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1. WO2020201034 - SYSTEM FOR COOLING AN AIRCRAFT TURBOJET ENGINE

Publication Number WO/2020/201034
Publication Date 08.10.2020
International Application No. PCT/EP2020/058632
International Filing Date 26.03.2020
IPC
F02C 7/14 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
12Cooling of plants
14of fluids in the plant
F02C 7/18 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
12Cooling of plants
16characterised by cooling medium
18the medium being gaseous, e.g. air
F02K 1/72 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
54Nozzles having means for reversing jet thrust
64Reversing fan flow
70using thrust reverser flaps or doors mounted on the fan housing
72the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F28F 9/26 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
28HEAT EXCHANGE IN GENERAL
FDETAILS OF HEAT-EXCHANGE OR HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
9Casings; Header boxes; Auxiliary supports for elements; Auxiliary members within casings
26Arrangements for connecting different sections of heat-exchange elements, e.g. of radiators
CPC
F02C 7/14
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, 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
12Cooling of plants
14of fluids in the plant ; , e.g. lubricant or fuel
F02C 7/18
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
7Features, 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
12Cooling of plants
16characterised by cooling medium
18the medium being gaseous, e.g. air
F02K 1/72
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
54Nozzles having means for reversing jet thrust
64Reversing fan flow
70using thrust reverser flaps or doors mounted on the fan housing
72the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F05D 2250/41
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2250Geometry
40Movement of components
41with one degree of freedom
F05D 2260/213
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2260Function
20Heat transfer, e.g. cooling
213by the provision of a heat exchanger within the cooling circuit
F05D 2260/50
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2260Function
50Kinematic linkage, i.e. transmission of position
Applicants
  • SAFRAN NACELLES [FR]/[FR]
Inventors
  • CORBIN, Julien
  • BOUCHOUT, Nicolas
  • DANG, Caroline
Agents
  • CABINET GERMAIN & MAUREAU
Priority Data
FR190354503.04.2019FR
Publication Language French (FR)
Filing Language French (FR)
Designated States
Title
(EN) SYSTEM FOR COOLING AN AIRCRAFT TURBOJET ENGINE
(FR) SYSTÈME DE REFROIDISSEMENT DE TURBORÉACTEUR POUR AÉRONEF
Abstract
(EN)
The invention relates to an engine nacelle (100) for a turbojet engine of the type comprising a lubricant (H), the nacelle comprising a cooling system comprising: - at least one exchanger (14), referred to as the cold source exchanger, between a heat-transfer fluid (C) and air (F), - a heat-transfer fluid inlet duct (18) leading into the cold source exchanger (14), - a heat-transfer fluid outlet duct (20) leading out of the cold source exchanger (14), the inlet (18) and outlet (20) ducts being intended to form a recirculation loop between the cold source exchanger (14) and a heat exchanger between the heat-transfer fluid and the lubricant, referred to as the hot source exchanger (12), the cold source exchanger (14) being arranged on a movable surface of the nacelle with respect to the hot source exchanger, and the heat-transfer fluid inlet and outlet ducts being extendable and/or flexible to allow the relative movement between the two exchangers to be accommodated.
(FR)
L'invention concerne une nacelle (100) de turboréacteur du type comportant un lubrifiant (H), la nacelle comprenant un système de refroidissement comportant : - au moins un échangeur (14), dit échangeur source froide, entre un fluide caloporteur (C) et de l'air (F), - un conduit d'entrée (18) de fluide caloporteur dans l'échangeur source froide (12), - un conduit de sortie (20) de fluide caloporteur de l'échangeur source froide (12) les conduits d'entrée (18) et de sortie (20) étant destinés à former une boucle de recirculation entre l'échangeur source froide (14) et un échangeur de chaleur entre le fluide caloporteur et le lubrifiant, dit échangeur source chaude (12), l'échangeur source froide (14) étant disposé sur une surface mobile de la nacelle par rapport à l'échangeur source chaude, et les conduits d'entrée et de sortie de fluide caloporteur étant extensibles et/ou flexibles pour permettre d'accommoder le mouvement relatif entre les deux échangeurs.
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