US3507449A - Rocket engine combustion chamber wall construction - Google Patents

Rocket engine combustion chamber wall construction Download PDF

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Publication number
US3507449A
US3507449A US659078A US3507449DA US3507449A US 3507449 A US3507449 A US 3507449A US 659078 A US659078 A US 659078A US 3507449D A US3507449D A US 3507449DA US 3507449 A US3507449 A US 3507449A
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US
United States
Prior art keywords
wire
wall
casing
combustion chamber
rocket engine
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
US659078A
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English (en)
Inventor
Karl Butter
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.)
Bolkow GmbH
Original Assignee
Bolkow GmbH
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Filing date
Publication date
Application filed by Bolkow GmbH filed Critical Bolkow GmbH
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Publication of US3507449A publication Critical patent/US3507449A/en
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Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/64—Combustion or thrust chambers having cooling arrangements

Definitions

  • a casing for a rocket engine combustion chamber formed by an axially elongated tubular inner wall enclosed by and in surface contact with an outer wall.
  • the inner wall has a number of channels in its outer surface which in combination with the inner surface of the outer wall form a plurality of cooling channels.
  • the outer Wall is formed by a strip of wire found continuously in a transverse direction around the inner wall with the longitudinal edges of the wire arranged in overlapping, interlocking relationship. In transverse cross section, the wire has U- shaped grooves into which the edge portions of the wire fit in interlocking engagement.
  • the present invention is directed to a wall construction for the casing of a rocket engine combustion chamber and, more particularly, it is concerned with a double walled casing.
  • the inner wall of the casing has a plurality of cooling channels extending in the axial direction and the outer wall is formed by a wire continuously wound about the inner wall in surface contact with it and having the edges of adjacent coils of the wire arranged in overlapping interlocking engagement.
  • the inner and outer walls of the casing and the adjacent coils of the wire forming the outer wall are integrally secured together.
  • Rocket engine combustion chambers which employ a double wall casing with the outer surface of the inner wall of the casing furnished with longitudinally extending cooling channels.
  • the outer surfaces of the channels have been closed by continuously winding a wire about the inner wall with the adjacent coils of the wire soldered together.
  • the wires used for this purpose have been strip or bandshaped with a rectangular or square cross section, for a typical arrangement see US. Patents 2,943,442 and 3,- 120,101.
  • the outer wall formed by continuous coils of wire, is capable of withstanding high radial forces resulting from the thermal P differences between the inner and outer walls and the high coolant pressures, however, it provides a problem in that it can only withstand low axial stresses across the soldered joints securing adjacent coils.
  • the present invention is directed to an arrangement of the outer wall of a combustion chamber casing capable of absorbing the high radial and axial stresses which develop in the operation of the rocket engine due to the substantially higher temperatures and greater elongation of the inner wall as compared to the outer wall.
  • the present invention utilizes a continuous strip of wire coiled transversely about the inner wall of the casing.
  • the wire is formed with grooves and edge members extending along its length with the grooves and edge members of adjacent coils interlocking and positively securing the wire in the longitudinal direction of the casing.
  • the additional surfaces formed by the cross sectional configuration of the wire afford increased strength in the integral attachment of adjacent coils of the wire.
  • the primary object of the present invention is to utilize a continuous strip of wire wound in overlapping interlocking relationship about the inner wall of a rocket engine combustion chamber to form an outer wall of increased strength in the axial direction.
  • Another object of the invention is to increase the area of surface contact between adjacent coils of wire and thereby augment the strength of the integral attachment between the coils.
  • Another object of the invention is to afford an improved cross sectional configuration of the wire forming the outer wall of the casing.
  • the preseint invention is directed to a casing for a rocket engine combustion chamber comprising an axially elongated tubular inner wall and an outer wall having at least a portion of its surface in contact with the inner wall.
  • the outer surface of the inner wall has a plurality of longitudinally extending grooves, which combine with the inner surface of the outer wall to form a plurality of axially extending cooling channels.
  • the outer wall is composed of a continuous strip of wire wound transversely around the inner wall and adjacent coils of the wire are disposed in overlapping interlocking engagement to afford increased strength in the axial direction of the casing. Further, the adjacent coils are integrally secured together affording additional strength in the axial direction.
  • FIG. 1 is a perspective view, partly in section, of the casing for a rocket engine combustion chamber showing the formation of the outer wall of the casing, and
  • FIGS. 2 to 8 illustrate a plurality of configurations of wire utilized in forming the outer wall of the casing shown in FIG. 1.
