GB1418077A - Variable-geometry convergent-divergent nozzles for jet propulsion engines - Google Patents
Variable-geometry convergent-divergent nozzles for jet propulsion enginesInfo
- Publication number
- GB1418077A GB1418077A GB1833573A GB1833573A GB1418077A GB 1418077 A GB1418077 A GB 1418077A GB 1833573 A GB1833573 A GB 1833573A GB 1833573 A GB1833573 A GB 1833573A GB 1418077 A GB1418077 A GB 1418077A
- Authority
- GB
- United Kingdom
- Prior art keywords
- convergent
- flaps
- point
- flap
- link
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1223—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series
-
- 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
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/323—Arrangement of components according to their shape convergent
-
- 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
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/324—Arrangement of components according to their shape divergent
-
- 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
- F05D2250/90—Variable geometry
-
- 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
- F05D2260/50—Kinematic linkage, i.e. transmission of position
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Transmission Devices (AREA)
Abstract
1418077 Jets propulsion nozzles - variable geometry SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 17 April 1973 [17 April 1972] 18335/73 Heading F1J The invention relates to a variable geometry convergent-divergent propulsion nozzle for a jet engine in which it is possible to vary simultaneously the nozzle throat section and the outlet section. The nozzle assembly shown in Fig. 1 comprises a jet pipe 4, 10 at the downstream end of which is pivotally mounted at 21 a plurality of convergent nozzle flaps 20 at the downstream end of each of which is pivotally mounted at 31 a divergent flap 30, each convergent flap and its associated divergent flap constituting a pair of flaps. Associated with each pair of flaps 20, 30 is fixed structure comprising a pair of circumferentially-spaced members 14a, 14b to which the convergent flaps 20 are pivotally mounted at the points 21, each convergent flap being integrally formed with a pair of links 20x to which the piston-rod 24, 22 of a hydraulic actuator 25 is pivotally connected at the point 23. The divergent flap 30 is integrally formed with a pair of links 30x to which is pivotally connected at the point 33 one end 32c of a link 32 which is bifurcated at its other end 32a, 32b, the ends 32a, 32b being pivotally mounted at a point 34 to the fixed members 14a, 14b. As the convergent flap 20 pivots about the point 21 so the pivot point 33 of the divergent flap 30 pivots about the point 34. In a second embodiment Fig. 5, bifurcated link 132 connecting the pivotal point 33 of the pair of links 30x integral with the divergent flap 30 and the pivotal point 34 on the fixed structure 14a, 14b is of extensible form. The forked portion of the link is indicated at 132a, 132b and the stem at 132c, the stem comprising a cylinder 132cy and a piston 132cx the piston and cylinder being loaded by a spring so that the stop 150 on the piston-rod is in abutment with the stop 151 on the cylinder. Stop members 160, 161 are provided on the convergent and divergent flap members 20, 30. In the maximum area position Fig. 5 the link 132 is of minimum length with the stops 150, 151 in abutment, and the stops 160, 161 on the flaps are spaced apart. As the convergent flap is pivoted inwardly about point 21, the link 132 remains of minimum length until the stops 160, 161 on the flaps come into abutment. Further inward movement of the flaps causes the link 132 to extend but the flaps 20, 30 do not move relatively to each other.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR7213397A FR2180440B1 (en) | 1972-04-17 | 1972-04-17 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1418077A true GB1418077A (en) | 1975-12-17 |
