FR3062876B1 - HIGH PRESSURE COMPRESSOR FOR TURBOMACHINE - Google Patents

HIGH PRESSURE COMPRESSOR FOR TURBOMACHINE Download PDF

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Publication number
FR3062876B1
FR3062876B1 FR1751189A FR1751189A FR3062876B1 FR 3062876 B1 FR3062876 B1 FR 3062876B1 FR 1751189 A FR1751189 A FR 1751189A FR 1751189 A FR1751189 A FR 1751189A FR 3062876 B1 FR3062876 B1 FR 3062876B1
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FR
France
Prior art keywords
radially inner
vanes
turbomachine
radially
axis
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
FR1751189A
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French (fr)
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FR3062876A1 (en
Inventor
Olivier Bazot
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
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Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1751189A priority Critical patent/FR3062876B1/en
Publication of FR3062876A1 publication Critical patent/FR3062876A1/en
Application granted granted Critical
Publication of FR3062876B1 publication Critical patent/FR3062876B1/en
Active legal-status Critical Current
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Classifications

    • 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
    • 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

Abstract

L'invention concerne un ensemble pour turbomachine comprenant une rangée annulaire (14) d'aubes de stator d'axe longitudinal (L) comportant des aubes à calage variable (16) comprenant chacune une pale (18) radiale reliée extérieurement à un pivot (22) radialement externe engagé en rotation autour de son axe (A) dans une douille (38) traversant un carter externe (26) entourant extérieurement les pales radiales (18) et relié intérieurement à un pivot (20) radialement interne engagé en rotation autour de son axe (A) dans une virole annulaire (32) radialement interne, ladite rangée annulaire (14) d'aubes de stator ayant une extrémité radialement interne libre, caractérisé en ce que la rangée annulaire d'aubes (14) comprend une pluralité de bras (40a, 40b) radiaux fixés à leur extrémité radialement externe au carter externe (26) et à leur extrémité radialement interne à la virole annulaire radialement interne (32).The invention relates to an assembly for a turbomachine comprising an annular row (14) of stator vanes with a longitudinal axis (L) comprising variable-pitch vanes (16) each comprising a radial blade (18) connected externally to a pivot ( 22) radially outwardly engaged in rotation about its axis (A) in a bush (38) passing through an outer casing (26) externally surrounding the radial blades (18) and connected internally to a radially inner pivot (20) engaged in rotation around of its axis (A) in a radially inner annular shell (32), said annular row (14) of stator vanes having a free radially inner end, characterized in that the annular row of vanes (14) comprises a plurality radial arms (40a, 40b) fixed at their radially outer end to the outer casing (26) and at their radially inner end to the radially inner annular shell (32).

FR1751189A 2017-02-14 2017-02-14 HIGH PRESSURE COMPRESSOR FOR TURBOMACHINE Active FR3062876B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1751189A FR3062876B1 (en) 2017-02-14 2017-02-14 HIGH PRESSURE COMPRESSOR FOR TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1751189 2017-02-14
FR1751189A FR3062876B1 (en) 2017-02-14 2017-02-14 HIGH PRESSURE COMPRESSOR FOR TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3062876A1 FR3062876A1 (en) 2018-08-17
FR3062876B1 true FR3062876B1 (en) 2021-03-12

Family

ID=59153007

Family Applications (1)

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FR1751189A Active FR3062876B1 (en) 2017-02-14 2017-02-14 HIGH PRESSURE COMPRESSOR FOR TURBOMACHINE

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FR (1) FR3062876B1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11555420B1 (en) 2021-08-20 2023-01-17 Raytheon Technologies Corporation Frame connection between fan case and core housing in a gas turbine engine
US11608796B1 (en) 2021-11-12 2023-03-21 Raytheon Technologies Corporation Radial strut frame connection between fan case and core housing in a gas turbine engine
US11674415B2 (en) 2021-08-20 2023-06-13 Raytheon Technologies Corporation Front section stiffness ratio
US11686220B2 (en) 2021-11-12 2023-06-27 Raytheon Technologies Corporation H-frame connection between fan case and core housing in a gas turbine engine
US11708772B2 (en) 2021-11-12 2023-07-25 Raytheon Technologies Corporation Triangular-frame connection between fan case and core housing in a gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3096397B1 (en) * 2019-05-21 2021-04-16 Safran Aircraft Engines REMOVABLE PIONE ON TURBOMACHINE DISTRIBUTOR

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US8007229B2 (en) * 2007-05-24 2011-08-30 United Technologies Corporation Variable area turbine vane arrangement
EP2075413B1 (en) * 2007-12-26 2011-10-26 Techspace Aero Device for rigidifying the stator of a turbomachine and application to aircraft engines
US20140314542A1 (en) * 2012-12-21 2014-10-23 United Technologies Corporation Gas turbine engine exhaust diffuser with movable struts
EP3047116B1 (en) * 2013-09-16 2021-04-14 Raytheon Technologies Corporation Variable area turbine vane row assembly

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11555420B1 (en) 2021-08-20 2023-01-17 Raytheon Technologies Corporation Frame connection between fan case and core housing in a gas turbine engine
US11674415B2 (en) 2021-08-20 2023-06-13 Raytheon Technologies Corporation Front section stiffness ratio
US11927106B2 (en) 2021-08-20 2024-03-12 Rtx Corporation Frame connection between fan case and core housing in a gas turbine engine
US11933190B2 (en) 2021-08-20 2024-03-19 Rtx Corporation Front section stiffness ratio
US11608796B1 (en) 2021-11-12 2023-03-21 Raytheon Technologies Corporation Radial strut frame connection between fan case and core housing in a gas turbine engine
US11686220B2 (en) 2021-11-12 2023-06-27 Raytheon Technologies Corporation H-frame connection between fan case and core housing in a gas turbine engine
US11708772B2 (en) 2021-11-12 2023-07-25 Raytheon Technologies Corporation Triangular-frame connection between fan case and core housing in a gas turbine engine

Also Published As

Publication number Publication date
FR3062876A1 (en) 2018-08-17

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