US2482262A - Steam production in jacketed combustion chambers - Google Patents

Steam production in jacketed combustion chambers Download PDF

Info

Publication number
US2482262A
US2482262A US77A US7748A US2482262A US 2482262 A US2482262 A US 2482262A US 77 A US77 A US 77A US 7748 A US7748 A US 7748A US 2482262 A US2482262 A US 2482262A
Authority
US
United States
Prior art keywords
chamber
combustion
volute
steam
combustion chamber
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
US77A
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
ESTHER C GODDARD
Original Assignee
DANIEL AND FLORENCE GUGGENHEIM
ESTHER C GODDARD
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, ESTHER C GODDARD filed Critical DANIEL AND FLORENCE GUGGENHEIM
Priority to US77A priority Critical patent/US2482262A/en
Application granted granted Critical
Publication of US2482262A publication Critical patent/US2482262A/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
    • F02K9/60Constructional parts; Details not otherwise provided for
    • F02K9/62Combustion or thrust chambers
    • F02K9/64Combustion or thrust chambers having cooling arrangements
    • 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

  • a further object is to provide steam-producing means which may be interposed between axially adjacent jackets on a cylindrical combustion chamber wall.
  • the invention further relates to arrangements and combinations of parts-which will be hereinafter described and more particularly pointed out in the appended claims.
  • FIG. 1 is a longitudinal section of a combustion chamber embodying this invention
  • Figs. 2 and 3 are transverse sections, taken along the lines 2-2 and 3-3 in Fig. 1;
  • Figs. 4 and 5 are enlarged sectional details of certain parts shown in Figs. 2 and 3 respectively;
  • Fig. 6 is a view similar to Fig. 5 but showing a slightly modified construction.
  • a combustion chamber C is shown as of general cylindrical shape and as being provided with a discharge nozzle N.
  • a casing l surrounds the nozzle N and a portion of chamber C and provides a jacket space S to which gasoline may be supplied through a pipe [2.
  • the left-hand portion of the space S (as viewed in Fig. 1) is connected by a pipe M to the end wall l of the chamber C, where it is fed through spray openings IE to the combustion chamber.
  • a second casing member 20 surrounds the lefthand portion ofthe combustion chamber C and encloses a jacket space S which may be supplied with liquid oxygen through a feed pipe 22.
  • the space S is connected by a pipe 24 to the end wall of the chamber C, through which liquid oxygen is delivered through spray openings 26.
  • the jacket casings l0 and 20 are spaced far enough apart axially to admit a pair of volutes 30 and 32.
  • These volutes are U-shaped in general cross section, with their inner faces open, and are welded or otherwise firmly secured to the outside of the chamber C, as clearly shown in Fig. 1.
  • Water is supplied to the volute 30 through an intake pipe 34 as indicated in Fig. 2, and steam is discharged from the volute 32 through a discharge pipe 36.
  • the cylindrical wall of the combustion chamber C has an annular series of outwardly d splaced portions .42 having openings 44 (Fig. 4) facin reversely to the direction of flow in the volute 33.
  • the chamber wall 40 also has a second series of outwardly displaced portions having openings 52 facing in the direction of flow in the volute 32.
  • the portions 42 and 50 are covered by the volutes 30 and 32 respectively.
  • combustion gases produced in the inner orleft-hand end of the chamber C travel rapidly toward the discharge nozzle N, and these 'gases are at relatively high temperatures.
  • combustion gases are not removed in any quantity from the combustion chamber, except usefully through the nozzle N, and all portions of the side walls of the chamber 0 and nozzle N are effectively jacketed.
  • FIG. 6 A slight modification is shown in Fig. 6, in which the chamber wall is provided with holes 6
  • an elongated combustion chamber having a discharge nomle, means to supply liquid fuel and oxidizer to said combustion chamber, a volute encircling said chamber in a plane transverse to the longitudinal axis of said chamber, means to supply water under pressure to said volute, said volute having tangential ports facing inward of saidchamber' and effective to introduce Jets of water from said volute tangentially into said combustion cham-.
  • an elongated combustion chamber having a discharge nozzle.
  • means to supply liquid fuel and oxidizer to said combustion chamber jacket members enclosing longitudinally spaced portions of the side wall of said combustion chamber, a pair of annular casing members encircling said chamber between said jacket members, means to supply water under pressure to the casing member which is remote from said discharge nozzle, and means to remove a mixture of steam and combustion gases from the second casing member, said combustion chamber having a plurality of tangential ports in said first casing member to direct water into said chamber and having a plurality of ports in said second casing member to abstract said mixture from said chamber.

