FR3108950B1 - Turbomachine a double flux pour un aeronef - Google Patents
Turbomachine a double flux pour un aeronef Download PDFInfo
- Publication number
- FR3108950B1 FR3108950B1 FR2003246A FR2003246A FR3108950B1 FR 3108950 B1 FR3108950 B1 FR 3108950B1 FR 2003246 A FR2003246 A FR 2003246A FR 2003246 A FR2003246 A FR 2003246A FR 3108950 B1 FR3108950 B1 FR 3108950B1
- Authority
- FR
- France
- Prior art keywords
- flow
- gas generator
- microgrooves
- aircraft
- turbomachine
- 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
- 238000000926 separation method Methods 0.000 abstract 1
- 238000011144 upstream manufacturing Methods 0.000 abstract 1
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
- F01D9/02—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
-
- 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
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- 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
- F02K3/06—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 with front fan
-
- 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
- F05D2230/00—Manufacture
- F05D2230/80—Repairing, retrofitting or upgrading methods
-
- 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)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Turbomachine (1) à double flux pour un aéronef, cette turbomachine comportant un générateur de gaz et une soufflante (3) montée en amont du générateur de gaz et configurée pour générer un flux d’entrée d’air (2), ce flux d’entrée d’air étant destiné à être divisé par un bec de séparation annulaire (4) en un flux primaire (21) qui alimente le générateur de gaz et en un flux secondaire (22) qui s’écoule sur une surface annulaire externe (7a) dudit bec et autour du générateur de gaz, caractérisée en ce que ladite surface comprend des microrainures (9) de guidage du flux secondaire, ces microrainures étant séparées les unes des autres par des crêtes espacées les unes des autres d’une distance S inférieure ou égale à 50 micromètres, lesdites microrainures ayant une profondeur (H) comprise entre 0,3.S et 1,2.S. Figure pour l’abrégé : Figure 2
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2003246A FR3108950B1 (fr) | 2020-04-01 | 2020-04-01 | Turbomachine a double flux pour un aeronef |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2003246 | 2020-04-01 | ||
FR2003246A FR3108950B1 (fr) | 2020-04-01 | 2020-04-01 | Turbomachine a double flux pour un aeronef |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3108950A1 FR3108950A1 (fr) | 2021-10-08 |
FR3108950B1 true FR3108950B1 (fr) | 2022-03-11 |
Family
ID=70978196
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR2003246A Active FR3108950B1 (fr) | 2020-04-01 | 2020-04-01 | Turbomachine a double flux pour un aeronef |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3108950B1 (fr) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8460779B2 (en) * | 2011-03-30 | 2013-06-11 | General Electric Company | Microstructures for reducing noise of a fluid dynamic structure |
BE1024081B1 (fr) * | 2015-03-20 | 2017-11-13 | Safran Aero Boosters S.A. | Refroidissement de turbomachine par evaporation |
FR3053074B1 (fr) | 2016-06-28 | 2018-06-15 | Safran Aircraft Engines | Piece et procede de fabrication d'une piece a trainee reduite par riblets evolutifs |
FR3059735B1 (fr) * | 2016-12-05 | 2020-09-25 | Safran Aircraft Engines | Piece de turbomachine a surface non-axisymetrique |
FR3076540B1 (fr) * | 2018-01-08 | 2021-04-16 | Airbus Operations Sas | Element aerodynamique d'un aeronef, pourvu d'un ensemble d'elements protuberants. |
-
2020
- 2020-04-01 FR FR2003246A patent/FR3108950B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
FR3108950A1 (fr) | 2021-10-08 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
FR3084916B1 (fr) | Cone d'ejection a fixation flexible | |
JP2015063994A5 (fr) | ||
FR3078367B1 (fr) | Turbomachine comportant un echangeur de chaleur dans la veine secondaire | |
FR2959774A1 (fr) | Refroidissement par convection du silencieux d'echappement | |
EP3150917A3 (fr) | Système et procédé de combustion ayant une architecture de trajet d'écoulement annulaire | |
FR3051016B1 (fr) | Dispositif de degivrage d'un bec de separation de turbomachine aeronautique | |
BR112018072749A2 (pt) | dispositivo de entrada de fluido para uso em separadores do tipo gás/líquido | |
FR3130896B1 (fr) | Turbomachine d’aéronef | |
FR3087820B1 (fr) | Turbomachine d'aeronef equipee d'une machine electrique | |
FR3108950B1 (fr) | Turbomachine a double flux pour un aeronef | |
FR3100575B1 (fr) | Cone d’ejection a fixation flexible aerodynamique | |
WO2016099663A3 (fr) | Élément de moteur destiné à une turbine à gaz | |
FR3100845B1 (fr) | Organe de tuyère extérieur pour turbomachine | |
FR3022988B1 (fr) | Systeme de chauffage d'un flux de gaz et installation employant ledit systeme | |
FR3093530B1 (fr) | Turbomachine comportant un échangeur de chaleur formé dans une plateforme | |
FR3049652B1 (fr) | Turbomachine d'aeronef a dispositif de decharge | |
WO2017022838A1 (fr) | Soupape | |
FR3115831B1 (fr) | Bride de liaison pour turbomachine | |
FR3117172B1 (fr) | Turbomachine pour un aéronef | |
FR3030707B1 (fr) | Ensemble de transfert de chaleur pour un echangeur de chaleur | |
FR3078101B1 (fr) | Turbomachine a bec de separation de flux a profil en serrations | |
FR3078368B1 (fr) | Turbomachine comportant un echangeur de chaleur dans la veine secondaire | |
FR3050485B1 (fr) | Turbomachine a double flux | |
FR2994461B1 (fr) | Cone d'echappement biconique pour un turboreacteur d'avion civil | |
FR3081913B1 (fr) | Aube de turbomachine comportant une ailette anti-tourbillons |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20211008 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
PLFP | Fee payment |
Year of fee payment: 4 |
|
PLFP | Fee payment |
Year of fee payment: 5 |