FR3097200B1 - INPUT CONE FOR AN AIRCRAFT TURBOMACHINE - Google Patents

INPUT CONE FOR AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3097200B1
FR3097200B1 FR1906355A FR1906355A FR3097200B1 FR 3097200 B1 FR3097200 B1 FR 3097200B1 FR 1906355 A FR1906355 A FR 1906355A FR 1906355 A FR1906355 A FR 1906355A FR 3097200 B1 FR3097200 B1 FR 3097200B1
Authority
FR
France
Prior art keywords
aircraft turbomachine
input cone
base
point
fixing
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
FR1906355A
Other languages
French (fr)
Other versions
FR3097200A1 (en
Inventor
Baptiste René Roger Batonnet
Lise Jeanne Bernadette Guillot
Jean-Marc Claude Perrollaz
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 FR1906355A priority Critical patent/FR3097200B1/en
Publication of FR3097200A1 publication Critical patent/FR3097200A1/en
Application granted granted Critical
Publication of FR3097200B1 publication Critical patent/FR3097200B1/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
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/431—Rubber
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

La présente invention concerne un cône d’entrée (20) pour une turbomachine d’aéronef (1), comportant un corps tronconique (22) et une pointe (21) en matériau élastiquement déformable fixée à une extrémité (211) de plus petit diamètre dudit corps (22), caractérisé en ce qu’il comprend en outre une embase de fixation (23) de la pointe (21) audit corps (22), la pointe (21) étant fixée à ladite embase (23) qui comprend des premiers moyens de fixation sur ladite extrémité (211) ainsi que des seconds moyens de centrage coopérant avec des moyens complémentaires de ladite extrémité (211). Figure pour l'abrégé : Figure 3The present invention relates to an inlet cone (20) for an aircraft turbomachine (1), comprising a frustoconical body (22) and a tip (21) of elastically deformable material fixed to an end (211) of smaller diameter. of said body (22), characterized in that it further comprises a base (23) for fixing the point (21) to said body (22), the point (21) being fixed to said base (23) which comprises first fixing means on said end (211) as well as second centering means cooperating with complementary means of said end (211). Figure for abstract: Figure 3

FR1906355A 2019-06-14 2019-06-14 INPUT CONE FOR AN AIRCRAFT TURBOMACHINE Active FR3097200B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1906355A FR3097200B1 (en) 2019-06-14 2019-06-14 INPUT CONE FOR AN AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1906355A FR3097200B1 (en) 2019-06-14 2019-06-14 INPUT CONE FOR AN AIRCRAFT TURBOMACHINE
FR1906355 2019-06-14

Publications (2)

Publication Number Publication Date
FR3097200A1 FR3097200A1 (en) 2020-12-18
FR3097200B1 true FR3097200B1 (en) 2021-05-14

Family

ID=67875710

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1906355A Active FR3097200B1 (en) 2019-06-14 2019-06-14 INPUT CONE FOR AN AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3097200B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3137941B1 (en) * 2022-07-18 2024-05-31 Safran Aircfraft Engines DEVICE FOR FIXING A TURBOMACHINE INLET CONE

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2621554B1 (en) * 1987-10-07 1990-01-05 Snecma NON-ROTATING INPUT COVER OF CENTRALLY FIXED TURBOREACTOR AND TURBOREACTOR THUS EQUIPPED
FR2979665B1 (en) * 2011-09-02 2016-02-05 Snecma TIGHTENING DEVICE FOR TURBOMACHINE PARTS, INCLUDING AN ANNULAR CLOSURE WRENCH OPEN RADIALLY TO THE OUTSIDE
DE102016101428A1 (en) * 2016-01-27 2017-07-27 Rolls-Royce Deutschland Ltd & Co Kg Nose cone for a fan of an aircraft engine
FR3051174B1 (en) * 2016-05-10 2018-06-01 Safran Aircraft Engines FRONT ROTATING PART OF AN AIRCRAFT TURBOMACHINE RECEIVER WITH IMPROVED DESIGN FOR RELEASE OF THE CONE TIP

Also Published As

Publication number Publication date
FR3097200A1 (en) 2020-12-18

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