72496A US7249649A US2528134A US 2528134 A US2528134 A US 2528134A US 72496 A US72496 A US 72496A US 7249649 A US7249649 A US 7249649A US 2528134 A US2528134 A US 2528134A
Authority
US
United States
Prior art keywords
tube
igniter
flame
chamber
quick
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
US72496A
Inventor
Esther C Goddard
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.)
DANIEL AND FLORENCE GUGGENHEIM
DANIEL AND FLORENCE GUGGENHEIM FOUNDATION
Original Assignee
DANIEL AND FLORENCE GUGGENHEIM
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 DANIEL AND FLORENCE GUGGENHEIM filed Critical DANIEL AND FLORENCE GUGGENHEIM
Priority to US72496A priority Critical patent/US2528134A/en
Application granted granted Critical
Publication of US2528134A publication Critical patent/US2528134A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44Feeding propellants
    • F02K9/56Control
    • F02K9/58Propellant feed valves
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S60/00Power plants
    • Y10S60/915Collection of goddard patents

Definitions

  • This invention relates to internal combustion chambers particularly adapted for use. in the propulsion of rockets and rocket craft and using liquid fuel, and relates more particularly to the coordinated operation of the igniter and the fuel feed control. Combustion in said chamber produces a large volume of combustion gases which are forcibly ejected from'a discharge opening in said chamber with propulsive effects.
  • the invention relates to a circult-closing device associated with the fuel feed and under quick-acting thermal control by the igniter of the combustion chamber.
  • ,lig. 2 is a sectional side elevation, looking in "the direction of the arrow 2 in Fig. 1;
  • Fig. 3 is a transverse sectional view, taken along the line 33 in Fig. 2;
  • Fig. 4 is a side elevation of an illustrative valve control device.
  • a combustion chamber C is shown as provided with an igniter H which may be of the general type shown in the prior Goddard Patent No. 2,090,039, issued August 17, 1937.
  • the igniter H comprises a relatively small igniter chamber l mounted on a tube T and to which gasoline or other liquid fuel may be fed through a pipe l2 and feed opening 14.
  • a liquid oxidizer, such as liquid oxygen, is also fed to the chamber l0 through a pipe l6, feed port or opening ll, recess 18, and additional inner feed ports or openings 20.
  • the gasoline feed is controlled by a needle valve 22, and the oxygen feed is similarly controlled by a needle valve 24.
  • a spark-plug 26 is mounted in the side of the igniter chamber l0 and may be activated by a battery Bror other source of current through a transformer T, wires 30 and 3
  • the recess 18 in the oxygen connections has a port 40 in its side wall which communicates through a passage 4
  • a series of slots 41 in one side of the flame tube 35 permit portions of oxygen to be introduced into the igniter flame at successive points along the length of the tube 35, thus keeping the flame hot and insuring complete combustion of any unconsumed fuel.
  • a portion of the oxygen also enters the combustion chamber C through the tube T and helps to prevent accidental failure of the igniter flame at the point where it is introduced to the chamber.
  • the needle valves 22 and 24 may be opened simultaneously with the closing of the switch s by any suitable coordinating device, such as is shown in Fig. 3 of the first cited Goddard patent.
  • a fuel port 50 in the chamber C is controlled by a needle valve 5!, and an oxidizer port 52 is controlled by a needle valve 53.
  • Levers 55 and 56 are mounted on fixed pivots 5'1 and 58 and are pivotally connected to the needle valves 5
  • the levers 55 and 56 have a pin-and-slot connection 62 to an armature 53 controlled by a magnet M.
  • a spring 65 also connected to the levers 55 and 56 at the point 62, holds the needle valves 5
  • Wires (0 and H connect the magnet M through a battery B to the normally spacedcontacts l2 and 73 to a switch S; When this switch is closed, the magnet M is energized and the armature 63 is drawn downward, thus raising the needle valves 5
  • the switch S is controlled by a plunger 80 attached to a disc 8
  • the tube 84 is connected to a segmental casing 86 which partially surrounds the igniter tube 35 and which is substantially extended lengthwise thereof as shown in Fig. 2.
  • the casing 83, tube 84 and space 88 between the segmental casing 86 and the tube 35 are filled with a temperature-responsive fluid by which the bellows operator P is compressed as the temperature increases and by which the plunger 80 is thereby advanced to close the switch S.
  • the tube T tends to overheat between the igniter chamber l8 and the combustion chamber C, the tube maybe provided with a jacket 90 to which cooling water may be supplied by a pipe 9! and from which the heated water may escape through a discharge pipe 92.
  • combustion apparatus having a combustion chamber, means to supply liquid fuel and a liquid oxidizer to said chamber under electric control, a flame-type igniter with a supporting outer tube and a flame-conducting inner tube, and means to produce a flame in said inner tube, that improvement which comprises a switch for such electric control, switch-shifting means responsive to temperature changes in a confined heat-responsive liquid, and a container for such liquid which consists in part of an elongated hollow segmental casing positioned in said igniter and between said inner and outer tubes and partially surrounding said flame-conducting tube.
  • combustion apparatus having a combustion chamber, means to supply liquid fuel and a liquid oxidizer to said chamber under electric control, a flame-type igniter with a supporting outer tube and a flame-conducting inner tube, and means to produce a flame in said inner tube
  • improvement which comprises a normallyopen switch for such electric control, switch-closing means responsive to temperature changes in a confined heat-responsive liquid, and a container for such liquid which includes a bellows operator for said switch and an elongated hollow segmental casing connected to said bellows operator and positioned between said inner 'and outer tubes and surrounding a large part of the heated surface of said flame-conducting tube.
  • Emecutria of the Last Will and Testament of Robert H. Goddard, Deceased.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)

