FR2014140A1 - - Google Patents
Info
- Publication number
- FR2014140A1 FR2014140A1 FR6915489A FR6915489A FR2014140A1 FR 2014140 A1 FR2014140 A1 FR 2014140A1 FR 6915489 A FR6915489 A FR 6915489A FR 6915489 A FR6915489 A FR 6915489A FR 2014140 A1 FR2014140 A1 FR 2014140A1
- Authority
- FR
- France
- 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.)
- Withdrawn
Links
Classifications
-
- 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
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB25484/68A GB1161186A (en) | 1968-05-28 | 1968-05-28 | A Gas Turbine Ducted Fan Engine. |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| FR2014140A1 true FR2014140A1 (fr) | 1970-04-17 |
Family
ID=10228454
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR6915489A Withdrawn FR2014140A1 (fr) | 1968-05-28 | 1969-05-13 |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US3566606A (fr) |
| DE (1) | DE1926432C3 (fr) |
| FR (1) | FR2014140A1 (fr) |
| GB (1) | GB1161186A (fr) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2941675A1 (fr) * | 2009-02-02 | 2010-08-06 | Airbus France | Nacelle d'aeronef comprenant un systeme de traitement acoustique optimise. |
| WO2010086560A3 (fr) * | 2009-02-02 | 2010-11-25 | Airbus Operations Sas | Nacelle d'aeronef comprenant un systeme de traitement acoustique optimise |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3933327A (en) * | 1974-08-30 | 1976-01-20 | Rohr Industries, Inc. | Aircraft anti-icing plenum |
| US4471609A (en) * | 1982-08-23 | 1984-09-18 | The Boeing Company | Apparatus and method for minimizing engine backbone bending |
| US4860534A (en) * | 1988-08-24 | 1989-08-29 | General Motors Corporation | Inlet particle separator with anti-icing means |
| US5088277A (en) * | 1988-10-03 | 1992-02-18 | General Electric Company | Aircraft engine inlet cowl anti-icing system |
| CA2449779C (fr) * | 2001-06-06 | 2009-11-03 | Howden Power A/S | Unite de sortie d'air pour un grand ensemble ventilateur |
| GB0211800D0 (en) * | 2002-05-22 | 2002-07-03 | Short Brothers Plc | An ice protection system for aircraft structures |
| GB2416192B (en) * | 2004-07-14 | 2006-09-27 | Rolls Royce Plc | Ducted fan with containment structure |
| US8657567B2 (en) * | 2007-05-29 | 2014-02-25 | United Technologies Corporation | Nacelle compartment plenum for bleed air flow delivery system |
| US8206102B2 (en) | 2007-08-16 | 2012-06-26 | United Technologies Corporation | Attachment interface for a gas turbine engine composite duct structure |
| US9534505B2 (en) * | 2012-07-23 | 2017-01-03 | United Technologies Corporation | Integrated nacelle inlet and metallic fan containment case |
| FR3075759B1 (fr) * | 2017-12-21 | 2020-11-06 | Airbus Operations Sas | Partie anterieure de nacelle d'un ensemble propulsif d'aeronef comportant un element amortisseur |
-
1968
- 1968-05-28 GB GB25484/68A patent/GB1161186A/en not_active Expired
-
1969
- 1969-05-13 FR FR6915489A patent/FR2014140A1/fr not_active Withdrawn
- 1969-05-16 US US825308A patent/US3566606A/en not_active Expired - Lifetime
- 1969-05-23 DE DE1926432A patent/DE1926432C3/de not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2941675A1 (fr) * | 2009-02-02 | 2010-08-06 | Airbus France | Nacelle d'aeronef comprenant un systeme de traitement acoustique optimise. |
| WO2010086560A3 (fr) * | 2009-02-02 | 2010-11-25 | Airbus Operations Sas | Nacelle d'aeronef comprenant un systeme de traitement acoustique optimise |
| US9010084B2 (en) | 2009-02-02 | 2015-04-21 | Airbus Operations Sas | Aircraft nacelle including an optimised acoustic processing system |
Also Published As
| Publication number | Publication date |
|---|---|
| GB1161186A (en) | 1969-08-13 |
| DE1926432C3 (de) | 1974-07-25 |
| DE1926432A1 (de) | 1970-04-02 |
| DE1926432B2 (de) | 1974-01-03 |
| US3566606A (en) | 1971-03-02 |
Similar Documents
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| TP | Transmission of property | ||
| TP | Transmission of property | ||
| TP | Transmission of property | ||
| ST | Notification of lapse |