FR3115879B1 - AIRCRAFT TURBOMACHINE TEST BENCH AND METHOD FOR REDUCING THE CROSS SECTION OF A FLOW FLOW VEIN IN THIS TEST BENCH - Google Patents

AIRCRAFT TURBOMACHINE TEST BENCH AND METHOD FOR REDUCING THE CROSS SECTION OF A FLOW FLOW VEIN IN THIS TEST BENCH Download PDF

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Publication number
FR3115879B1
FR3115879B1 FR2011132A FR2011132A FR3115879B1 FR 3115879 B1 FR3115879 B1 FR 3115879B1 FR 2011132 A FR2011132 A FR 2011132A FR 2011132 A FR2011132 A FR 2011132A FR 3115879 B1 FR3115879 B1 FR 3115879B1
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France
Prior art keywords
test bench
flow
vein
cross
section
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
FR2011132A
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French (fr)
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FR3115879A1 (en
Inventor
Thibault Xavier Alexis Berranger
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 FR2011132A priority Critical patent/FR3115879B1/en
Publication of FR3115879A1 publication Critical patent/FR3115879A1/en
Application granted granted Critical
Publication of FR3115879B1 publication Critical patent/FR3115879B1/en
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Classifications

    • 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
    • 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
    • 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
    • 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
    • F05D2260/12—Testing on a test bench

Abstract

Banc d’essai (2) de turbomachine d’aéronef, comportant : - un dispositif configuré pour générer un flux de gaz (20) dans une veine annulaire (16) qui s’étend le long d’un axe (X) et qui est délimitée intérieurement par une surface annulaire externe (17) aérodynamique d’un carter (15), caractérisé en ce qu’il comprend en outre des panneaux (50) comprenant des premiers panneaux amovibles (24), les premiers panneaux (24) étant montés autour dudit carter (15) et ayant une première surface (29) annulaire externe aérodynamique destinée à recouvrir au moins en partie la surface externe (17) du carter (15) et à réduire la section transversale (25) de la veine (16) par rapport audit axe (X). Figure pour l'abrégé : Figure 3Aircraft turbomachine test bed (2), comprising: - a device configured to generate a gas flow (20) in an annular vein (16) which extends along an axis (X) and which is internally delimited by an aerodynamic outer annular surface (17) of a casing (15), characterized in that it further comprises panels (50) comprising first removable panels (24), the first panels (24) being mounted around said casing (15) and having a first aerodynamic outer annular surface (29) intended to at least partially cover the outer surface (17) of the casing (15) and to reduce the cross-section (25) of the vein (16 ) with respect to said axis (X). Figure for abstract: Figure 3

FR2011132A 2020-10-30 2020-10-30 AIRCRAFT TURBOMACHINE TEST BENCH AND METHOD FOR REDUCING THE CROSS SECTION OF A FLOW FLOW VEIN IN THIS TEST BENCH Active FR3115879B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2011132A FR3115879B1 (en) 2020-10-30 2020-10-30 AIRCRAFT TURBOMACHINE TEST BENCH AND METHOD FOR REDUCING THE CROSS SECTION OF A FLOW FLOW VEIN IN THIS TEST BENCH

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2011132A FR3115879B1 (en) 2020-10-30 2020-10-30 AIRCRAFT TURBOMACHINE TEST BENCH AND METHOD FOR REDUCING THE CROSS SECTION OF A FLOW FLOW VEIN IN THIS TEST BENCH
FR2011132 2020-10-30

Publications (2)

Publication Number Publication Date
FR3115879A1 FR3115879A1 (en) 2022-05-06
FR3115879B1 true FR3115879B1 (en) 2022-12-23

Family

ID=73793512

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2011132A Active FR3115879B1 (en) 2020-10-30 2020-10-30 AIRCRAFT TURBOMACHINE TEST BENCH AND METHOD FOR REDUCING THE CROSS SECTION OF A FLOW FLOW VEIN IN THIS TEST BENCH

Country Status (1)

Country Link
FR (1) FR3115879B1 (en)

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2905975B1 (en) * 2006-09-20 2008-12-05 Snecma Sa BLOWER DRIVE FOR A TURBOMACHINE.
US10704734B2 (en) * 2017-08-22 2020-07-07 General Electric Company Method and apparatus for determining lubricant contamination or deterioration in an engine

Also Published As

Publication number Publication date
FR3115879A1 (en) 2022-05-06

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