Description

Oct. 31, 1950 R. H. GODDARD CIRCUIT CLOSING DEVICE FOR FUEL FEED APPARATUS AND HAVING QUICK-ACTING THERMAL CONTROL Filed Jan. -24, 1949 III In E D IN V EN TOR. Rose/z T Gem/1R0, ocb BYLsTI-IER C. Gama/ea, fxecumlx.
Patented Oct. 31, 1950 APPARATUS AND HAVING QUICK-ACTING THERMAL CONTROL Robert H. Goddard, deceased, late of Annapolis,
Md, by Esther C. Goddard, executrix, Worcester, Mass, assignor of one-half to The Daniel and'Florence Guggenheim Foundation, New York, N. Y., a corporation of New York Application January 24, 1949, Serial No. 72,496
6 Claims.
This invention relates to internal combustion chambers particularly adapted for use. in the propulsion of rockets and rocket craft and using liquid fuel, and relates more particularly to the coordinated operation of the igniter and the fuel feed control. Combustion in said chamber produces a large volume of combustion gases which are forcibly ejected from'a discharge opening in said chamber with propulsive effects.
More specifically, the invention relates to a circult-closing device associated with the fuel feed and under quick-acting thermal control by the igniter of the combustion chamber.
It is the general object of the invention to pro- .vide a construction by which fuel feed will automatically follow activation of the igniter and with much reduced delay. Such a construction is particularly usefulwhere a combustion chamber is intermittently operated.
The invention further relates to arrangements and combinations of parts Which will be hereinafter described and more particularly pointed out in the appended claims.
,lig. 2 is a sectional side elevation, looking in "the direction of the arrow 2 in Fig. 1;
Fig. 3 is a transverse sectional view, taken along the line 33 in Fig. 2; and
Fig. 4 is a side elevation of an illustrative valve control device.
Referring to the drawing, a combustion chamber C is shown as provided with an igniter H which may be of the general type shown in the prior Goddard Patent No. 2,090,039, issued August 17, 1937. As in said patent, the igniter H comprises a relatively small igniter chamber l mounted on a tube T and to which gasoline or other liquid fuel may be fed through a pipe l2 and feed opening 14. A liquid oxidizer, such as liquid oxygen, is also fed to the chamber l0 through a pipe l6, feed port or opening ll, recess 18, and additional inner feed ports or openings 20.
The gasoline feed is controlled by a needle valve 22, and the oxygen feed is similarly controlled by a needle valve 24. A spark-plug 26 is mounted in the side of the igniter chamber l0 and may be activated by a battery Bror other source of current through a transformer T, wires 30 and 3| and a manually operated switch S.
igniter chamber l0 and the switch S is closed, ignition promptly takes place and the resultant igniter flame is projected through a tube 35 to the combustion chamber C, thus igniting the fuel supplied to said combustion chamber.
The recess 18 in the oxygen connections has a port 40 in its side wall which communicates through a passage 4| and port 42 with the annular space M between the flame tube 35 and the outer tube T by which the igniter is mounted on the combustion chamber C. i
A series of slots 41 in one side of the flame tube 35 permit portions of oxygen to be introduced into the igniter flame at successive points along the length of the tube 35, thus keeping the flame hot and insuring complete combustion of any unconsumed fuel. i
A portion of the oxygen also enters the combustion chamber C through the tube T and helps to prevent accidental failure of the igniter flame at the point where it is introduced to the chamber.
The construction thus far described is similar to the construction shown in the prior Goddard patent above cited and certain features of the described construction are similar to the disclosure in copending Goddard application Serial No. 770,312, filed August 23, 1947, noW Patent No. 2,498,263.
The needle valves 22 and 24 may be opened simultaneously with the closing of the switch s by any suitable coordinating device, such as is shown in Fig. 3 of the first cited Goddard patent.
It is desirable that the fuel feed to the chamber C be started as soon as possible after the igniter flame is in effective operation.
In the illustrative device shown in Fig. 4, a fuel port 50 in the chamber C is controlled by a needle valve 5!, and an oxidizer port 52 is controlled by a needle valve 53. Levers 55 and 56 are mounted on fixed pivots 5'1 and 58 and are pivotally connected to the needle valves 5| and 53 at the points 59 and 60.
The levers 55 and 56 have a pin-and-slot connection 62 to an armature 53 controlled by a magnet M. A spring 65, also connected to the levers 55 and 56 at the point 62, holds the needle valves 5| and 53 normally in closed position.
