FR3114610B1 - Aube d’entrée d'air pour une turbomachine d’aéronef - Google Patents
Aube d’entrée d'air pour une turbomachine d’aéronef Download PDFInfo
- Publication number
- FR3114610B1 FR3114610B1 FR2009782A FR2009782A FR3114610B1 FR 3114610 B1 FR3114610 B1 FR 3114610B1 FR 2009782 A FR2009782 A FR 2009782A FR 2009782 A FR2009782 A FR 2009782A FR 3114610 B1 FR3114610 B1 FR 3114610B1
- Authority
- FR
- France
- Prior art keywords
- arm
- flow
- air intake
- aircraft turbomachine
- intake 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
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
- 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
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/02—De-icing means for engines having icing phenomena
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/148—Blades with variable camber, e.g. by ejection of fluid
-
- 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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
-
- 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
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
- F05D2220/3217—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the first stage of a compressor or a low pressure compressor
-
- 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
- F05D2250/70—Shape
- F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
L’invention concerne une aube (21a) d’entrée d’air pour une turbomachine d’aéronef, comprenant : un bras structural (22) s’étendant radialement par rapport à un axe, le bras (22) étant en outre tubulaire, comportant une cavité (34) interne configurée pour être alimentée par un flux (33) d’air de dégivrage, et un bord aval (31) comportant des ouvertures (39) d’évacuation de ce flux (33), etun volet mobile (24) monté pivotant en aval du bras (22), caractérisé en ce que le bras (22) est équipé d’un déflecteur (60) qui s’étend le long du bord aval (31) du bras (22) et qui comprend une paroi de guidage (61) configurée pour forcer ledit flux (33) d’air de dégivrage à s’écouler exclusivement sur une surface d’intrados (42) du volet (24). Figure pour l'abrégé : Figure 4
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2009782A FR3114610B1 (fr) | 2020-09-25 | 2020-09-25 | Aube d’entrée d'air pour une turbomachine d’aéronef |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2009782 | 2020-09-25 | ||
FR2009782A FR3114610B1 (fr) | 2020-09-25 | 2020-09-25 | Aube d’entrée d'air pour une turbomachine d’aéronef |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3114610A1 FR3114610A1 (fr) | 2022-04-01 |
FR3114610B1 true FR3114610B1 (fr) | 2023-03-31 |
Family
ID=74045654
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR2009782A Active FR3114610B1 (fr) | 2020-09-25 | 2020-09-25 | Aube d’entrée d'air pour une turbomachine d’aéronef |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3114610B1 (fr) |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2218746B (en) * | 1988-05-17 | 1992-06-17 | Rolls Royce Plc | A nozzle guide vane for a gas turbine engine |
US5253828A (en) * | 1992-07-17 | 1993-10-19 | The Board Of Regents Of The University Of Oklahoma | Concealable flap-actuated vortex generator |
FR2857699B1 (fr) | 2003-07-17 | 2007-06-29 | Snecma Moteurs | Dispositif de degivrage pour aube de roue directrice d'entree de turbomachine, aube dotee d'un tel dispositif de degivrage, et moteur d'aeronef equipe de telles aubes |
FR2908828B1 (fr) | 2006-11-16 | 2013-11-01 | Snecma | Dispositif d'etancheite de volet mobile de roue directrice d'entree d'une turbomachine |
CN102606312B (zh) * | 2012-04-10 | 2014-07-09 | 北京航空航天大学 | 一种用于燃气涡轮导叶分段式几何调节的冷却方法 |
FR3093136B1 (fr) * | 2019-02-27 | 2021-01-29 | Safran Aircraft Engines | Carter d’entree pour une turbomachine d’aeronef |
-
2020
- 2020-09-25 FR FR2009782A patent/FR3114610B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
FR3114610A1 (fr) | 2022-04-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP5092143B2 (ja) | 高バイパス比ターボファンジェットエンジン | |
EP0743434B1 (fr) | Dispositif pour prélever et refroidir de l'air chaud au niveau d'un moteur d'aéronef | |
EP1998025B1 (fr) | Compresseur à réinjection d'air | |
EP1748153B1 (fr) | Aube de turbomachine et turbomachine comprenant une telle aube | |
KR102296564B1 (ko) | 냉각 팬 모듈 | |
CA2975570A1 (fr) | Ensemble de redressement a performances aerodynamiques optimisees | |
JP2002540334A (ja) | タービン翼 | |
FR3082230B1 (fr) | Moteur d'aeronef a rotor non carene avec adaptation des aubes de stator | |
US20050045774A1 (en) | Laminar flow nacelle for an aircraft engine | |
FR3025843B1 (fr) | Bras de passage de servitudes pour une turbomachine | |
JP2012031855A (ja) | 燃焼タービンエンジンにおけるディフューザに関連するシステム及び装置 | |
FR3114610B1 (fr) | Aube d’entrée d'air pour une turbomachine d’aéronef | |
WO2013132190A1 (fr) | Générateurs de vortex placés dans le canal inter-aubes d'un redresseur de compresseur | |
CN112985742B (zh) | 一种平面叶栅风洞出口段背压调节装置 | |
EP3164585B1 (fr) | Dispositif de guidage d'air pour turbomachine | |
CA3174519A1 (fr) | Grille de conduit de decharge a canaux acoustiquement optimisee | |
FR3115561B1 (fr) | Aubage d’entrée d'air pour une turbomachine d’aéronef, turbomachine d'aéronef équipée d’un tel aubage d’entrée d’air et son procédé de fabrication | |
FR3093136B1 (fr) | Carter d’entree pour une turbomachine d’aeronef | |
CN204113442U (zh) | 涡轮增压器 | |
FR2979376A1 (fr) | Plaque papillon pour une enceinte d'echappement de turbine a vapeur | |
WO2022084611A1 (fr) | Turboréacteur à double flux | |
FR3107562B1 (fr) | Aube de turbomachine comportant des fentes de refroidissement de son bord de fuite équipées de perturbateurs | |
FR3116311B1 (fr) | Aube de soufflante comprenant un bouclier à densité variable | |
FR3108939B1 (fr) | Fonctionnement d’une d’écope dans une turbomachine | |
FR2914705A1 (fr) | Compresseur de turbomachine avec trous de prelevement d'air |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20220401 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
PLFP | Fee payment |
Year of fee payment: 4 |