FR3054203B1 - Nacelle pour turboreacteur double flux a soufflante a calage variable et ensemble propulsif comportant une telle nacelle - Google Patents
Nacelle pour turboreacteur double flux a soufflante a calage variable et ensemble propulsif comportant une telle nacelle Download PDFInfo
- Publication number
- FR3054203B1 FR3054203B1 FR1656964A FR1656964A FR3054203B1 FR 3054203 B1 FR3054203 B1 FR 3054203B1 FR 1656964 A FR1656964 A FR 1656964A FR 1656964 A FR1656964 A FR 1656964A FR 3054203 B1 FR3054203 B1 FR 3054203B1
- Authority
- FR
- France
- Prior art keywords
- nacelle
- external structure
- rear section
- internal structure
- flow
- 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
- 230000001141 propulsive effect Effects 0.000 title 1
- 238000012423 maintenance Methods 0.000 abstract 2
- 210000003462 vein Anatomy 0.000 abstract 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/08—Inspection panels for power plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/56—Reversing jet main flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
- F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
-
- 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
- F05D2230/72—Maintenance
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
L'invention se rapporte à une nacelle (3) de turboréacteur à double flux à soufflante à calage variable, la nacelle comportant une section avant (300) destinée à entourer la soufflante du turboréacteur, et une section arrière (310), la section arrière (310) comportant une structure interne (314) destinée à entourer le corps primaire du turboréacteur, la structure interne (314) définissant avec une structure externe (312) de la section arrière (310) une veine secondaire pour l'écoulement d'un flux d'air, la structure externe (312) de la section arrière (310) étant mobile en translation par rapport à la section avant (300), entre une position avancée, dans laquelle la structure externe (312) assure la continuité aérodynamique avec la section avant (300), et une position reculée, dans laquelle la structure externe (312) ouvre un passage vers la veine secondaire, la structure externe (312) comportant un élément tubulaire (318) apte à prendre une position de maintenance par rotation autour d'un axe (316) perpendiculaire à un axe longitudinal de la nacelle, l'élément tubulaire (318) libérant en position de maintenance un accès à la structure interne (314).
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1656964A FR3054203B1 (fr) | 2016-07-21 | 2016-07-21 | Nacelle pour turboreacteur double flux a soufflante a calage variable et ensemble propulsif comportant une telle nacelle |
PCT/FR2017/051987 WO2018015672A1 (fr) | 2016-07-21 | 2017-07-20 | Nacelle pour turboréacteur double flux à soufflante à calage variable et ensemble propulsif comportant une telle nacelle |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1656964A FR3054203B1 (fr) | 2016-07-21 | 2016-07-21 | Nacelle pour turboreacteur double flux a soufflante a calage variable et ensemble propulsif comportant une telle nacelle |
FR1656964 | 2016-07-21 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3054203A1 FR3054203A1 (fr) | 2018-01-26 |
FR3054203B1 true FR3054203B1 (fr) | 2020-05-22 |
Family
ID=56990619
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1656964A Active FR3054203B1 (fr) | 2016-07-21 | 2016-07-21 | Nacelle pour turboreacteur double flux a soufflante a calage variable et ensemble propulsif comportant une telle nacelle |
Country Status (2)
Country | Link |
---|---|
FR (1) | FR3054203B1 (fr) |
WO (1) | WO2018015672A1 (fr) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102015206093A1 (de) * | 2015-04-02 | 2016-10-06 | Rolls-Royce Deutschland Ltd & Co Kg | Triebwerksverkleidung einer Fluggasturbine |
GB201816864D0 (en) | 2018-10-16 | 2018-11-28 | Cambridge Mechatronics Ltd | Electromagnetic screening of an image sensor from an actuator in a camera |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4506850A (en) * | 1983-01-04 | 1985-03-26 | The Boeing Company | Engine installation for aircraft |
US4922711A (en) * | 1988-06-10 | 1990-05-08 | The Boeing Company | Thrust reversing system for high bypass fan engines |
US5090196A (en) | 1989-07-21 | 1992-02-25 | The Boeing Company | Ducted fan type gas turbine engine power plants |
US9435293B2 (en) * | 2013-02-22 | 2016-09-06 | United Technologies Corporation | Full ring sliding nacelle with thrust reverser |
US10113508B2 (en) | 2014-11-21 | 2018-10-30 | General Electric Company | Gas turbine engine and method of assembling the same |
-
2016
- 2016-07-21 FR FR1656964A patent/FR3054203B1/fr active Active
-
2017
- 2017-07-20 WO PCT/FR2017/051987 patent/WO2018015672A1/fr active Application Filing
Also Published As
Publication number | Publication date |
---|---|
WO2018015672A1 (fr) | 2018-01-25 |
FR3054203A1 (fr) | 2018-01-26 |
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