  • FIG. 1 a casing A for a rocket engine combustion chamber is shown formed by a tubular shaped axially elongated inner wall enclosed by and in surface contact with an outer wall 3. Axially extending grooves 2 are disposed along the outer surface of the inner wall 1.
  • the outer wall 3 of the casing A is formed by continuously winding a strip of wire 3A about and in contact with the outer surface of the inner wall 1.
  • the strip of wire has a configuration whereby the edges of adjacent coils of the Wire are arranged in overlapping interlocking relationship so that the outer wall is provided with increased strength in the axial direction of the casing. It is possible to shape the wire forming the outer wall 3 in a number of different forms to achieve the interlocking relationship shown in FIG. 1.
  • the wire 3A has a reverse curve configuration, that is, it has an S-shaped form.
  • the downwardly facing surface 4 of the wire has a groove 4A and its upwardly facing surface 5 has an oppositely disposed groove A.
  • the left-hand edge 4B of the strip faces downwardly and the right-hand edge 5B faces upwardly.
  • the edge 48 fits in interlocking overlapping engagement into the upwardly facing groove 5A of the adjacent coil and its other edge 5B fits into the downwardly directed groove 4A on the opposite adjacent coil of wire.
  • the upper surface 8 and the lower surface 9 is smooth or as can be seen if FIG. 1 lies in a continuous curved plane.
  • the wire 38 shown in FIG. 3 is a rectilinear version of the S-shaped arrangement illustrated in FIG. 2.
  • the wire 3B comprises a pair of right angled U-shaped members 6 and 7 joined by a common leg 15.
  • the left hand member 6 has a groove 6A facing downwardly and a downwardly directed edge member 6B, similarly the right-hand member 7 has an upwardly directed groove 7A and an upwardly extending edge member 7B.
  • the member 6B fits into the groove 7A along the edge of the adjacent coil and the upwardly directed member 78 fits into the downwardly directed groove 6A of the coil along the other edge of the wire 38.
  • the arrangement of the wire 3C is similar to that shown in FIG. 3, however, the width of the wire and the corresponding widths of the grooves and the edge members is increased. As the width of the wire strip is increased the number of turns or coils required to enclose the inner wall is reduced.
  • the wire 3D has a shape which combines features of both of the wires 3A and 3B.
  • the end members 12A, 12B of the strip 3D have round surfaces as do the downwardly and upwardly directed grooves 6D, 7D. Because the rounded surfaces of adjacent coils of the wire 3D engage one another in overlapping relationship a slight sliding or a low-resistance slipping will develop between adacent coils.
  • the surface of the end members which fit into the grooves can be oblong or, as is shown in the wire 36 of FIG. 8, it may be given a larger radius to improve the winding conditions and, in addition, to reduce the winding time by reducing the number of turns required.
  • FIG. 6 Another arrangement is shown in FIG. 6 wherein the end members 11 of the wire strip 3E and their corresponding grooves have a trapezoidal shape.
  • edge members 12A and 12B and the common intermediate member 13 are angularly disposed with regard to the inner and outer surfaces 8, 9. This shape provides an improved hooking of the interlocking portions of the wire so that a joint of increased strength is attained.
  • the individual coils of wire forming the outer wall 3 can be integrally attached to each other in any of a number of known ways, such as, by cementing, soldering or welding.
  • the joining of the individual coils of wire can be achieved by applying solder or some other binding material to the contacting surfaces of the wire strip before it is wound about the inner wall casing. After the casing A is completed it can be inserted into a furnace for soldering the contacting surfaces of the wire strip together. Further it is also possible to insert solder or other binding material between the contacting faces of the wire strip, for example a joining material could be inserted between the individual contact faces of the S- shaped Wire strip 3A shown in FIG. 2. It will be appreciated that in the other wire strip configurations shown in FIGS. 3 to 8 the soldering material could be placed between the contacting surfaces of adjacent coils of the wire strip.
  • a casing for a rocket engine combustion chamber comprising an axially elongated tubular shaped inner wall and an outer wall having a portion of its inner surface in contact with said inner wall, said outer wall formed of a continuous strip of wire wound transversely around said inner wall and having adjacent coils thereof disposed in overlapping interlocking engagement, said wire having an inner surface, an outer surface and a pair of edge surfaces disposed angularly to the inner and outer surfaces, a longitudinally extending inwardly facing groove is formed in the inner surface of said wire, a longitudinally extending outwardly facing groove is formed in the outer surface of said wire and is spaced laterally from said inwardly facing groove, said wire comprises an inwardly projecting member an outwardly projecting member and a common intermediate member positioned between said inwardly projecting member and said outwardly projecting member, said inwardly projecting member extends longitudinally along one side of said wire adjacent said inwardly facing groove, said inwardly projecting member having a pair of parallel longitudinally extending side surfaces with one of
  • a casing as set forth in claim 1 wherein the outer surface of said inner wall has a plurality of axially extending grooves therein which in combination with the inner surface of the said outer wall provide a plurality of axially extending coolant channels about the combustion chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Gas Burners (AREA)
US659078A 1966-08-12 1967-08-08 Rocket engine combustion chamber wall construction Expired - Lifetime US3507449A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEB0088452 1966-08-12

