FR3120852B1 - ATTACHING A FRONT CONE WITH IMPROVED AERODYNAMICS - Google Patents

ATTACHING A FRONT CONE WITH IMPROVED AERODYNAMICS Download PDF

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Publication number
FR3120852B1
FR3120852B1 FR2102698A FR2102698A FR3120852B1 FR 3120852 B1 FR3120852 B1 FR 3120852B1 FR 2102698 A FR2102698 A FR 2102698A FR 2102698 A FR2102698 A FR 2102698A FR 3120852 B1 FR3120852 B1 FR 3120852B1
Authority
FR
France
Prior art keywords
holes
cone
front cone
attaching
diameter
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
FR2102698A
Other languages
French (fr)
Other versions
FR3120852A1 (en
Inventor
Alexandre Michel Henri Hasquenoph
Kevin Bolzer
Jeremy Smith
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 FR2102698A priority Critical patent/FR3120852B1/en
Publication of FR3120852A1 publication Critical patent/FR3120852A1/en
Application granted granted Critical
Publication of FR3120852B1 publication Critical patent/FR3120852B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/14—Spinners
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/33—Retaining components in desired mutual position with a bayonet coupling

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Refuge Islands, Traffic Blockers, Or Guard Fence (AREA)

Abstract

FIXATION D’UN CONE AVANT A AERODYNAMIQUE AMELIOREE Un aspect de l’invention concerne un ensemble pour moteur aéronautique comprenant un cône avant (2) et une virole (3) d’axe X, et n vis (4) de fixation coopérant avec des écrous (5), le cône avant (2) présentant une face avant (211) et une face arrière (210), le cône avant (2) étant percé de n premiers trous (23) et la virole (3) de n deuxièmes trous (30) placés en vis-à-vis des premiers trous (23), chaque vis (4) comportant une tête (41) de diamètre d1 et un corps (40) de diamètre d0, il est caractérisé en ce que le cône avant (2) comprend n logements (24) en arc de cercle ouverts, disposés sur la face arrière (210) du cône avant (2), les n premiers trous (23) débouchant dans les n logements (24) et que le logement (24) a un profil en T, une partie large (242) correspondant à la barre du T et une partie étroite (243) correspondant au pied du T, que la partie étroite (243) a une largeur égale à d0 ± 5mm et la partie large (242) a une largeur supérieur à d1 et que les premiers trous (23) ont un diamètre D1 inférieur à d1. Figure à publier avec l’abrégé : Figure 6ATTACHING A FRONT CONE WITH IMPROVED AERODYNAMICS One aspect of the invention relates to an assembly for an aeroengine comprising a nose cone (2) and an X-axis ferrule (3), and n fixing screws (4) cooperating with nuts (5), the front cone (2) having a front face (211) and a rear face (210), the front cone (2) being pierced with n first holes (23) and the ferrule (3) with n second holes (30) placed opposite the first holes (23), each screw (4) comprising a head (41) of diameter d1 and a body (40) of diameter d0, it is characterized in that the cone front (2) comprises n housings (24) in an open arc of circle, arranged on the rear face (210) of the front cone (2), the n first holes (23) opening into the n housings (24) and that the housing (24) has a T profile, a wide part (242) corresponding to the bar of the T and a narrow part (243) corresponding to the foot of the T, that the narrow part (243) has a width equal to d0 ± 5mm and the wide part (242) has a width greater than d1 and the first holes (23) have a diameter D1 less than d1. Figure to be published with abstract: Figure 6

FR2102698A 2021-03-18 2021-03-18 ATTACHING A FRONT CONE WITH IMPROVED AERODYNAMICS Active FR3120852B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2102698A FR3120852B1 (en) 2021-03-18 2021-03-18 ATTACHING A FRONT CONE WITH IMPROVED AERODYNAMICS

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2102698A FR3120852B1 (en) 2021-03-18 2021-03-18 ATTACHING A FRONT CONE WITH IMPROVED AERODYNAMICS
FR2102698 2021-03-18

Publications (2)

Publication Number Publication Date
FR3120852A1 FR3120852A1 (en) 2022-09-23
FR3120852B1 true FR3120852B1 (en) 2023-03-17

Family

ID=75850336

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2102698A Active FR3120852B1 (en) 2021-03-18 2021-03-18 ATTACHING A FRONT CONE WITH IMPROVED AERODYNAMICS

Country Status (1)

Country Link
FR (1) FR3120852B1 (en)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2362261A1 (en) * 1973-12-14 1975-06-26 Gen Electric Fastening arrangement for nose part - esp for bullet-shaped nose as used on drive for air stream
US5573378A (en) * 1995-07-10 1996-11-12 United Technologies Corporation Gas turbine nose cone attachment
FR2908827B1 (en) 2006-11-16 2011-06-17 Snecma INPUT CONE FOR TURBOMACHINE
US8292592B2 (en) * 2008-04-02 2012-10-23 United Technologies Corporation Nosecone bolt access and aerodynamic leakage baffle
FR2986046B1 (en) 2012-01-24 2016-01-08 Snecma ASSEMBLY FOR A TURBOMACHINE BLOWER ROTOR
FR2989115B1 (en) * 2012-04-05 2015-10-30 Snecma SYSTEM FOR FASTENING A COME OF ENTRY OF A TURBOREACTOR
FR3060056B1 (en) 2016-12-13 2019-05-31 Safran Aircraft Engines CAP FOR TURBOMACHINE ROTATING INPUT HOOD, COMPRISING AERODYNAMIC EXTERNAL WALL BEYOND A CONE ATTACHMENT
FR3063309B1 (en) * 2017-02-24 2019-06-07 Safran Aircraft Engines TURBOMACHINE ROTATING INLET COVER, COMPRISING AERODYNAMIC EXTERNAL WALL AND CONE CLAMP

Also Published As

Publication number Publication date
FR3120852A1 (en) 2022-09-23

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