FR3108369B1 - AIRCRAFT TURBOMACHINE RECTIFIER, INCLUDING VARIABLE PITCH ANGLE BLADE SWING LIMITER - Google Patents

AIRCRAFT TURBOMACHINE RECTIFIER, INCLUDING VARIABLE PITCH ANGLE BLADE SWING LIMITER Download PDF

Info

Publication number
FR3108369B1
FR3108369B1 FR2002650A FR2002650A FR3108369B1 FR 3108369 B1 FR3108369 B1 FR 3108369B1 FR 2002650 A FR2002650 A FR 2002650A FR 2002650 A FR2002650 A FR 2002650A FR 3108369 B1 FR3108369 B1 FR 3108369B1
Authority
FR
France
Prior art keywords
pitch angle
variable pitch
aircraft turbomachine
including variable
angle blade
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
FR2002650A
Other languages
French (fr)
Other versions
FR3108369A1 (en
Inventor
Delphine Hermance Maxime Parent
Kamel Benderradji
Pauline Anne Freche
Joël Robert Mathieu
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 FR2002650A priority Critical patent/FR3108369B1/en
Publication of FR3108369A1 publication Critical patent/FR3108369A1/en
Application granted granted Critical
Publication of FR3108369B1 publication Critical patent/FR3108369B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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

Abstract

L’invention concerne un redresseur (24) pour turbomachine d’aéronef, comprenant une structure annulaire extérieure (30), une structure annulaire intérieure (40), ainsi qu’une pluralité d’aubes (26) à angle de calage variable comprenant une tête (50) ainsi qu’un pied (60) définissant ensemble un axe de rotation (76) de l’aube. Selon l’invention, le redresseur comprend, associé à au moins l’une des aubes (26) à angle de calage variable, un limitateur (80) de pivotement de cette aube autour de son axe de rotation (76), le limitateur comprenant : - au moins un organe de butée (96a, 96b) prévu sur un premier élément (60) parmi la tête et le pied de l’aube ; et - au moins un organe de butée complémentaire (102a, 102b) prévu sur la structure annulaire extérieure/intérieure (40) qui coopère avec ledit premier élément (60). Figure pour l’abrégé : Figure 3.The invention relates to a stator (24) for an aircraft turbomachine, comprising an outer annular structure (30), an inner annular structure (40), as well as a plurality of blades (26) with variable pitch angle comprising a head (50) and a foot (60) together defining an axis of rotation (76) of the blade. According to the invention, the stator comprises, associated with at least one of the vanes (26) with variable pitch angle, a limiter (80) for pivoting of this vane around its axis of rotation (76), the limiter comprising : - at least one abutment member (96a, 96b) provided on a first element (60) among the head and the root of the blade; and - at least one complementary abutment member (102a, 102b) provided on the outer/inner annular structure (40) which cooperates with said first element (60). Figure for abstract: Figure 3.

FR2002650A 2020-03-18 2020-03-18 AIRCRAFT TURBOMACHINE RECTIFIER, INCLUDING VARIABLE PITCH ANGLE BLADE SWING LIMITER Active FR3108369B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2002650A FR3108369B1 (en) 2020-03-18 2020-03-18 AIRCRAFT TURBOMACHINE RECTIFIER, INCLUDING VARIABLE PITCH ANGLE BLADE SWING LIMITER

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2002650A FR3108369B1 (en) 2020-03-18 2020-03-18 AIRCRAFT TURBOMACHINE RECTIFIER, INCLUDING VARIABLE PITCH ANGLE BLADE SWING LIMITER
FR2002650 2020-03-18

Publications (2)

Publication Number Publication Date
FR3108369A1 FR3108369A1 (en) 2021-09-24
FR3108369B1 true FR3108369B1 (en) 2022-10-28

