FR3081924B1 - TURBOMACHINE FOR AIRCRAFT COMPRISING A PRESSURIZED FLUID DUCT SURROUNDED BY A BRAIDED OR WOVEN METAL SHEATH - Google Patents

TURBOMACHINE FOR AIRCRAFT COMPRISING A PRESSURIZED FLUID DUCT SURROUNDED BY A BRAIDED OR WOVEN METAL SHEATH Download PDF

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Publication number
FR3081924B1
FR3081924B1 FR1854639A FR1854639A FR3081924B1 FR 3081924 B1 FR3081924 B1 FR 3081924B1 FR 1854639 A FR1854639 A FR 1854639A FR 1854639 A FR1854639 A FR 1854639A FR 3081924 B1 FR3081924 B1 FR 3081924B1
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FR
France
Prior art keywords
pressurized fluid
metal sheath
braided
aircraft
turbomachine
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.)
Active
Application number
FR1854639A
Other languages
French (fr)
Other versions
FR3081924A1 (en
Inventor
Yann Sung Yul Linee
Thierry Kohn
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1854639A priority Critical patent/FR3081924B1/en
Publication of FR3081924A1 publication Critical patent/FR3081924A1/en
Application granted granted Critical
Publication of FR3081924B1 publication Critical patent/FR3081924B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L57/00—Protection of pipes or objects of similar shape against external or internal damage or wear
    • F16L57/02—Protection of pipes or objects of similar shape against external or internal damage or wear against cracking or buckling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
    • B64D15/04—Hot gas application
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601—Fabrics
    • F05D2300/6012—Woven fabrics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6034—Orientation of fibres, weaving, ply angle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/702—Reinforcement

Abstract

Une turbomachine pour aéronef comprend au moins un conduit de fluide pressurisé (50), et au moins une gaine métallique tressée ou tissée (60) entourant une portion au moins du conduit. En cas de rupture, la gaine métallique s'oppose aux déformations et déplacements relatifs des parties (50A, 50B) du conduit situées de part et d'autre de la ligne ou zone de rupture, ce qui permet de limiter l'étendue de l'ouverture (54) formée au sein du conduit du fait de la rupture, et donc le débit de la fuite de fluide pressurisé résultant d'une telle rupture.An aircraft turbomachine comprises at least one pressurized fluid duct (50), and at least one braided or woven metal sheath (60) surrounding at least a portion of the duct. In the event of rupture, the metal sheath opposes the deformations and relative displacements of the parts (50A, 50B) of the duct located on either side of the line or zone of rupture, which makes it possible to limit the extent of the The opening (54) formed within the conduit as a result of the rupture, and therefore the rate of the leakage of pressurized fluid resulting from such rupture.

FR1854639A 2018-05-30 2018-05-30 TURBOMACHINE FOR AIRCRAFT COMPRISING A PRESSURIZED FLUID DUCT SURROUNDED BY A BRAIDED OR WOVEN METAL SHEATH Active FR3081924B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1854639A FR3081924B1 (en) 2018-05-30 2018-05-30 TURBOMACHINE FOR AIRCRAFT COMPRISING A PRESSURIZED FLUID DUCT SURROUNDED BY A BRAIDED OR WOVEN METAL SHEATH

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1854639 2018-05-30
FR1854639A FR3081924B1 (en) 2018-05-30 2018-05-30 TURBOMACHINE FOR AIRCRAFT COMPRISING A PRESSURIZED FLUID DUCT SURROUNDED BY A BRAIDED OR WOVEN METAL SHEATH

Publications (2)

Publication Number Publication Date
FR3081924A1 FR3081924A1 (en) 2019-12-06
FR3081924B1 true FR3081924B1 (en) 2021-05-14

Family

ID=62875018

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1854639A Active FR3081924B1 (en) 2018-05-30 2018-05-30 TURBOMACHINE FOR AIRCRAFT COMPRISING A PRESSURIZED FLUID DUCT SURROUNDED BY A BRAIDED OR WOVEN METAL SHEATH

Country Status (1)

Country Link
FR (1) FR3081924B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3140397A1 (en) 2022-09-30 2024-04-05 Safran Aircraft Engines Set of parts for a turbojet engine, one part of which is subject to vibrational coincidences and method for modifying the natural frequency of this set of parts

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4259989A (en) * 1979-06-06 1981-04-07 Titeflex Corporation Chafe or fire sleeve for hose
US7918081B2 (en) * 2006-12-19 2011-04-05 United Technologies Corporation Flame prevention device
FR3021350B1 (en) * 2014-05-20 2016-07-01 Snecma METHOD FOR DETECTING FLUID LEAKAGE IN TURBOMACHINE AND FLUID DISPENSING SYSTEM
WO2017189478A1 (en) * 2016-04-25 2017-11-02 Eaton Corporation Fire zone hose and method for forming the same
US10295107B2 (en) * 2016-06-24 2019-05-21 The Boeing Company Systems and methods for duct protection

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3140397A1 (en) 2022-09-30 2024-04-05 Safran Aircraft Engines Set of parts for a turbojet engine, one part of which is subject to vibrational coincidences and method for modifying the natural frequency of this set of parts

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Publication number Publication date
FR3081924A1 (en) 2019-12-06

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