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FR3036735B1 - Veine instrumentee de turbomachine - Google Patents

Veine instrumentee de turbomachine Download PDF

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Publication number
FR3036735B1
FR3036735B1 FR1554724A FR1554724A FR3036735B1 FR 3036735 B1 FR3036735 B1 FR 3036735B1 FR 1554724 A FR1554724 A FR 1554724A FR 1554724 A FR1554724 A FR 1554724A FR 3036735 B1 FR3036735 B1 FR 3036735B1
Authority
FR
France
Prior art keywords
vein
internal
external
instrumented
rod
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
FR1554724A
Other languages
English (en)
Other versions
FR3036735A1 (fr
Inventor
Nicolas LAMARCHE
Jeremy Giordan
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
SNECMA 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, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1554724A priority Critical patent/FR3036735B1/fr
Priority to US14/722,877 priority patent/US9856743B2/en
Publication of FR3036735A1 publication Critical patent/FR3036735A1/fr
Application granted granted Critical
Publication of FR3036735B1 publication Critical patent/FR3036735B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
    • G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une veine annulaire (33) d'écoulement d'air d'une turbomachine, telle qu'un turboréacteur ou un turbopropulseur, traversée par une tige instrumentée (50) comportant des moyens de mesure de caractéristiques d'un flux pouvant parcourir la veine, ladite tige s'étendant entre une paroi annulaire externe (48) et une paroi annulaire interne (42) de la veine. Selon l'invention, des moyens de liaison externes (60, 86) fixent une extrémité externe (58) de la tige instrumentée à la paroi externe rigidement dans toutes les directions, et des moyens de liaison internes (62) fixent une extrémité interne (56) de la tige instrumentée à la paroi interne rigidement dans la direction circonférentielle et avec un degré de liberté en déplacement uniquement dans une direction donnée (51) s'étendant entre les parois interne (42) et externe (48) de la veine et ayant au moins une composante radiale.
FR1554724A 2014-05-28 2015-05-26 Veine instrumentee de turbomachine Active FR3036735B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1554724A FR3036735B1 (fr) 2015-05-26 2015-05-26 Veine instrumentee de turbomachine
US14/722,877 US9856743B2 (en) 2014-05-28 2015-05-27 Instrumented flow passage of a turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1554724A FR3036735B1 (fr) 2015-05-26 2015-05-26 Veine instrumentee de turbomachine
FR1554724 2015-05-26

Publications (2)

Publication Number Publication Date
FR3036735A1 FR3036735A1 (fr) 2016-12-02
FR3036735B1 true FR3036735B1 (fr) 2020-03-20

Family

ID=53484081

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1554724A Active FR3036735B1 (fr) 2014-05-28 2015-05-26 Veine instrumentee de turbomachine

Country Status (1)

Country Link
FR (1) FR3036735B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11513034B2 (en) 2020-02-14 2022-11-29 Raytheon Technologies Corporation Probe adapter for a blade outer air seal and method for using same

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3072169B1 (fr) * 2017-10-09 2019-10-11 Safran Aircraft Engines Dispositif de mesure d'au moins un parametre d'un flux aerodynamique d'une turbomachine equipe d'un moyen d'amortissement vibratoire et veine de turbomachine equipee d'un tel dispositif
FR3079299B1 (fr) * 2018-03-22 2020-06-05 Safran Aircraft Engines Dispositif de mesure des caracteristiques d'un flux d'air
FR3082937B1 (fr) * 2018-06-22 2020-07-03 Safran Aircraft Engines Dispositif de mesure de parametres d'un flux aerodynamique precontraint, veine de turbomachine pour un tel dispositif de mesure et procede de montage d'un tel dispositif de mesure

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6595062B1 (en) * 2000-10-16 2003-07-22 Lockheed Martin Corporation High temperature rake for suspersonic flow
FR2952713B1 (fr) * 2009-11-16 2014-01-03 Snecma Procede de fabrication d'un peigne de mesure comportant des moyens de mesure aptes a la mesure de parametres dans un flux d'air de turboreacteur experimental
FR2979013B1 (fr) * 2011-08-08 2015-07-03 Snecma Systeme de surveillance en banc d'essai de moteur d'aeronef
US9442022B2 (en) * 2011-12-30 2016-09-13 Unison Industries, Llc Temperature sensing device and method of assembling the same
US20140182292A1 (en) * 2012-12-29 2014-07-03 United Technologies Corporation Integral instrumentation in additively manufactured components of gas turbine engines

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11513034B2 (en) 2020-02-14 2022-11-29 Raytheon Technologies Corporation Probe adapter for a blade outer air seal and method for using same

Also Published As

Publication number Publication date
FR3036735A1 (fr) 2016-12-02

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