FR3115600B1 - TEST DEVICE FOR MEASURING THE TIGHTNESS OF A RING INTENDED TO EXTEND AROUND A BLADE ROTOR OF AN AIRCRAFT TURBOMACHINE AND ASSOCIATED TEST METHOD - Google Patents

TEST DEVICE FOR MEASURING THE TIGHTNESS OF A RING INTENDED TO EXTEND AROUND A BLADE ROTOR OF AN AIRCRAFT TURBOMACHINE AND ASSOCIATED TEST METHOD Download PDF

Info

Publication number
FR3115600B1
FR3115600B1 FR2011020A FR2011020A FR3115600B1 FR 3115600 B1 FR3115600 B1 FR 3115600B1 FR 2011020 A FR2011020 A FR 2011020A FR 2011020 A FR2011020 A FR 2011020A FR 3115600 B1 FR3115600 B1 FR 3115600B1
Authority
FR
France
Prior art keywords
ring
tightness
measuring
delimiting
sector
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
FR2011020A
Other languages
French (fr)
Other versions
FR3115600A1 (en
Inventor
Christophe Paul Aupetit
Rémy Pierre Marie Dupont
Eric François Mariage
Thierry Guy Xavier Tesson
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 Ceramics SA
Original Assignee
Safran Ceramics SA
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 Ceramics SA filed Critical Safran Ceramics SA
Priority to FR2011020A priority Critical patent/FR3115600B1/en
Publication of FR3115600A1 publication Critical patent/FR3115600A1/en
Application granted granted Critical
Publication of FR3115600B1 publication Critical patent/FR3115600B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • G01M3/00—Investigating fluid-tightness of structures
    • G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
    • G01M3/025—Details with respect to the testing of engines or engine parts
    • 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
    • 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
    • G01M3/00—Investigating fluid-tightness of structures
    • G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
    • G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
    • 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
    • F01D11/005—Sealing means between non relatively rotating 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
    • F01D25/28—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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/57—Leaf 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
    • F05D2260/83—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

Abstract

L’invention concerne un dispositif (100) de test pour mesurer une étanchéité d’un anneau (12) destiné à s’étendre autour d’un rotor aubagé d’une turbomachine (1) d’aéronef, l’anneau (12) comprenant des secteurs d’anneau (14) délimitant entre eux un jeu (J) inter secteurs, le dispositif (100) comprenant : - un premier secteur d’anneau (14a) et un second secteur d’anneau (14b) délimitant entre eux un jeu (J0) inter secteurs, - un support (102) de fixation et d’immobilisation des premier et second secteurs d’anneau (14a, 14b), - une enceinte (104) délimitant une cavité interne (110) dans laquelle le support (102) et le premier et second secteurs d’anneau (14a, 14b) sont agencés, l’enceinte (104) comprenant un port d’alimentation (112) en gaz de la cavité (110) et un port de sortie de gaz (114), et - un organe d’étanchéité (106) agencé entre le premier et le second secteurs d’anneau (14a, 14b) et ledit port de sortie (114), cet organe d’étanchéité (106) s’étendant autour du jeu (J0) et délimitant un passage (300) de circulation de gaz depuis le port d’entrée (112) jusqu’audit port de sortie (114). Figure d’abrégé : 4aThe invention relates to a test device (100) for measuring the tightness of a ring (12) intended to extend around a bladed rotor of an aircraft turbine engine (1), the ring (12) comprising ring sectors (14) delimiting an inter-sector clearance (J) between them, the device (100) comprising: - a first ring sector (14a) and a second ring sector (14b) delimiting between them an inter-sector play (J0), - a support (102) for fixing and immobilizing the first and second ring sectors (14a, 14b), - an enclosure (104) delimiting an internal cavity (110) in which the support (102) and the first and second ring sectors (14a, 14b) are arranged, the enclosure (104) comprising a gas supply port (112) for the cavity (110) and a gas outlet port gas (114), and - a sealing member (106) arranged between the first and the second ring sectors (14a, 14b) and said outlet port (114), this sealing member (106) extending around the gap (J0) and delimiting a passage (300) for the circulation of gas from the inlet port (112) to said outlet port (114). Abstract Figure: 4a

