FR1198723A - Convergent-divergent nozzle with continuously variable geometry and neck sections - Google Patents
Convergent-divergent nozzle with continuously variable geometry and neck sectionsInfo
- Publication number
- FR1198723A FR1198723A FR1198723DA FR1198723A FR 1198723 A FR1198723 A FR 1198723A FR 1198723D A FR1198723D A FR 1198723DA FR 1198723 A FR1198723 A FR 1198723A
- Authority
- FR
- France
- Prior art keywords
- convergent
- continuously variable
- variable geometry
- divergent nozzle
- neck sections
- 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.)
- Expired
Links
Classifications
-
- 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
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/10—Varying effective area of jet pipe or nozzle by distorting the jet pipe or nozzle
-
- 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
- F05D2250/20—Three-dimensional
- F05D2250/27—Three-dimensional hyperboloid
-
- 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
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1198723T | 1958-02-03 |
Publications (1)
Publication Number | Publication Date |
---|---|
FR1198723A true FR1198723A (en) | 1959-12-09 |
Family
ID=9670167
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1198723D Expired FR1198723A (en) | 1958-02-03 | 1958-02-03 | Convergent-divergent nozzle with continuously variable geometry and neck sections |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR1198723A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1174580B (en) * | 1960-05-18 | 1964-07-23 | Gen Electric | Convergent-divergent thrust nozzle for jet engines or the like. |
EP0750107A1 (en) * | 1995-06-21 | 1996-12-27 | Volvo Aero Corporation | Exhaust nozzle flap |
WO1996041940A1 (en) * | 1995-06-12 | 1996-12-27 | Bohumil Svoboda | Supersonic jet with a controllable critical cross section |
WO2008021618A2 (en) * | 2006-08-18 | 2008-02-21 | General Electric Company | Multiple vane variable geometry nozzle |
DE102008022271A1 (en) * | 2008-05-06 | 2009-11-26 | Opara, Günther | Nozzle i.e. jet-nozzle, for e.g. gas turbine of aircraft, has one-piece tubular body including wall that forms convergent and divergent channel parts by radial contraction of cross-section dimension of nozzle |
DE102013105345A1 (en) * | 2013-05-24 | 2014-11-27 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Thrust chamber device and method for operating a thrust chamber device |
CN114687888A (en) * | 2022-04-14 | 2022-07-01 | 中国航发沈阳发动机研究所 | Binary vector spray pipe cooling structure |
-
1958
- 1958-02-03 FR FR1198723D patent/FR1198723A/en not_active Expired
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1174580B (en) * | 1960-05-18 | 1964-07-23 | Gen Electric | Convergent-divergent thrust nozzle for jet engines or the like. |
WO1996041940A1 (en) * | 1995-06-12 | 1996-12-27 | Bohumil Svoboda | Supersonic jet with a controllable critical cross section |
EP0750107A1 (en) * | 1995-06-21 | 1996-12-27 | Volvo Aero Corporation | Exhaust nozzle flap |
US5713522A (en) * | 1995-06-21 | 1998-02-03 | Volvo Aero Corporation | Exhaust nozzle flap for turbojet afterburner |
WO2008021618A2 (en) * | 2006-08-18 | 2008-02-21 | General Electric Company | Multiple vane variable geometry nozzle |
WO2008021618A3 (en) * | 2006-08-18 | 2008-07-10 | Gen Electric | Multiple vane variable geometry nozzle |
US7802432B2 (en) | 2006-08-18 | 2010-09-28 | General Electric Company | Multiple vane variable geometry nozzle |
DE102008022271A1 (en) * | 2008-05-06 | 2009-11-26 | Opara, Günther | Nozzle i.e. jet-nozzle, for e.g. gas turbine of aircraft, has one-piece tubular body including wall that forms convergent and divergent channel parts by radial contraction of cross-section dimension of nozzle |
DE102013105345A1 (en) * | 2013-05-24 | 2014-11-27 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Thrust chamber device and method for operating a thrust chamber device |
DE102013105345B4 (en) | 2013-05-24 | 2019-01-10 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Thrust chamber device and method for operating a thrust chamber device |
CN114687888A (en) * | 2022-04-14 | 2022-07-01 | 中国航发沈阳发动机研究所 | Binary vector spray pipe cooling structure |
CN114687888B (en) * | 2022-04-14 | 2024-01-30 | 中国航发沈阳发动机研究所 | Binary vector spray pipe cooling structure |
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