FR3066779B1 - Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure - Google Patents

Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure Download PDF

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Publication number
FR3066779B1
FR3066779B1 FR1754663A FR1754663A FR3066779B1 FR 3066779 B1 FR3066779 B1 FR 3066779B1 FR 1754663 A FR1754663 A FR 1754663A FR 1754663 A FR1754663 A FR 1754663A FR 3066779 B1 FR3066779 B1 FR 3066779B1
Authority
FR
France
Prior art keywords
blade
turbomachine
turbomachine blade
measuring parameters
aerodynamic flow
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
FR1754663A
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English (en)
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FR3066779A1 (fr
Inventor
Jean Jausovec Antoine
Roger Schwartz Eric
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
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 FR1754663A priority Critical patent/FR3066779B1/fr
Priority to US15/988,982 priority patent/US10683771B2/en
Publication of FR3066779A1 publication Critical patent/FR3066779A1/fr
Application granted granted Critical
Publication of FR3066779B1 publication Critical patent/FR3066779B1/fr
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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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/83—Testing, e.g. methods, components or tools therefor
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un dispositif (1) de mesure de paramètres d'un flux aérodynamique d'une turbomachine, le dispositif (1) comprenant des moyens de relevé d'informations (2) relatives aux paramètres du flux, et un corps (3) comprenant lesdits moyens de relevé d'informations (2). Selon l'invention, le corps (3) présente une partie (4) allongée suivant une direction longitudinale (L) configurée pour former le bord d'attaque d'une pale (66) de la turbomachine et une première portion latérale (15, 16) prolongeant latéralement la partie (4) suivant une direction axiale (A), les moyens de relevé d'informations (2) étant agencés en saillie depuis le bord d'attaque de la partie (4) et la partie (4) comprenant des canaux internes (9) d'acheminement des informations en communication chacun au moins avec un moyen de relevé d'informations (2), la première portion latérale (15, 16) présentant une première surface (18, 20) configurée de manière à épouser au moins en partie une deuxième surface (19) d'une paroi intrados ou extrados d'une pale de turbomachine.
FR1754663A 2017-05-26 2017-05-26 Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure Active FR3066779B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1754663A FR3066779B1 (fr) 2017-05-26 2017-05-26 Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure
US15/988,982 US10683771B2 (en) 2017-05-26 2018-05-24 Measuring device for measuring aerodynamic flow parameters of a turbomachine vane, vane and part of turbomachine equipped with said measuring device

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1754663A FR3066779B1 (fr) 2017-05-26 2017-05-26 Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure
FR1754663 2017-05-26

Publications (2)

Publication Number Publication Date
FR3066779A1 FR3066779A1 (fr) 2018-11-30
FR3066779B1 true FR3066779B1 (fr) 2020-04-03

Family

ID=59409529

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1754663A Active FR3066779B1 (fr) 2017-05-26 2017-05-26 Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure

Country Status (2)

Country Link
US (1) US10683771B2 (fr)
FR (1) FR3066779B1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3044412B1 (fr) * 2015-11-30 2018-11-09 Safran Aircraft Engines Veine instrumentee de turbomachine
FR3090102A1 (fr) * 2018-12-17 2020-06-19 Airbus Operations Outil de mesure de pression comportant un fourreau pour sa mise en place dans une veine d’un moteur d’aeronef
US11692455B1 (en) * 2022-09-19 2023-07-04 Pratt & Whitney Canada Corp. Passively orientable pressure probe

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB759268A (en) * 1953-07-14 1956-10-17 Power Jets Res & Dev Ltd Method of mounting instruments in turbines and compressors
US4433584A (en) * 1981-11-27 1984-02-28 United Technologies Corp. Total pressure probe
US4605315A (en) * 1984-12-13 1986-08-12 United Technologies Corporation Temperature probe for rotating machinery
US4765751A (en) * 1987-06-29 1988-08-23 United Technologies Corporation Temperature and pressure probe
GB0510440D0 (en) * 2005-05-21 2005-06-29 Rolls Royce Plc An instrumentation rake
US7527471B2 (en) * 2006-07-31 2009-05-05 General Electric Company Stator vane and gas turbine engine assembly including same
US9297720B2 (en) * 2012-12-21 2016-03-29 United Technologies Corporation Gas turbine engine vane embedded beam interrupt optical tip-timing probe system
US20140182292A1 (en) * 2012-12-29 2014-07-03 United Technologies Corporation Integral instrumentation in additively manufactured components of gas turbine engines
FR3012169B1 (fr) * 2013-10-21 2018-01-12 Safran Aircraft Engines Pale instrumentee
EP3102806B1 (fr) * 2014-02-05 2020-09-09 United Technologies Corporation Capteur de pression pour turbine à gaz
FR3017459B1 (fr) * 2014-02-07 2017-07-21 Snecma Aube instrumentee a tube rapporte dans une rainure
US9856743B2 (en) * 2014-05-28 2018-01-02 Safran Aircraft Engines Instrumented flow passage of a turbine engine
GB201507281D0 (en) * 2015-04-29 2015-06-10 Composite Technology & Applic Ltd Methods and systems for bonding
GB2541356A (en) * 2015-06-08 2017-02-22 Meggitt (Uk) Ltd Moving-vane angle of attack probe
FR3043775B1 (fr) * 2015-11-12 2017-11-10 Snecma Dispositif de mesure de grandeurs aerodynamiques destine a etre place dans une veine d'ecoulement d'une turbomachine
US10520524B1 (en) * 2017-02-03 2019-12-31 Aurora Flight Sciences Corporation System and method for distributed airflow sensing

Also Published As

Publication number Publication date
FR3066779A1 (fr) 2018-11-30
US20180340444A1 (en) 2018-11-29
US10683771B2 (en) 2020-06-16

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