Publications (1)

Publication Number Publication Date
US3507449A true US3507449A (en) 1970-04-21

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ID=6984300

Family Applications (1)

Application Number Title Priority Date Filing Date
US659078A Expired - Lifetime US3507449A (en) 1966-08-12 1967-08-08 Rocket engine combustion chamber wall construction

Country Status (3)

Country Link
US (1) US3507449A (enrdf_load_stackoverflow)
DE (1) DE1303377B (enrdf_load_stackoverflow)
GB (1) GB1133415A (enrdf_load_stackoverflow)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3630449A (en) * 1970-05-11 1971-12-28 Us Air Force Nozzle for rocket engine
US4071194A (en) * 1976-10-28 1978-01-31 The United States Of America As Represented By The Secretary Of The Navy Means for cooling exhaust nozzle sidewalls
US4477024A (en) * 1983-04-05 1984-10-16 The United States Of America As Represented By The Secretary Of The Air Force Carbon/carbon rocket motor exit cone reinforcement
US4740357A (en) * 1986-06-27 1988-04-26 International Fuel Cells Radiation shield for reformer apparatus
US20060213182A1 (en) * 2005-03-22 2006-09-28 The Boeing Company Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing
US20080241440A1 (en) * 2005-08-19 2008-10-02 Bauer Jorg R Detachably-Affixable, Flat Components, in Particular Floor Covering Parts, and Component
US10451006B2 (en) * 2015-10-20 2019-10-22 Arianegroup Sas Propulsion chamber with reinforcing fiber belts and a method of fabricating the propulsion chamber
US10527003B1 (en) 2015-04-12 2020-01-07 Rocket Lab Usa, Inc. Rocket engine thrust chamber, injector, and turbopump

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2690472C1 (ru) * 2018-07-30 2019-06-03 Федеральное казенное предприятие "Государственный научно-исследовательский институт химических продуктов" (ФКП "ГосНИИХП") Заряд твердого ракетного топлива для стартовых реактивных двигателей

