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1. WO2020114988 - AIR INTAKE AND METHOD FOR DE-ICING AN AIR INTAKE OF A NACELLE OF AN AIRCRAFT JET ENGINE

Publication Number WO/2020/114988
Publication Date 11.06.2020
International Application No. PCT/EP2019/083371
International Filing Date 03.12.2019
IPC
F02C 7/047 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
04Air intakes for gas-turbine plants or jet-propulsion plants
047Heating to prevent icing
CPC
F02C 7/045
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
04Air intakes for gas-turbine plants or jet-propulsion plants
045having provisions for noise suppression
F02C 7/047
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
04Air intakes for gas-turbine plants or jet-propulsion plants
047Heating to prevent icing
F05D 2260/202
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
202by film cooling
F05D 2260/963
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
96Preventing, counteracting or reducing vibration or noise
963by Helmholtz resonators
Applicants
  • SAFRAN NACELLES [FR]/[FR]
Inventors
  • HURLIN, Hervé Léopold
Agents
  • ARGYMA
Priority Data
187226804.12.2018FR
Publication Language French (FR)
Filing Language French (FR)
Designated States
Title
(EN) AIR INTAKE AND METHOD FOR DE-ICING AN AIR INTAKE OF A NACELLE OF AN AIRCRAFT JET ENGINE
(FR) ENTRÉE D'AIR ET PROCÉDÉ DE DÉGIVRAGE D'UNE ENTRÉE D'AIR D'UNE NACELLE D'UN TURBORÉACTEUR D'AÉRONEF
Abstract
(EN)
A de-icing device for an air intake of an aircraft jet engine nacelle extending along an axis (X) in which a flow of air flows from upstream to downstream, the intake comprising an inner wall (21) and an outer wall connected by a leading edge (23), the inner wall (21) comprising a plurality of blowing lines (3), each blowing line (3) comprising a plurality of through-openings (4) configured to blow elementary streams (Fe) from the hot air source in order to de-ice said inner wall (21), the blowing lines (3) being parallel to one another in a cylindrical projection plane, each blowing line (3) having a depth (P3) defined along the axis X and a length (L3) defined along the axis Y in the cylindrical projection plane, two adjacent blowing lines (3) being spaced apart by a distance (D3), the ratio of the distances L3/D3 being between 1 and 2.
(FR)
Un dispositif de dégivrage pour une entrée d'air d'une nacelle de turboréacteur d'aéronef s'étendant selon un axe (X) dans lequel circule un flux d'air d'amont vers l'aval, l'entrée comportant une paroi intérieure (21) et une paroi extérieure reliées par un bord d'attaque (23), la paroi intérieure (21) comportant une pluralité de lignes de soufflage (3), chaque ligne de soufflage (3) comportant une pluralité d'ouvertures traversantes (4) configurées pour souffler des flux élémentaires (Fe) issus de la source d'air chaud afin de dégivrer ladite paroi intérieure (21), les lignes de soufflage (3) étant parallèles entre elles dans un plan de projection cylindrique, chaque ligne de soufflage (3) ayant une profondeur (P3) définie selon l'axe X et une longueur (L3) définie selon l'axe Y dans le plan de projection cylindrique, deux lignes de soufflage (3) adjacentes étant écartées d'une distance (D3) le rapport des distances L3/D3 étant compris entre 1 et 2.
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