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

Sept. 20, 1949. R. H. GODDARD 2,482,262
STEAM PRODUCTION IN JACKETED COMBUSTION CHABERS riled Jan. 2. 194a INVENTOR.
A TORNEY Patented Sept. 20, 1949 STEAM PRODUCTION IN JACKETED COM- BUSTION CHAMBERS 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 2, 1948, Serial No. 77
6 Claims. (Cl. till-35.6)
steam in a combusion chamber and without substantial interference with the normal operation of the chamber.
A further object is to provide steam-producing means which may be interposed between axially adjacent jackets on a cylindrical combustion chamber wall.
The invention further relates to arrangements and combinations of parts-which will be hereinafter described and more particularly pointed out in the appended claims.
A preferred form of the invention is shown in the drawing, in which Fig. 1 is a longitudinal section of a combustion chamber embodying this invention;
Figs. 2 and 3 are transverse sections, taken along the lines 2-2 and 3-3 in Fig. 1;
Figs. 4 and 5 are enlarged sectional details of certain parts shown in Figs. 2 and 3 respectively; and
Fig. 6 is a view similar to Fig. 5 but showing a slightly modified construction.
Referring to Fig. 1, a combustion chamber C is shown as of general cylindrical shape and as being provided with a discharge nozzle N. A casing l surrounds the nozzle N and a portion of chamber C and provides a jacket space S to which gasoline may be supplied through a pipe [2. The left-hand portion of the space S (as viewed in Fig. 1) is connected by a pipe M to the end wall l of the chamber C, where it is fed through spray openings IE to the combustion chamber.
A second casing member 20 surrounds the lefthand portion ofthe combustion chamber C and encloses a jacket space S which may be supplied with liquid oxygen through a feed pipe 22. The space S is connected by a pipe 24 to the end wall of the chamber C, through which liquid oxygen is delivered through spray openings 26.
Any usual provision, such as a spark plu 21, may be provided for igniting the mixed combustion elements.
In order to produce a limited amount of steam the direct from the combustion chamber C, the jacket casings l0 and 20 are spaced far enough apart axially to admit a pair of volutes 30 and 32. These volutes are U-shaped in general cross section, with their inner faces open, and are welded or otherwise firmly secured to the outside of the chamber C, as clearly shown in Fig. 1. Water is supplied to the volute 30 through an intake pipe 34 as indicated in Fig. 2, and steam is discharged from the volute 32 through a discharge pipe 36.
The cylindrical wall of the combustion chamber C has an annular series of outwardly d splaced portions .42 having openings 44 (Fig. 4) facin reversely to the direction of flow in the volute 33. The chamber wall 40 also has a second series of outwardly displaced portions having openings 52 facing in the direction of flow in the volute 32. The portions 42 and 50 are covered by the volutes 30 and 32 respectively.
The operation of the improved means for producing steam is as follows:
When the combustion chamber C is in active operation, combustion gases produced in the inner orleft-hand end of the chamber C travel rapidly toward the discharge nozzle N, and these 'gases are at relatively high temperatures. If
water is now supplied under pressure to the volute 30, jets of water will be injected tangentially through the openings 44 and will be immediately exposed to the direct heat of the stream of hot combustion gases. The jets of water will thus be immediately changed to a mass of steam which will travel toward the nozzle N with the combustion gases. At the same time, the mass of steam will be in rapid rotation, due to the tangential injection of the water.
When this annular mass of rotating steam reaches the plane of the volute 32, the greater portion of the steam, together with some very small amount of combustion gases, passes through the openings 52 (Fig. 5) into the volute 32, from which it is discharged through: the pipe 36. A continuous flow of steam is thusobtained for any desired purpose, while the combustion chamber continues to operate normally and without substantial interference.