FR2011020A 2020-10-28 2020-10-28 TEST DEVICE FOR MEASURING THE TIGHTNESS OF A RING INTENDED TO EXTEND AROUND A BLADE ROTOR OF AN AIRCRAFT TURBOMACHINE AND ASSOCIATED TEST METHOD Active FR3115600B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2011020A FR3115600B1 (en) 2020-10-28 2020-10-28 TEST DEVICE FOR MEASURING THE TIGHTNESS OF A RING INTENDED TO EXTEND AROUND A BLADE ROTOR OF AN AIRCRAFT TURBOMACHINE AND ASSOCIATED TEST METHOD

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2011020 2020-10-28
FR2011020A FR3115600B1 (en) 2020-10-28 2020-10-28 TEST DEVICE FOR MEASURING THE TIGHTNESS OF A RING INTENDED TO EXTEND AROUND A BLADE ROTOR OF AN AIRCRAFT TURBOMACHINE AND ASSOCIATED TEST METHOD

Publications (2)

Publication Number Publication Date
FR3115600A1 FR3115600A1 (en) 2022-04-29
FR3115600B1 true FR3115600B1 (en) 2023-03-17

Family

ID=74182989

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2011020A Active FR3115600B1 (en) 2020-10-28 2020-10-28 TEST DEVICE FOR MEASURING THE TIGHTNESS OF A RING INTENDED TO EXTEND AROUND A BLADE ROTOR OF AN AIRCRAFT TURBOMACHINE AND ASSOCIATED TEST METHOD

Country Status (1)

Country Link
FR (1) FR3115600B1 (en)

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3033825B1 (en) 2015-03-16 2018-09-07 Safran Aircraft Engines TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL
FR3070417B1 (en) * 2017-08-24 2019-08-23 Safran Aircraft Engines DEVICE FOR TESTING THE INTER-SECTOR PERMEABILITY OF TWO RING SECTIONS OF A TURBOMACHINE ELEMENT

Also Published As

Publication number Publication date
FR3115600A1 (en) 2022-04-29

Similar Documents

Publication Publication Date Title
US10934872B2 (en) Turbomachine case comprising a central part projecting from two lateral portions in a junction region
JP4546334B2 (en) Turbine stator blades with improved cooling
US11300365B2 (en) Heat exchanger and leak detection system
RU2379522C2 (en) Device to adjust gas turbine radial gaps with equalisation of airflows
CN102498266B (en) Device for supporting a turbine ring, turbine having such a device, and turbine engine having such a turbine
JP5491110B2 (en) Shrouds for turbomachinery
SA05260023B1 (en) Moving blade and gas turbine using the same
US7185499B2 (en) Device for passive control of the thermal expansion of the extension casing of a turbo-jet engine
JPH08100674A (en) Method and equipment for shaft seal and cooling on exhaust side of axial-flow gas turbine
UA86585C2 (en) Lubrication device for lubrication of elements of turbo-machine and turbo-jet engine
US11808662B2 (en) Device for sealingly repositioning and cooling an air flow measuring element within an operating turbomachine
EP3012405A2 (en) Coolant flow redirection component
US9856748B2 (en) Probe tip cooling
JP2015510984A (en) Gas turbine arrangement and corresponding gas turbine to reduce stress in turbine disc
JP2012112378A (en) Sensor assembly for use with turbomachine and methods for assembling the same
JP2017122449A (en) Systems and methods for compressor diffusion slot
JP2010065690A (en) Turbine bucket with dovetail seal and related method
US10167722B2 (en) Disk outer rim seal
FR3115600B1 (en) TEST DEVICE FOR MEASURING THE TIGHTNESS OF A RING INTENDED TO EXTEND AROUND A BLADE ROTOR OF AN AIRCRAFT TURBOMACHINE AND ASSOCIATED TEST METHOD
CA2646297A1 (en) Turbomachine module provided with a device to improve radial clearances
KR20170125731A (en) Turbomachine including clearance control system
Liu et al. Comparison of 3D unsteady transient conjugate heat transfer analysis on a high pressure cooled turbine stage with experimental data
US20160123591A1 (en) Method for diverting flow around an obstruction in an internal cooling circuit
US20230160313A1 (en) Turbine rotor for a turbomachine and method for mounting the rotor
Lavagnoli et al. Wind Tunnel Testing of Turbine Blade Tip Flows

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20220429

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4