Wires (0 and H connect the magnet M through a battery B to the normally spacedcontacts l2 and 73 to a switch S; When this switch is closed, the magnet M is energized and the armature 63 is drawn downward, thus raising the needle valves 5| and 53 and starting the feed of liquid When fuel and oxidizer are admitted to the 55 fuel and oxidizerto the combustion chamber C.
The switch S is controlled by a plunger 80 attached to a disc 8| forming the movable inner end of an annular bellows operator P which is mounted within a casing 83 supported by a tube 84 extending through and secured to the tube T which supports the igniter H.
At its inner end, the tube 84 is connected to a segmental casing 86 which partially surrounds the igniter tube 35 and which is substantially extended lengthwise thereof as shown in Fig. 2.
The casing 83, tube 84 and space 88 between the segmental casing 86 and the tube 35 are filled with a temperature-responsive fluid by which the bellows operator P is compressed as the temperature increases and by which the plunger 80 is thereby advanced to close the switch S.
As soon as the igniter flame is produced and traverses the tube 35, the liquid in the space 88 inside of the segmental casing 86 very quickly increases in temperature and expands to close the switch S. Such closing operates through the magnet M to open the fuel and oxidizer valves 50 and 52 of the chamber C. Consequently, the production of the igniter flame and the feed of fuel and oxidizer to the main combustion chamber C are closely and accurately coordinated, and the fuel feed to the chamber C follows the production of the igniter flame with extreme promptness.
If the tube T tends to overheat between the igniter chamber l8 and the combustion chamber C, the tube maybe provided with a jacket 90 to which cooling water may be supplied by a pipe 9! and from which the heated water may escape through a discharge pipe 92.
Having thus described the'invention and the advantages thereof, it will be understood that the invention is not to be limited to the detais herein disclosed, otherwise than as set forth in the claims, but what is claimed is:
1. In combustion apparatus having a combustion chamber, means to supply liquid fuel and a liquid oxidizer to said chamber under electric control, a flame-type igniter with a supporting outer tube and a flame-conducting inner tube, and means to produce a flame in said inner tube, that improvement which comprises a switch for such electric control, switch-shifting means responsive to temperature changes in a confined heat-responsive liquid, and a container for such liquid which consists in part of an elongated hollow segmental casing positioned in said igniter and between said inner and outer tubes and partially surrounding said flame-conducting tube.
2. The combination in combustion apparatus as set forth in claim 1, in which the switch-shifting means includes a bellows operator in direct communication with said hollow segmental casmg.
3. The combination in combustion apparatus as set forth in claim 1, in which means is provided to introduce additional oxidizer to the flame through that portion of the inner tube which is not enclosed by said segmental casing.
4. The combination in combustion apparatus as set forth in claim 1, in which the segmental casing encloses a major part of the periphery of said flame-conducting tube.
5. The combination in combustion apparatus as set forth in claim 1, in which the segmental casing encloses a major part of the periphery of said flame-conducting tube and is in intimate association therewith.
6. In combustion apparatus having a combustion chamber, means to supply liquid fuel and a liquid oxidizer to said chamber under electric control, a flame-type igniter with a supporting outer tube and a flame-conducting inner tube, and means to produce a flame in said inner tube, that improvement which comprises a normallyopen switch for such electric control, switch-closing means responsive to temperature changes in a confined heat-responsive liquid, and a container for such liquid which includes a bellows operator for said switch and an elongated hollow segmental casing connected to said bellows operator and positioned between said inner 'and outer tubes and surrounding a large part of the heated surface of said flame-conducting tube.
ESTHER C. GODDARD,
Emecutria: of the Last Will and Testament of Robert H. Goddard, Deceased.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 2,090,039 Goddard Aug. 17, 1937 2,269,157 Levine Jan. 6, 1942
US72496A 1949-01-24 1949-01-24 Circuit closing device for fuel feed apparatus and having quick-acting thermal control Expired - Lifetime US2528134A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US72496A US2528134A (en) 1949-01-24 1949-01-24 Circuit closing device for fuel feed apparatus and having quick-acting thermal control