The combustion gases are not removed in any quantity from the combustion chamber, except usefully through the nozzle N, and all portions of the side walls of the chamber 0 and nozzle N are effectively jacketed.
A slight modification is shown in Fig. 6, in which the chamber wall is provided with holes 6| for removal of the steam, with the edges of the holes slightly and oppositely displaced as indicated at 82 and 63, and with the edges 63 projecting slightly into the chamber 0' and being thinned down or sharpened to reduce interference with the normal flow of combustion gases.
Having thus described the invention and the advantages thereof, it will be understood that the invention is not'to be limited to the detailsherein disclosed, otherwise than as set forth in the claims, but what is claimed is:
1. In a combustion apparatus, an elongated combustion chamber having a discharge nomle, means to supply liquid fuel and oxidizer to said combustion chamber, a volute encircling said chamber in a plane transverse to the longitudinal axis of said chamber, means to supply water under pressure to said volute, said volute having tangential ports facing inward of saidchamber' and effective to introduce Jets of water from said volute tangentially into said combustion cham-.
ber, a second and reversed volute encircling said chamber adjacent said first volute and on that side of said first volute which is toward the chamber nozzle, said second volute having ports facing outward of said chamber and positioned to abstract a mixture of steam and combustion gases from the rotating and axially moving mass of steam and gases in said combustion chamber, and means to discharge said mixture from said second volute.
2. The combination in combustion apparatus as set forth in claim 1, in which the combustion chamber and nozzle are jacketed at both sides of said pair of volutes, and in which means is provided to supply cooling liquids to the jacket spaces.
3. The combination in combustion apparatus as set forth in claim 1, in which the combustion chamber and nozzle are jacketed at both sides of said pair of volutes and in which means is pro- 1 q 4 r vided to conduct the combustion liquids through the jacket spaces to the combustion chamber.
4. The combination in combustion apparatus as set forth in claim 1, in which the ports associated with the two volutes are located in outwardlyzdisplaced portions of,,the combustion chamber wall. v
5. The combination in combustion apparatus as set forth in claim 1, in which the ports for said second volute are formed as holes in the combusti'on' chamber wall, with the opposite edge portions thereof displaced outwardly and inwardly respectively, and with the edge portion which is displaced inwardly with respect to the combustion chamber madev thin and sharp.
6. In a combustion apparatus, an elongated combustion chamber having a discharge nozzle. means to supply liquid fuel and oxidizer to said combustion chamber, jacket members enclosing longitudinally spaced portions of the side wall of said combustion chamber, a pair of annular casing members encircling said chamber between said jacket members, means to supply water under pressure to the casing member which is remote from said discharge nozzle, and means to remove a mixture of steam and combustion gases from the second casing member, said combustion chamber having a plurality of tangential ports in said first casing member to direct water into said chamber and having a plurality of ports in said second casing member to abstract said mixture from said chamber.
No references cited.
US77A 1948-01-02 1948-01-02 Steam production in jacketed combustion chambers Expired - Lifetime US2482262A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US77A US2482262A (en) 1948-01-02 1948-01-02 Steam production in jacketed combustion chambers

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US77A US2482262A (en) 1948-01-02 1948-01-02 Steam production in jacketed combustion chambers

Publications (1)

Publication Number Publication Date
US2482262A true US2482262A (en) 1949-09-20

Family

ID=21689808

Family Applications (1)