Family

ID=70804783

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2002650A Active FR3108369B1 (en) 2020-03-18 2020-03-18 AIRCRAFT TURBOMACHINE RECTIFIER, INCLUDING VARIABLE PITCH ANGLE BLADE SWING LIMITER

Country Status (1)

Country Link
FR (1) FR3108369B1 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4585390A (en) * 1984-06-04 1986-04-29 General Electric Company Vane retaining means
FR2582720B1 (en) * 1985-05-29 1989-06-02 Snecma PROCESS FOR PRODUCING A TURBOMACHINE BLADE PIVOT AND A STATOR BLADE COMPRISING SAME
FR2775731B1 (en) * 1998-03-05 2000-04-07 Snecma CIRCULAR STAGE OF BLADES AT INTERIOR ENDS JOINED BY A CONNECTING RING
FR2890707B1 (en) 2005-09-14 2007-12-14 Snecma SOCKET FOR VANE PIVOT WITH VARIABLE SETTING ANGLE FOR TURBOMACHINE
FR2941018B1 (en) 2009-01-09 2011-02-11 Snecma A VARIABLE CALIPER FOR A RECTIFIER STAGE, COMPRISING A NON-CIRCULAR INTERNAL PLATFORM
US20140234087A1 (en) * 2013-02-17 2014-08-21 United Technologies Corporation Inlet guide vane retention feature

Also Published As

Publication number Publication date
FR3108369A1 (en) 2021-09-24

Similar Documents

Publication Publication Date Title
US10400622B2 (en) Guide vane adjusting device and turbomachine
US5730584A (en) Vibration damping
EP1939399A3 (en) Turbine assembly
FR3107319B1 (en) TURBOMACHINE MODULE EQUIPPED WITH STATOR BLADE PITCH CHANGE SYSTEM
DE3223164C2 (en) Turbo machine rotor assembly and blade
GB2547554A (en) Turbomachine blade, compromising a root with reduced stress concentrations
FR3108369B1 (en) AIRCRAFT TURBOMACHINE RECTIFIER, INCLUDING VARIABLE PITCH ANGLE BLADE SWING LIMITER
US9500091B2 (en) Wear-resistant part for the support of a blade of a turbojet fan
EP1462617A3 (en) Blading for an axial-flow turbomachine
FR3091725B1 (en) TOGETHER FOR A TURBOMACHINE
EP3312388B1 (en) Rotor part, corresponding compressor, turbine and manufacturing method
FR3112809B1 (en) TURBOMACHINE MODULE EQUIPPED WITH A PROPELLER AND STATOR VANE SUPPORTED BY HOLDING MEANS AND CORRESPONDING TURBOMACHINE
US10036282B2 (en) Vane support systems
EP3739171A3 (en) Vane forward rail for gas turbine engine assembly
FR3060065B1 (en) TURBOMACHINE PARTS SET WITH INTEGRATED PLATFORM BLOWER VANE AND CORRESPONDING TURBOMACHINE
CN1982674A (en) Variable stator vane assembly
US20180156050A1 (en) Steam turbine
US20180328195A1 (en) Rotor device of a turbomachine
FR3082878B1 (en) TURBOMACHINE DAWN
FR3076865B1 (en) REAR ASSEMBLY OF AN AIRCRAFT TURBOREACTOR NACELLE INCLUDING A SLIDING GRID DRIVE INVERTER
CN107810309A (en) The rotor blade of turbomachinery
FR3041714B1 (en) TURBOMACHINE COMPRESSOR, ESPECIALLY AN AIRPLANE TURBOPROPELLER OR TURBOREACTOR
GB2596677A9 (en) Variable-pitch stator blade for an aircraft turbine engine
FR3082555B1 (en) STRAIGHTENING VANE WHEEL OF AN AIRCRAFT ENGINE, SUCH AS A TURBOREACTOR
FR3104636B1 (en) IMPROVED DESIGN STATOR SECTOR FOR AIRCRAFT TURBOMACHINE

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20210924

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5