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1. WO2020002822 - IMPROVED FIRE RESISTANCE DEVICE DESIGNED TO BE PLACED BETWEEN ONE END OF A MOUNTING STRUT FOR AN AIRCRAFT TURBOMACHINE AND A COWLING OF SAID TURBOMACHINE, DELIMITING AN INTER-FLOW COMPARTMENT

Publication Number WO/2020/002822
Publication Date 02.01.2020
International Application No. PCT/FR2019/051554
International Filing Date 25.06.2019
IPC
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
D
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS
27
Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
26
Aircraft characterised by construction of power-plant mounting
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02
COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
C
GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7
Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
24
Heat or noise insulation
25
Fire protection or prevention
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
D
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS
45
Aircraft indicators or protectors not otherwise provided for
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
16
ENGINEERING ELEMENTS OR UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
J
PISTONS; CYLINDERS; PRESSURE VESSELS IN GENERAL; SEALINGS
15
Sealings
02
between relatively-stationary surfaces
06
with solid packing compressed between sealing surfaces
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
16
ENGINEERING ELEMENTS OR UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
J
PISTONS; CYLINDERS; PRESSURE VESSELS IN GENERAL; SEALINGS
15
Sealings
02
between relatively-stationary surfaces
F MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02
COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
C
GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7
Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
28
Arrangement of seals
B64D 27/26 (2006.01)
F02C 7/25 (2006.01)
B64D 45/00 (2006.01)
F16J 15/06 (2006.01)
F16J 15/02 (2006.01)
F02C 7/28 (2006.01)
CPC
B64D 2045/009
B64D 27/26
F02C 7/20
F02C 7/25
F05D 2230/53
F05D 2240/55
Applicants
  • SAFRAN AIRCRAFT ENGINES [FR/FR]; 2 boulevard du Général Martial Valin 75015 PARIS, FR
Inventors
  • JACON, Bruno, Alexandre, Didier; FR
  • ACHBARI, Baghdad; FR
  • SIMONOTTI, Hervé; FR
Agents
  • AHNER, Philippe; FR
Priority Data
185604129.06.2018FR
Publication Language French (FR)
Filing Language French (FR)
Designated States
Title
(EN) IMPROVED FIRE RESISTANCE DEVICE DESIGNED TO BE PLACED BETWEEN ONE END OF A MOUNTING STRUT FOR AN AIRCRAFT TURBOMACHINE AND A COWLING OF SAID TURBOMACHINE, DELIMITING AN INTER-FLOW COMPARTMENT
(FR) DISPOSITIF DE RESISTANCE AU FEU AMELIORE DESTINE A ETRE INTERPOSE ENTRE UNE EXTREMITE DE MAT D'ACCROCHAGE DE TURBOMACHINE D'AERONEF, ET UN CAPOTAGE DE LA TURBOMACHINE DELIMITANT UN COMPARTIMENT INTER-VEINE
Abstract
(EN)
The invention relates to a fire resistance device (50) that is designed to be placed between a mounting strut (9) of a double-flow aircraft turbomachine and a connecting cowling (30) with which said turbomachine is equipped, the connecting cowling being designed to connect an upstream ring (10), delimiting an inter-flow compartment (8a), to an arm (22) that extends radially across a secondary flow (26) of said turbomachine. According to the invention, the device (50) is produced as a single piece and comprises two contact lips (52a, 52b) which extend along different lines, the first lip (52a) having a C-shaped cross-section.
(FR)
L'invention concerne un dispositif de résistance au feu(50) destiné à être interposé entre unmât d'accrochage (9) d'une turbomachine d'aéronef à double flux et un capotage de raccord (30) équipant cette turbomachine, le capotage de raccord étant destiné à raccorder un anneau amont (10) délimitant un compartiment inter-veine (8a), à un bras (22) traversant radialement une veine secondaire (26) de la turbomachine. Selon l'invention, le dispositif (50) est réalisé monobloc, et comprend deux lèvres de contact (52a, 52b) s'étendant selon des lignes distinctes, dont une première lèvre (52a) de section en C.
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