FR3083260B1 - Module d’un moteur d’aeronef a double flux dont un bras integre une aube de stator - Google Patents
Module d’un moteur d’aeronef a double flux dont un bras integre une aube de stator Download PDFInfo
- Publication number
- FR3083260B1 FR3083260B1 FR1855840A FR1855840A FR3083260B1 FR 3083260 B1 FR3083260 B1 FR 3083260B1 FR 1855840 A FR1855840 A FR 1855840A FR 1855840 A FR1855840 A FR 1855840A FR 3083260 B1 FR3083260 B1 FR 3083260B1
- Authority
- FR
- France
- Prior art keywords
- module
- aircraft engine
- double flow
- flow
- stator vane
- 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
- 210000003462 vein Anatomy 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
-
- 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
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
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- 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
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
L'invention concerne un module d'un moteur (1) d'aéronef à double flux, comportant une veine annulaire (8) d'écoulement d'un flux secondaire (F) de gaz dans laquelle est montée une rangée annulaire (10) d'aubes de stator configurées pour redresser le flux de gaz, un bras (2) s'étendant dans ladite veine (8) en aval de ladite rangée annulaire (10) d'aubes et étant relié physiquement à l'une desdites aubes (2b) de stator de façon à former un ensemble aérodynamique unique, caractérisé en ce qu'au moins une (15') des deux aubes adjacentes à l'aube (2b) dudit ensemble aérodynamique unique est du type à calage variable et apte à être déplacée en rotation autour d'un axe sensiblement radial par rapport à un axe longitudinal (X) du moteur.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1855840A FR3083260B1 (fr) | 2018-06-28 | 2018-06-28 | Module d’un moteur d’aeronef a double flux dont un bras integre une aube de stator |
US16/455,126 US11319899B2 (en) | 2018-06-28 | 2019-06-27 | Module of an aircraft bypass engine of which one arm integrates a stator blade |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1855840A FR3083260B1 (fr) | 2018-06-28 | 2018-06-28 | Module d’un moteur d’aeronef a double flux dont un bras integre une aube de stator |
FR1855840 | 2018-06-28 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3083260A1 FR3083260A1 (fr) | 2020-01-03 |
FR3083260B1 true FR3083260B1 (fr) | 2020-06-19 |
Family
ID=63407474
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1855840A Active FR3083260B1 (fr) | 2018-06-28 | 2018-06-28 | Module d’un moteur d’aeronef a double flux dont un bras integre une aube de stator |
Country Status (2)
Country | Link |
---|---|
US (1) | US11319899B2 (fr) |
FR (1) | FR3083260B1 (fr) |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2631386A1 (fr) * | 1988-05-11 | 1989-11-17 | Snecma | Turbomachine comportant une grille d'entree incorporant des tubes de passage d'huile |
US5203163A (en) * | 1990-08-01 | 1993-04-20 | General Electric Company | Heat exchange arrangement in a gas turbine engine fan duct for cooling hot bleed air |
WO2013141930A1 (fr) * | 2011-12-30 | 2013-09-26 | United Technologies Corporation | Turbomoteur à faible rapport de pression de soufflante |
US10221707B2 (en) * | 2013-03-07 | 2019-03-05 | Pratt & Whitney Canada Corp. | Integrated strut-vane |
FR3004749B1 (fr) * | 2013-04-22 | 2015-05-08 | Snecma | Roue de stator, roue d'aubes de redresseur, turbomachine equipee d'une telle roue et procede de compensation de la distorsion dans une telle roue |
WO2015084452A2 (fr) * | 2013-09-16 | 2015-06-11 | United Technologies Corporation | Ensemble rangée d'aubes de turbine à superficie variable |
FR3032495B1 (fr) * | 2015-02-09 | 2017-01-13 | Snecma | Ensemble de redressement a performances aerodynamiques optimisees |
FR3032480B1 (fr) * | 2015-02-09 | 2018-07-27 | Safran Aircraft Engines | Ensemble de redressement d'air a performances aerodynamiques ameliorees |
FR3039227B1 (fr) | 2015-07-22 | 2019-12-27 | Safran Aircraft Engines | Aeronef comprenant un propulseur arriere carene avec stator d’entree a volets mobiles |
US20170058831A1 (en) * | 2015-08-27 | 2017-03-02 | William Barry Bryan | Gas turbine engine having radially-split inlet guide vanes |
GB201703423D0 (en) * | 2017-03-03 | 2017-04-19 | Rolls Royce Plc | Gas turbine engine vanes |
-
2018
- 2018-06-28 FR FR1855840A patent/FR3083260B1/fr active Active
-
2019
- 2019-06-27 US US16/455,126 patent/US11319899B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3083260A1 (fr) | 2020-01-03 |
US11319899B2 (en) | 2022-05-03 |
US20200332743A1 (en) | 2020-10-22 |
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