FR3065745B1 - AIRCRAFT TURBOMACHINE STATOR - Google Patents

AIRCRAFT TURBOMACHINE STATOR Download PDF

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Publication number
FR3065745B1
FR3065745B1 FR1753670A FR1753670A FR3065745B1 FR 3065745 B1 FR3065745 B1 FR 3065745B1 FR 1753670 A FR1753670 A FR 1753670A FR 1753670 A FR1753670 A FR 1753670A FR 3065745 B1 FR3065745 B1 FR 3065745B1
Authority
FR
France
Prior art keywords
revolution
axis
stator
cavity
respect
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
FR1753670A
Other languages
French (fr)
Other versions
FR3065745A1 (en
Inventor
Lise Julia Dufresne Alicia
Yann Dumas Lilian
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 FR1753670A priority Critical patent/FR3065745B1/en
Publication of FR3065745A1 publication Critical patent/FR3065745A1/en
Application granted granted Critical
Publication of FR3065745B1 publication Critical patent/FR3065745B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Stator (14) pour une turbomachine d'aéronef, ledit stator ayant une forme générale annulaire et étant destiné à s'étendre autour d'une roue à aubes (16) de rotor, ledit stator comportant un carter de révolution (22) comportant au moins une cavité annulaire (30) s'étendant autour d'un axe de révolution, ladite cavité débouchant radialement vers l'intérieur par rapport audit axe et étant destinée à s'étendre sensiblement autour de ladite roue, caractérisé en ce qu'il comprend des moyens de réglage d'au moins un paramètre dimensionnel de ladite cavité, tel que sa dimension radiale ou axiale vis-à-vis dudit axe de révolution, de façon à conserver une forme axisymétrique de ladite cavité vis-à-vis dudit axe de révolution.Stator (14) for an aircraft turbomachine, said stator having a generally annular shape and being intended to extend around a rotor impeller (16), said stator comprising a housing of revolution (22) comprising at at least one annular cavity (30) extending around an axis of revolution, said cavity opening radially inward with respect to said axis and being intended to extend substantially around said wheel, characterized in that it comprises means for adjusting at least one dimensional parameter of said cavity, such as its radial or axial dimension with respect to said axis of revolution, so as to maintain an axisymmetric shape of said cavity with respect to said axis of revolution.

FR1753670A 2017-04-27 2017-04-27 AIRCRAFT TURBOMACHINE STATOR Active FR3065745B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1753670A FR3065745B1 (en) 2017-04-27 2017-04-27 AIRCRAFT TURBOMACHINE STATOR

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1753670A FR3065745B1 (en) 2017-04-27 2017-04-27 AIRCRAFT TURBOMACHINE STATOR
FR1753670 2017-04-27

Publications (2)

Publication Number Publication Date
FR3065745A1 FR3065745A1 (en) 2018-11-02
FR3065745B1 true FR3065745B1 (en) 2019-12-27

Family

ID=59253733

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1753670A Active FR3065745B1 (en) 2017-04-27 2017-04-27 AIRCRAFT TURBOMACHINE STATOR

Country Status (1)

Country Link
FR (1) FR3065745B1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11092030B2 (en) * 2019-04-18 2021-08-17 Raytheon Technologies Corporation Adaptive case for a gas turbine engine
US11572897B1 (en) * 2021-07-13 2023-02-07 Pratt & Whitney Canada Corp. Compressor with casing treatment

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
WO2014143311A1 (en) * 2013-03-14 2014-09-18 Uskert Richard C Turbine shrouds
WO2014143934A1 (en) * 2013-03-15 2014-09-18 United Technologies Corporation Floating blade outer air seal assembly for gas turbine engine
US10557367B2 (en) * 2013-12-30 2020-02-11 United Technologies Corporation Accessible rapid response clearance control system
US9784117B2 (en) * 2015-06-04 2017-10-10 United Technologies Corporation Turbine engine tip clearance control system with rocker arms

Also Published As

Publication number Publication date
FR3065745A1 (en) 2018-11-02

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