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US72496A US2528134A (en) 1949-01-24 1949-01-24 Circuit closing device for fuel feed apparatus and having quick-acting thermal control

Publications (1)

Publication Number Publication Date
US2528134A true US2528134A (en) 1950-10-31

Family

ID=22107961

Family Applications (1)

Application Number Title Priority Date Filing Date
US72496A Expired - Lifetime US2528134A (en) 1949-01-24 1949-01-24 Circuit closing device for fuel feed apparatus and having quick-acting thermal control

Country Status (1)

Country Link
US (1) US2528134A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2656883A (en) * 1950-09-05 1953-10-27 Motor Wheel Corp Electric ignition and control for vaporizing oil burners
US2722800A (en) * 1949-02-21 1955-11-08 Rolls Royce Fuel systems for gas turbine engines or the like with main and pilot fuel injectors
US2741085A (en) * 1952-05-12 1956-04-10 Phillips Petroleum Co Safety device, including fusible member for rocket engine starting control
US3882676A (en) * 1972-11-01 1975-05-13 Messerschmitt Boelkow Blohm Main stream liquid-fuel rocket engine construction

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2090039A (en) * 1935-05-07 1937-08-17 Robert H Goddard Igniter
US2269157A (en) * 1940-07-31 1942-01-06 Gen Electric Automatic fluid fuel burner control

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2090039A (en) * 1935-05-07 1937-08-17 Robert H Goddard Igniter
US2269157A (en) * 1940-07-31 1942-01-06 Gen Electric Automatic fluid fuel burner control

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2722800A (en) * 1949-02-21 1955-11-08 Rolls Royce Fuel systems for gas turbine engines or the like with main and pilot fuel injectors
US2656883A (en) * 1950-09-05 1953-10-27 Motor Wheel Corp Electric ignition and control for vaporizing oil burners
US2741085A (en) * 1952-05-12 1956-04-10 Phillips Petroleum Co Safety device, including fusible member for rocket engine starting control
US3882676A (en) * 1972-11-01 1975-05-13 Messerschmitt Boelkow Blohm Main stream liquid-fuel rocket engine construction

Similar Documents

Publication Publication Date Title
US2816419A (en) Propellant displacement gas generators
US2858672A (en) Monofuel decomposition apparatus
US2677232A (en) Combination pulse jet and ram jet engine
US3177657A (en) Rocket engine
US2862482A (en) Internal combustion engine
US2544422A (en) Cooling means for a combustion chamber and nozzle in which solid fuel is burned
US3065597A (en) Reignitable solid rocket motor
US2750887A (en) Motor mechanism for missiles
US2397657A (en) Control mechanism for rocket apparatus
US2574495A (en) Flame igniter for jet propulsion units
US2479888A (en) Controlling system for reaction motors
US3568448A (en) Ignition system for igniting a gas generator by the use of combustion gases from a solid propellant rocket motor having selective zoning capabilities
US3178885A (en) Hybrid rocket engine
US2528134A (en) Circuit closing device for fuel feed apparatus and having quick-acting thermal control
US2998703A (en) Reso-jet igniter
US2397659A (en) Control mechanism for rocket apparatus
US2763126A (en) Fuel feeding and ignition means for rocket motors with non-self-igniting propellants
US2522113A (en) Means for cooling powder-burning combustion chambers and nozzles
US3143853A (en) Solid propellant burn area control
US2518882A (en) Combined igniting and fuel feed control mechanism for a thrust unit
US2743577A (en) Rocket engine control
US2299466A (en) Power generating unit and igniting means therefor
US3533233A (en) Hot gas generator utilizing a mono-propellant fuel
US3156092A (en) Hybrid demonstrator
US2465926A (en) Sequence firing of jet motors