FR3099796B1 - Air inlet of a turbomachine nacelle comprising a duct for circulating a flow of hot air between a moving upstream part and a fixed downstream part - Google Patents

Air inlet of a turbomachine nacelle comprising a duct for circulating a flow of hot air between a moving upstream part and a fixed downstream part Download PDF

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Publication number
FR3099796B1
FR3099796B1 FR1908990A FR1908990A FR3099796B1 FR 3099796 B1 FR3099796 B1 FR 3099796B1 FR 1908990 A FR1908990 A FR 1908990A FR 1908990 A FR1908990 A FR 1908990A FR 3099796 B1 FR3099796 B1 FR 3099796B1
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France
Prior art keywords
flow
air inlet
upstream part
fixed downstream
air
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Active
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FR1908990A
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French (fr)
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FR3099796A1 (en
Inventor
Pierre Charles Caruel
Loïc Chapelain
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Safran Nacelles SAS
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Safran Nacelles SAS
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Priority to FR1908990A priority Critical patent/FR3099796B1/en
Publication of FR3099796A1 publication Critical patent/FR3099796A1/en
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Publication of FR3099796B1 publication Critical patent/FR3099796B1/en
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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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Une entrée d'air d'une nacelle de turbomachine d'aéronef s’étendant selon un axe X dans lequel circule un flux d’air d’amont vers l’aval, l’entrée d’air s’étendant de manière annulaire autour de l’axe X, l’entrée d’air comportant une partie amont mobile (2a) et une partie aval fixe (2b) et au moins un organe de déplacement commandable (4) configuré pour déplacer la partie amont mobile (2a) entre une position rentrée dans laquelle la partie amont mobile (2a) est adjacente à la partie aval fixe (2b) et une position sortie dans laquelle la partie amont mobile (2a) est écartée de la partie aval fixe (2b) afin de permettre une circulation d’un flux d’air traversant entre la partie amont mobile (2a) et la partie aval fixe (2b), l’entrée d’air comportant un circuit de dégivrage (5), l’organe de déplacement commandable (4) comportant une conduite de circulation (40) reliant fluidiquement la partie amont mobile (2a) et la partie aval fixe (2b), le circuit de dégivrage (5) étant configuré pour faire circuler un flux d’air chaud (FAC) dans la conduite de circulation (40) de manière à injecter un flux d’air chaud (FAC) dans la partie amont mobile (2a). Figure de l’abrégé : Figure 8An air inlet of an aircraft turbomachine nacelle extending along an axis X in which circulates an air flow from upstream to downstream, the air inlet extending annularly around of the X axis, the air inlet comprising a mobile upstream part (2a) and a fixed downstream part (2b) and at least one controllable displacement member (4) configured to move the mobile upstream part (2a) between a retracted position in which the movable upstream part (2a) is adjacent to the fixed downstream part (2b) and an extended position in which the movable upstream part (2a) is spaced from the fixed downstream part (2b) in order to allow circulation a flow of air passing between the mobile upstream part (2a) and the fixed downstream part (2b), the air inlet comprising a defrost circuit (5), the controllable displacement member (4) comprising a circulation pipe (40) fluidly connecting the mobile upstream part (2a) and the fixed downstream part (2b), the defrost circuit (5) being configured to f area circulating a flow of hot air (FAC) in the circulation pipe (40) so as to inject a flow of hot air (FAC) into the mobile upstream part (2a). Abstract figure: Figure 8

FR1908990A 2019-08-06 2019-08-06 Air inlet of a turbomachine nacelle comprising a duct for circulating a flow of hot air between a moving upstream part and a fixed downstream part Active FR3099796B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1908990A FR3099796B1 (en) 2019-08-06 2019-08-06 Air inlet of a turbomachine nacelle comprising a duct for circulating a flow of hot air between a moving upstream part and a fixed downstream part

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1908990A FR3099796B1 (en) 2019-08-06 2019-08-06 Air inlet of a turbomachine nacelle comprising a duct for circulating a flow of hot air between a moving upstream part and a fixed downstream part
FR1908990 2019-08-06

Publications (2)

Publication Number Publication Date
FR3099796A1 FR3099796A1 (en) 2021-02-12
FR3099796B1 true FR3099796B1 (en) 2021-07-16

Family

ID=68072816

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1908990A Active FR3099796B1 (en) 2019-08-06 2019-08-06 Air inlet of a turbomachine nacelle comprising a duct for circulating a flow of hot air between a moving upstream part and a fixed downstream part

Country Status (1)

Country Link
FR (1) FR3099796B1 (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB850691A (en) * 1957-05-14 1960-10-05 Power Jets Res & Dev Ltd Improvements in or relating to aircraft engine nacelle structures
US5014933A (en) 1989-04-27 1991-05-14 The Boeing Company Translating lip aircraft cowling structure adapted for noise reduction
US10221764B2 (en) * 2014-08-19 2019-03-05 Pratt & Whitney Canada Corp. Variable geometry inlet system

Also Published As

Publication number Publication date
FR3099796A1 (en) 2021-02-12

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