GB827027A - An arrangement for mounting reaction propulsion units in aircraft - Google Patents

An arrangement for mounting reaction propulsion units in aircraft

Info

Publication number
GB827027A
GB827027A GB20542/57A GB2054257A GB827027A GB 827027 A GB827027 A GB 827027A GB 20542/57 A GB20542/57 A GB 20542/57A GB 2054257 A GB2054257 A GB 2054257A GB 827027 A GB827027 A GB 827027A
Authority
GB
United Kingdom
Prior art keywords
frame
attached
unit
lugs
nacelle
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
GB20542/57A
Inventor
Gerhard Eggers
Erich Haberkorn
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB827027A publication Critical patent/GB827027A/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Measuring Fluid Pressure (AREA)

Abstract

827,027. Gas turbine jet propulsion plant. SOC. NATIONALE D' ETUDE ET DE CONSTRUCTION DE MOTEURS D' AVIATION. June 28, 1957 [July 30, 1956], No. 20542/57. Class 110 (3). [Also in Group XXXIII] The mounting of an aircraft jet propulsion unit within a nacelle comprises a substantially circular rigid frame supported by the nacelle at an intermediate section thereof and spaced from and surrounding the unit in a transverse plane near the centre of gravity of the unit, and a sheet-metal annular flange of generally frustoconical shape secured along its outer periphery to the frame and along its inner periphery to the unit. In Fig. 1, a gas turbine engine 1 is formed with a flange 4 to which is attached the frusto-conical sheet metal member 3, itself attached to the frame 5. The nacelle 2 is in two portions each attached to the frame 5 by rivets and mounting lugs 7 are also attached to the frame. The frame may be of rectangular cross-section, being formed by inner and outer cylindrical pieces riveted or welded to two annular side faces, and the inner cylindrical piece may be integral with member 3. The frame may alternatively be of circular cross-section, or may be in two portions which grip the member 3 between them. Fig. 6 shows an embodiment in which the housing 2 is disposed inside a ram jet casing 13, rods 14 extending between the lugs 7 and lugs 8 on the casing. The member 3 may be impermeable or apertured, and may be fireproof.
GB20542/57A 1956-07-30 1957-06-28 An arrangement for mounting reaction propulsion units in aircraft Expired GB827027A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR827027X 1956-07-30

Publications (1)

Publication Number Publication Date
GB827027A true GB827027A (en) 1960-02-03

Family

ID=9283158

Family Applications (1)

Application Number Title Priority Date Filing Date
GB20542/57A Expired GB827027A (en) 1956-07-30 1957-06-28 An arrangement for mounting reaction propulsion units in aircraft

Country Status (1)

Country Link
GB (1) GB827027A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2148398A (en) * 1983-10-25 1985-05-30 Alan Edward Coppin A support housing for machinery
GB2271390A (en) * 1992-10-12 1994-04-13 Rolls Royce Plc Mounting for a gas turbine engine
EP2256304A3 (en) * 2009-03-24 2015-01-07 Rolls-Royce Plc A casing arrangement

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2148398A (en) * 1983-10-25 1985-05-30 Alan Edward Coppin A support housing for machinery
GB2271390A (en) * 1992-10-12 1994-04-13 Rolls Royce Plc Mounting for a gas turbine engine
US5427348A (en) * 1992-10-12 1995-06-27 Rolls-Royce Plc Mounting for a gas turbine engine
GB2271390B (en) * 1992-10-12 1995-07-05 Rolls Royce Plc Mounting for a gas turbine engine
EP2256304A3 (en) * 2009-03-24 2015-01-07 Rolls-Royce Plc A casing arrangement

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