GB743317A - Improved devices such as rocket motors for the directional release of high velocity hot gases - Google Patents

Improved devices such as rocket motors for the directional release of high velocity hot gases

Info

Publication number
GB743317A
GB743317A GB3283053A GB3283053A GB743317A GB 743317 A GB743317 A GB 743317A GB 3283053 A GB3283053 A GB 3283053A GB 3283053 A GB3283053 A GB 3283053A GB 743317 A GB743317 A GB 743317A
Authority
GB
United Kingdom
Prior art keywords
refractory
shell
high velocity
hot gases
cement
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
GB3283053A
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.)
Unifrax 1 LLC
Original Assignee
Carborundum 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 Carborundum Co filed Critical Carborundum Co
Priority to GB3283053A priority Critical patent/GB743317A/en
Publication of GB743317A publication Critical patent/GB743317A/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
    • F02K9/974—Nozzle- linings; Ablative coatings

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Powder Metallurgy (AREA)

Abstract

743,317. Generating combustion products under pressure. CARBORUNDUM CO. Nov. 26, 1953, No. 32830/53. Class 51 (1). [Also in Group XXVI] The outlet nozzle of a rocket motor comprises a metal shell 3 having a lining 4 of silicon-nitride bonded material cemented to the shell by a layer 5 of refractory cement. The shell is made of steel and has an internally turned end 6. It is provided with a flange 7 by which it is attached to the fuel injection head. The refractory lining 4 is formed from a mixture of finely divided silicon metal with or without the inclusion of a hard granular refractory material such as silicon carbide or a hard granular refractory oxidic material which is fired in an atmosphere of nitrogen or a nitrogenous atmosphere at a suitable temperature. The detailed compositions of suitable refractory linings and of the cement are given. Specification 716,842, [Group V], is referred to.
GB3283053A 1953-11-26 1953-11-26 Improved devices such as rocket motors for the directional release of high velocity hot gases Expired GB743317A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3283053A GB743317A (en) 1953-11-26 1953-11-26 Improved devices such as rocket motors for the directional release of high velocity hot gases

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3283053A GB743317A (en) 1953-11-26 1953-11-26 Improved devices such as rocket motors for the directional release of high velocity hot gases

Publications (1)

Publication Number Publication Date
GB743317A true GB743317A (en) 1956-01-11

Family

ID=10344630

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3283053A Expired GB743317A (en) 1953-11-26 1953-11-26 Improved devices such as rocket motors for the directional release of high velocity hot gases

Country Status (1)

Country Link
GB (1) GB743317A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1214476B (en) * 1956-12-21 1966-04-14 Haveg Industries Inc High-temperature-resistant construction or protective layer material for rocket combustion chambers or missile outer shells
CN107339519A (en) * 2016-07-01 2017-11-10 辽宁卓异新材料有限公司 A kind of anti-corrosion compound pipeline complex pipeline of novel wear resistant and preparation method thereof

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1214476B (en) * 1956-12-21 1966-04-14 Haveg Industries Inc High-temperature-resistant construction or protective layer material for rocket combustion chambers or missile outer shells
CN107339519A (en) * 2016-07-01 2017-11-10 辽宁卓异新材料有限公司 A kind of anti-corrosion compound pipeline complex pipeline of novel wear resistant and preparation method thereof
CN107339519B (en) * 2016-07-01 2020-05-05 辽宁卓异新材料有限公司 Novel wear-resistant corrosion-resistant composite pipeline and preparation method thereof

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