FR3114840B1 - Annular assembly for turbomachine turbine - Google Patents
Annular assembly for turbomachine turbine Download PDFInfo
- Publication number
- FR3114840B1 FR3114840B1 FR2010150A FR2010150A FR3114840B1 FR 3114840 B1 FR3114840 B1 FR 3114840B1 FR 2010150 A FR2010150 A FR 2010150A FR 2010150 A FR2010150 A FR 2010150A FR 3114840 B1 FR3114840 B1 FR 3114840B1
- Authority
- FR
- France
- Prior art keywords
- sector
- deflector
- crown
- annular assembly
- ring
- 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
Links
- 238000012423 maintenance Methods 0.000 abstract 1
- 230000003068 static effect Effects 0.000 abstract 1
Classifications
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- 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
- 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
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- 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
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F05D2240/10—Stators
- F05D2240/15—Heat shield
-
- 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
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
-
- 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)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Le présent docuement concerne un ensemble annulaire pour turbine de turbomachine, en particulier d’aéronef, ledit ensemble annulaire s’étendant autour d’un axe longitudinal X et comprenant :- un distributeur (20);- une roue à aubes (4) agencée en aval du distributeur (20) ;- ladite roue à aubes (4) étant entourée par un anneau sectorisé circonférentiellement et porté par le carter (16) externe et formé d’une couronne (18) et d’un déflecteur (20);caractérisé en ce que chaque secteur de déflecteur d’au moins un secteur d’anneau est engagé pour partie dans un logement du secteur de couronne dudit secteur d’anneau et en ce que le secteur de déflecteur et le secteur de couronne coopère par liaison de forme pour le maintien statique du secteur de déflecteur avec le secteur de couronne. Figure à publier avec l’abrégé : Figure 7This document relates to an annular assembly for a turbomachine turbine, in particular an aircraft turbine, said annular assembly extending around a longitudinal axis X and comprising:- a distributor (20);- a blade wheel (4) arranged downstream of the distributor (20); - said blade wheel (4) being surrounded by a circumferentially sectorized ring and carried by the outer casing (16) and formed of a crown (18) and a deflector (20); characterized in that each deflector sector of at least one ring sector is partly engaged in a housing of the crown sector of said ring sector and in that the deflector sector and the crown sector cooperate by linking form for the static maintenance of the deflector sector with the crown sector. Figure to be published with abstract: Figure 7
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2010150A FR3114840B1 (en) | 2020-10-05 | 2020-10-05 | Annular assembly for turbomachine turbine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2010150A FR3114840B1 (en) | 2020-10-05 | 2020-10-05 | Annular assembly for turbomachine turbine |
FR2010150 | 2020-10-05 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3114840A1 FR3114840A1 (en) | 2022-04-08 |
FR3114840B1 true FR3114840B1 (en) | 2022-11-11 |
Family
ID=74871448
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR2010150A Active FR3114840B1 (en) | 2020-10-05 | 2020-10-05 | Annular assembly for turbomachine turbine |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3114840B1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3145182A1 (en) * | 2023-01-23 | 2024-07-26 | Safran Aircraft Engines | Turbomachine turbine annular assembly particularly for turbine sealing |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3016391B1 (en) * | 2014-01-10 | 2017-12-29 | Snecma | DEVICE FOR SEALING AND THERMALLY PROTECTING A TURBOMACHINE |
FR3058458B1 (en) * | 2016-11-09 | 2020-11-20 | Safran Aircraft Engines | TURBOMACHINE TURBINE STAGE PROVIDED WITH SEALING MEANS |
US10428689B2 (en) * | 2017-05-17 | 2019-10-01 | Rolls-Royce Deutschland Ltd & Co Kg | Heat shield for a gas turbine engine |
FR3083563B1 (en) * | 2018-07-03 | 2020-07-24 | Safran Aircraft Engines | AIRCRAFT TURBOMACHINE SEALING MODULE |
-
2020
- 2020-10-05 FR FR2010150A patent/FR3114840B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3114840A1 (en) | 2022-04-08 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20220408 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
PLFP | Fee payment |
Year of fee payment: 4 |
|
PLFP | Fee payment |
Year of fee payment: 5 |