Application Number Title Priority Date Filing Date
US77A Expired - Lifetime US2482262A (en) 1948-01-02 1948-01-02 Steam production in jacketed combustion chambers

Country Status (1)

Country Link
US (1) US2482262A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2636345A (en) * 1947-03-21 1953-04-28 Babcock & Wilcox Co Gas turbine combustor having helically directed openings to admit steam and secondary air
US2654997A (en) * 1952-02-23 1953-10-13 Esther C Goddard Two-liquid combustion chamber for rocket apparatus
US3400754A (en) * 1965-10-04 1968-09-10 Commissariat Energie Atomique Method and device for providing protection against scale formation on a heat exchange surface
US3404529A (en) * 1965-06-23 1968-10-08 Asea Ab Propulsion machinery for submarines
US3597923A (en) * 1969-10-02 1971-08-10 Michael Simon Rocket propulsion system
US3642061A (en) * 1968-04-16 1972-02-15 Stein & Roubaix Heat exchanger
US3773462A (en) * 1969-04-04 1973-11-20 Stein Industrie Heat exchanger
US4527514A (en) * 1983-10-20 1985-07-09 Sundstrand Corporation Direct contact liquid heater and heating method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2636345A (en) * 1947-03-21 1953-04-28 Babcock & Wilcox Co Gas turbine combustor having helically directed openings to admit steam and secondary air
US2654997A (en) * 1952-02-23 1953-10-13 Esther C Goddard Two-liquid combustion chamber for rocket apparatus
US3404529A (en) * 1965-06-23 1968-10-08 Asea Ab Propulsion machinery for submarines
US3400754A (en) * 1965-10-04 1968-09-10 Commissariat Energie Atomique Method and device for providing protection against scale formation on a heat exchange surface
US3642061A (en) * 1968-04-16 1972-02-15 Stein & Roubaix Heat exchanger
US3773462A (en) * 1969-04-04 1973-11-20 Stein Industrie Heat exchanger
US3597923A (en) * 1969-10-02 1971-08-10 Michael Simon Rocket propulsion system
US4527514A (en) * 1983-10-20 1985-07-09 Sundstrand Corporation Direct contact liquid heater and heating method

Similar Documents

Publication Publication Date Title
US2735263A (en) charshafian
US2523656A (en) Combustion apparatus comprising successive combustion chambers
US2749706A (en) Mechanism for cooling a combustion chamber in propulsion apparatus and for feeding combustion liquids thereto
US2930194A (en) Combustor having high turbulent mixing for turbine-type starter
US2482262A (en) Steam production in jacketed combustion chambers
US2706887A (en) Liquid propellant rocket motor
US2518000A (en) Auxiliary combustion chambers for reaction jet propulsion apparatus
US2510572A (en) Mixing partition for combustion chambers
US2532709A (en) Liquid cooled baffles between mixing and combustion chambers
US2576046A (en) Double-walled annular combustion chamber with turbine shaft air jacket
US2689454A (en) Rocket engine
US2544419A (en) Combustion chamber with wide-angle discharge for use in propulsion apparatus
US2526222A (en) Cooling and feeding means for rocket type combustion chambers
GB1069217A (en) Improvements relating to engines
US2612750A (en) Rotatable combustion chamber
US3171465A (en) Furnace for intermittent combustion
US2536599A (en) Steam-operated rotating combustion chamber
US3040521A (en) Thermal ignition rocket motor
US2979898A (en) Hooded crossover tube
US3286469A (en) Rocket nozzle cooling and thrust recovery device
US2518881A (en) Fuel feeding and cooling construction for rotating combustion chambers
US2808701A (en) Injector for rocket motor
GB1046909A (en) Rocket thrust chambers
US2526219A (en) Steam production from cooling liquid in combustion chambers
US2523010A (en) Auxiliary power take-off for combustion chambers