GB865942A - Improvements relating to exhaust ducts included in jet propulsion engines - Google Patents

Improvements relating to exhaust ducts included in jet propulsion engines

Info

Publication number
GB865942A
GB865942A GB34118/59A GB3411859A GB865942A GB 865942 A GB865942 A GB 865942A GB 34118/59 A GB34118/59 A GB 34118/59A GB 3411859 A GB3411859 A GB 3411859A GB 865942 A GB865942 A GB 865942A
Authority
GB
United Kingdom
Prior art keywords
section
duct
corrugations
skin
jet propulsion
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
Application number
GB34118/59A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation Co
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 Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB865942A publication Critical patent/GB865942A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02K9/97—Rocket nozzles
    • F02K9/972—Fluid cooling arrangements for nozzles
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Exhaust Silencers (AREA)

Abstract

865,942. Generating combustion products under pressure. GENERAL MOTORS CORPORATION. Oct. 8, 1959 [Oct. 10, 1958], No. 34118/59. Class 51 (1). [Also in Group XXVI] A jet propulsion engine has an exhaust duct developed by the rotation of a curve about the axis of the duct, the curved wall portion so formed comprising a pair of spaced metal skins between which is sandwiched a corrugated metal sheet, the corrugations of which have axes running along the length of the duct, afford coolant passages and are transversely slotted. Fig. 1 shows a duct 10 with a convergentdivergent section 14 between two straight sections 12 and 16. An inner skin 18 extends the full length of the duct and is surrounded by a corrugated skin 20 having corrugations of rectangular or other section between which are formed passages 22. The portion of the skin 20 covering the section 14 has slots 24 transverse to the axes of the corrugations, these slots being staggered so that one cuts completely through a ridge and partially through a groove and the next one cuts completely through a groove and partially through a ridge. The section 14 is completed by an outer skin 26 which permits the transmission of coolant between the skins. The sections 12, 14, and 16 may be preformed and assembled subsequently or may be formed together and the section 14 shaped after the corrugations have been slotted.
GB34118/59A 1958-10-10 1959-10-08 Improvements relating to exhaust ducts included in jet propulsion engines Expired GB865942A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US865942XA 1958-10-10 1958-10-10

Publications (1)

Publication Number Publication Date
GB865942A true GB865942A (en) 1961-04-26

Family

ID=22199603

Family Applications (1)

Application Number Title Priority Date Filing Date
GB34118/59A Expired GB865942A (en) 1958-10-10 1959-10-08 Improvements relating to exhaust ducts included in jet propulsion engines

Country Status (1)

Country Link
GB (1) GB865942A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2196394A (en) * 1986-10-14 1988-04-27 Gen Electric Propulsion device
US4817890A (en) * 1986-10-14 1989-04-04 General Electric Company Multiple-propellant air vehicle and propulsion system
US4835959A (en) * 1986-10-14 1989-06-06 General Electric Company Multiple-propellant air vehicle and propulsion system
FR2945581A1 (en) * 2009-05-15 2010-11-19 Snecma Divergent for engine i.e. rocket engine, has channels located parallel to meridian lines and delimited between corrugated sheets for circulation of coolant, and external wall and internal wall connected to one another

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2196394A (en) * 1986-10-14 1988-04-27 Gen Electric Propulsion device
US4817890A (en) * 1986-10-14 1989-04-04 General Electric Company Multiple-propellant air vehicle and propulsion system
US4835959A (en) * 1986-10-14 1989-06-06 General Electric Company Multiple-propellant air vehicle and propulsion system
GB2196394B (en) * 1986-10-14 1991-06-26 Gen Electric Rocket propulsion system.
FR2945581A1 (en) * 2009-05-15 2010-11-19 Snecma Divergent for engine i.e. rocket engine, has channels located parallel to meridian lines and delimited between corrugated sheets for circulation of coolant, and external wall and internal wall connected to one another

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