FR3110637B1 - THROUGH HOLE FOR ENGINE BALANCING SCREW - Google Patents

THROUGH HOLE FOR ENGINE BALANCING SCREW Download PDF

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Publication number
FR3110637B1
FR3110637B1 FR2005034A FR2005034A FR3110637B1 FR 3110637 B1 FR3110637 B1 FR 3110637B1 FR 2005034 A FR2005034 A FR 2005034A FR 2005034 A FR2005034 A FR 2005034A FR 3110637 B1 FR3110637 B1 FR 3110637B1
Authority
FR
France
Prior art keywords
hole
balancing screw
engine
ferrule
balancing
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
FR2005034A
Other languages
French (fr)
Other versions
FR3110637A1 (en
Inventor
Jean-Marc Claude Perrollaz
Philippe Gérard Edmond Joly
Romain Nicolas Lagarde
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 FR2005034A priority Critical patent/FR3110637B1/en
Publication of FR3110637A1 publication Critical patent/FR3110637A1/en
Application granted granted Critical
Publication of FR3110637B1 publication Critical patent/FR3110637B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • 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
    • 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

Abstract

TROU DEBOUCHANT POUR VIS D’EQUILIBRAGE D’UN MOTEUR Un aspect de l’invention concerne un ensemble (1) pour moteur aéronautique comprenant un cône avant (2) et une virole (3) d’axe X fixés l’un à l’autre, la virole (3) présentant une surface extérieure (32) dans le prolongement du cône avant (2), et n vis (4) d’équilibrage disposées radialement dans un plan perpendiculaire à l’axe X et placées dans n trous débouchants (30) caractérisé en ce que chaque trou débouchant (30) présente un bord aval (311, 312) incliné axialement. L’inclinaison du bord aval (311, 312) permet de supprimer la surface frontale dans la veine aérodynamique. La surface de raccordement est alors évolutive dans le sens du flux d’air entre le trou qui sert à loger la vis d’équilibrage et la veine aérodynamique de la virole arrière de capot. Figure à publier avec l’abrégé : Figure 4THROUGH HOLE FOR ENGINE BALANCING SCREW One aspect of the invention relates to an assembly (1) for an aeronautical engine comprising a front cone (2) and an X-axis ferrule (3) fixed to each other another, the ferrule (3) having an outer surface (32) in the extension of the front cone (2), and n balancing screws (4) arranged radially in a plane perpendicular to the axis X and placed in n through holes (30) characterized in that each through hole (30) has a downstream edge (311, 312) inclined axially. The inclination of the downstream edge (311, 312) eliminates the frontal surface in the aerodynamic vein. The connection surface is then scalable in the direction of the air flow between the hole which is used to house the balancing screw and the aerodynamic vein of the rear cowl shell. Figure to be published with abstract: Figure 4

FR2005034A 2020-05-19 2020-05-19 THROUGH HOLE FOR ENGINE BALANCING SCREW Active FR3110637B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2005034A FR3110637B1 (en) 2020-05-19 2020-05-19 THROUGH HOLE FOR ENGINE BALANCING SCREW

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2005034 2020-05-19
FR2005034A FR3110637B1 (en) 2020-05-19 2020-05-19 THROUGH HOLE FOR ENGINE BALANCING SCREW

Publications (2)

Publication Number Publication Date
FR3110637A1 FR3110637A1 (en) 2021-11-26
FR3110637B1 true FR3110637B1 (en) 2023-07-21

Family

ID=72266451

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2005034A Active FR3110637B1 (en) 2020-05-19 2020-05-19 THROUGH HOLE FOR ENGINE BALANCING SCREW

Country Status (1)

Country Link
FR (1) FR3110637B1 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0102169D0 (en) * 2001-01-27 2001-03-14 Rolls Royce Plc A gas turbine engine nose cone
FR2908827B1 (en) 2006-11-16 2011-06-17 Snecma INPUT CONE FOR TURBOMACHINE
WO2014105668A1 (en) * 2012-12-28 2014-07-03 United Technologies Corporation Gas turbine engine nosecone attachment structure
US9879698B2 (en) * 2015-10-26 2018-01-30 Rolls-Royce North American Technologies Inc. Nose cone and shaft balancing assembly
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
FR3082228B1 (en) * 2018-06-08 2020-09-11 Safran Aircraft Engines TURBOMACHINE PART INCLUDING A WASHER COOPERATING WITH A BLADE

Also Published As

Publication number Publication date
FR3110637A1 (en) 2021-11-26

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