FR3083207B1 - Ensemble propulsif pour un aeronef comprenant un rotor non carene - Google Patents
Ensemble propulsif pour un aeronef comprenant un rotor non carene Download PDFInfo
- Publication number
- FR3083207B1 FR3083207B1 FR1855836A FR1855836A FR3083207B1 FR 3083207 B1 FR3083207 B1 FR 3083207B1 FR 1855836 A FR1855836 A FR 1855836A FR 1855836 A FR1855836 A FR 1855836A FR 3083207 B1 FR3083207 B1 FR 3083207B1
- Authority
- FR
- France
- Prior art keywords
- rotor
- hooded
- pylon
- aircraft including
- aircraft
- 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
- 238000011144 upstream manufacturing Methods 0.000 abstract 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B64D27/40—
-
- 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
-
- 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
-
- 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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
- B64C11/04—Blade mountings
- B64C11/06—Blade mountings for variable-pitch blades
-
- 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
- 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
-
- 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 ensemble propulsif pour un aéronef, comportant un moteur (1) équipé d'au moins une hélice (5) de rotor non carénée et d'une rangée annulaire (6) d'aubes de stator configurées pour redresser au moins une partie d'un flux (F) de gaz traversant ladite hélice (5), l'ensemble propulsif comportant en outre un pylône (2) de fixation du moteur (1) à l'aéronef, ce pylône (2) s'étendant en aval ou en amont de ladite rangée annulaire (6) d'aubes, caractérisé en ce que ledit pylône (2) est relié physiquement à l'une desdites aubes (2b) de stator de façon à former un ensemble aérodynamique unique.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1855836A FR3083207B1 (fr) | 2018-06-28 | 2018-06-28 | Ensemble propulsif pour un aeronef comprenant un rotor non carene |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1855836A FR3083207B1 (fr) | 2018-06-28 | 2018-06-28 | Ensemble propulsif pour un aeronef comprenant un rotor non carene |
FR1855836 | 2018-06-28 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3083207A1 FR3083207A1 (fr) | 2020-01-03 |
FR3083207B1 true FR3083207B1 (fr) | 2020-12-25 |
Family
ID=63312137
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1855836A Active FR3083207B1 (fr) | 2018-06-28 | 2018-06-28 | Ensemble propulsif pour un aeronef comprenant un rotor non carene |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3083207B1 (fr) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3112809B1 (fr) * | 2020-07-23 | 2022-07-29 | Safran Aircraft Engines | Module de turbomachine equipe d’une helice et d’aubes de stator supportees par des moyens de maintien et turbomachine correspondante |
FR3125797A1 (fr) | 2021-07-29 | 2023-02-03 | Safran Aircraft Engines | Propulseur pour un aéronef |
FR3126733A1 (fr) | 2021-09-06 | 2023-03-10 | Safran Aircraft Engines | Turbomachine a double flux a bec variable en position |
FR3130320B1 (fr) * | 2021-12-13 | 2023-11-03 | Safran Aircraft Engines | Turbomachine non carénée comprenant des aubes de stator présentant des cordes différentes |
FR3130319B1 (fr) | 2021-12-13 | 2023-11-03 | Safran Aircraft Engines | Turbomachine non carénée comprenant des aubes de stator présentant des cordes différentes |
FR3131732B1 (fr) | 2022-01-10 | 2024-03-15 | Safran Aircraft Engines | Ensemble propulsif a helice pour aeronef, comprenant une aube de stator integree a une partie d’extremite amont d’un mat d’accrochage de hauteur reduite |
FR3136448A1 (fr) * | 2022-06-08 | 2023-12-15 | Safran Aircraft Engines | Ensemble de production de poussée non caréné comprenant un redresseur chargé en pied d’aube |
FR3137369A1 (fr) * | 2022-06-29 | 2024-01-05 | Safran Aircraft Engines | Intégration d’une aube de stator à un pylône de fixation |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4486146A (en) * | 1980-08-08 | 1984-12-04 | British Aerospace Public Limited Company | Aircraft propulsion means |
US10704410B2 (en) * | 2012-10-23 | 2020-07-07 | General Electric Company | Unducted thrust producing system architecture |
PL412269A1 (pl) * | 2015-05-11 | 2016-11-21 | General Electric Company | Zanurzony wlot kanału przepływu między łopatką wirnika i łopatką kierowniczą dla turbiny gazowej z otwartym wentylatorem |
FR3050721B1 (fr) * | 2016-04-28 | 2018-04-13 | Airbus Operations | Ensemble moteur pour aeronef comprenant un bord d'attaque de mat integre a une rangee annulaire d'aubes directrices de sortie non carenees |
ES2835263T3 (es) * | 2016-12-20 | 2021-06-22 | Airbus Operations Sl | Sistema de propulsión rotativo de una aeronave |
-
2018
- 2018-06-28 FR FR1855836A patent/FR3083207B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
FR3083207A1 (fr) | 2020-01-03 |
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Legal Events
Date | Code | Title | Description |
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PLFP | Fee payment |
Year of fee payment: 2 |
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PLSC | Publication of the preliminary search report |
Effective date: 20200103 |
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PLFP | Fee payment |
Year of fee payment: 3 |
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PLFP | Fee payment |
Year of fee payment: 4 |
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PLFP | Fee payment |
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PLFP | Fee payment |
Year of fee payment: 6 |