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE538923A (enrdf_load_stackoverflow) *
DE526049C (de) * 1931-06-02 Mathias Varnhagen Stossverbindung von Bauteilen aus Holz oder aehnlichen nachgiebigen Stoffen
US2288094A (en) * 1939-01-28 1942-06-30 Gen Motors Corp Method of making tubing
US3035333A (en) * 1959-01-09 1962-05-22 Edward F Baehr Method of making a regeneratively cooled combustion chamber
US3044257A (en) * 1958-06-02 1962-07-17 Thiokol Chemical Corp Combustion chamber outer jacket
US3162012A (en) * 1961-05-04 1964-12-22 Casey J Blaze Formed metal ribbon wrap
US3254487A (en) * 1963-01-04 1966-06-07 Edward F Baehr Rocket motor casing
US3289843A (en) * 1964-03-19 1966-12-06 Dorr Oliver Inc Apparatus for centrifugal screening

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE538923A (enrdf_load_stackoverflow) *
DE526049C (de) * 1931-06-02 Mathias Varnhagen Stossverbindung von Bauteilen aus Holz oder aehnlichen nachgiebigen Stoffen
US2288094A (en) * 1939-01-28 1942-06-30 Gen Motors Corp Method of making tubing
US3044257A (en) * 1958-06-02 1962-07-17 Thiokol Chemical Corp Combustion chamber outer jacket
US3035333A (en) * 1959-01-09 1962-05-22 Edward F Baehr Method of making a regeneratively cooled combustion chamber
US3162012A (en) * 1961-05-04 1964-12-22 Casey J Blaze Formed metal ribbon wrap
US3254487A (en) * 1963-01-04 1966-06-07 Edward F Baehr Rocket motor casing
US3289843A (en) * 1964-03-19 1966-12-06 Dorr Oliver Inc Apparatus for centrifugal screening

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3630449A (en) * 1970-05-11 1971-12-28 Us Air Force Nozzle for rocket engine
US4071194A (en) * 1976-10-28 1978-01-31 The United States Of America As Represented By The Secretary Of The Navy Means for cooling exhaust nozzle sidewalls
US4477024A (en) * 1983-04-05 1984-10-16 The United States Of America As Represented By The Secretary Of The Air Force Carbon/carbon rocket motor exit cone reinforcement
US4740357A (en) * 1986-06-27 1988-04-26 International Fuel Cells Radiation shield for reformer apparatus
US20090100678A1 (en) * 2005-03-22 2009-04-23 Fint Jeffry A Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing
US20060213182A1 (en) * 2005-03-22 2006-09-28 The Boeing Company Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing
US7596940B2 (en) * 2005-03-22 2009-10-06 Pratt & Whitney Rocketdyne, Inc. Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing
US8127443B2 (en) 2005-03-22 2012-03-06 United Technologies Corporation Method of fabricating a rocket engine nozzle using pressure brazing
US20080241440A1 (en) * 2005-08-19 2008-10-02 Bauer Jorg R Detachably-Affixable, Flat Components, in Particular Floor Covering Parts, and Component
US10527003B1 (en) 2015-04-12 2020-01-07 Rocket Lab Usa, Inc. Rocket engine thrust chamber, injector, and turbopump
US11408375B1 (en) 2015-04-12 2022-08-09 Rocket Labs USA, Inc. Rocket engine turbopump with coolant passage in impeller central hub
US11415082B1 (en) 2015-04-12 2022-08-16 Rocket Labs USA, Inc. Turbopump, thrust chamber, and injector with distribution system and a circular array of support columns to flow liquid from the distribution system into a combustion chamber
US12196159B1 (en) 2015-04-12 2025-01-14 Rocket Lab Usa, Inc. Rocket engine injector
US10451006B2 (en) * 2015-10-20 2019-10-22 Arianegroup Sas Propulsion chamber with reinforcing fiber belts and a method of fabricating the propulsion chamber

Also Published As

Publication number Publication date
DE1303377B (enrdf_load_stackoverflow) 1971-09-16
GB1133415A (en) 1968-11-13

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