Family
ID=9096965
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1833573A Expired GB1418077A (en) | 1972-04-17 | 1973-04-17 | Variable-geometry convergent-divergent nozzles for jet propulsion engines |
Country Status (4)
Country | Link |
---|---|
US (1) | US3807637A (en) |
DE (1) | DE2318607C3 (en) |
FR (1) | FR2180440B1 (en) |
GB (1) | GB1418077A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2456386A (en) * | 1985-04-17 | 2009-07-22 | Snecma | Nozzle assembly for a turbo-jet engine |
US12018628B2 (en) | 2020-11-09 | 2024-06-25 | Safran Aircraft Engines | Turbojet engine rear part comprising a nozzle having flaps comprising levers that are movable by means of upstream and downstream bearing walls |
Families Citing this family (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4052007A (en) * | 1975-11-25 | 1977-10-04 | United Technologies Corporation | Flap-type two-dimensional nozzle |
US4176792A (en) * | 1977-07-11 | 1979-12-04 | General Electric Company | Variable area exhaust nozzle |
FR2714421B1 (en) * | 1980-01-14 | 1996-03-01 | Snecma | Nozzle comprising an adjustable convergent-diverging nozzle, in particular for a jet engine. |
FR2474592A1 (en) * | 1980-01-25 | 1981-07-31 | Snecma | TURBOREACTOR TUBE DEVICE |
FR2724977B1 (en) * | 1980-12-30 | 1996-12-13 | Snecma | CONVERGENT-DIVERGENT NOZZLE ESPECIALLY FOR A TURBOREACTOR |
FR2723145B1 (en) * | 1981-11-24 | 1996-12-13 | Snecma | CONVERGENT-DIVERGENT NOZZLE, PARTICULARLY FOR A TURBOREACTOR |
FR2714422A1 (en) * | 1983-01-13 | 1995-06-30 | Snecma | Convergent-divergent nozzle, particularly for jet engines |
US5140809A (en) * | 1990-02-12 | 1992-08-25 | General Electric Company | Exhaust nozzle idle thrust spoiling method |
US5235808A (en) * | 1990-02-12 | 1993-08-17 | General Electric Company | Exhaust nozzle including idle thrust spoiling |
ES2105929B1 (en) * | 1993-11-23 | 1998-05-01 | Sener Ing & Sist | ADJUSTABLE AXISIMETRIC NOZZLE OF VARIABLE GEOMETRY FOR GAS TURBINE PROPELLERS. |
ES2194171T3 (en) * | 1997-01-23 | 2003-11-16 | Turbo Propulsores Ind | DIVERGENT PETAL FOR A GAS TURBINE ENGINE NOZZLE. |
US8020386B2 (en) * | 2007-08-21 | 2011-09-20 | United Technologies Corporation | Rollertrack pivoting axi-nozzle |
US7874160B2 (en) * | 2007-08-21 | 2011-01-25 | United Technologies Corporation | Nozzle-area ratio float bias |
US8443931B2 (en) * | 2011-04-06 | 2013-05-21 | Lockheed Martin Corporation | Noise reduction of supersonic jet engines |
GB201314667D0 (en) * | 2013-08-16 | 2013-10-02 | Rolls Royce Plc | A panel attachment system |
US9856956B2 (en) * | 2015-01-20 | 2018-01-02 | United Technologies Corporation | Rod-and-bracket connector system for securing a pivoting member to a guide anchor moveably secured within a guide track |
GB2588652A (en) | 2019-10-31 | 2021-05-05 | Rolls Royce Plc | An exhaust nozzle |
GB2588651A (en) * | 2019-10-31 | 2021-05-05 | Rolls Royce Plc | An exhaust nozzle |
GB2588653A (en) | 2019-10-31 | 2021-05-05 | Rolls Royce Plc | An exhaust nozzle |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1329959A (en) * | 1962-07-27 | 1963-06-14 | Rolls Royce | Convergent-Divergent Jet Jet Engines |
FR1537247A (en) * | 1967-08-18 | 1968-08-23 | United Aircraft Corp | Free-floating articulated ejection nozzle |
-
1972
- 1972-04-17 FR FR7213397A patent/FR2180440B1/fr not_active Expired
-
1973
- 1973-04-13 DE DE2318607A patent/DE2318607C3/en not_active Expired
- 1973-04-16 US US00351578A patent/US3807637A/en not_active Expired - Lifetime
- 1973-04-17 GB GB1833573A patent/GB1418077A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2456386A (en) * | 1985-04-17 | 2009-07-22 | Snecma | Nozzle assembly for a turbo-jet engine |
GB2456386B (en) * | 1985-04-17 | 2010-01-13 | Snecma | Jet Nozzle |
US12018628B2 (en) | 2020-11-09 | 2024-06-25 | Safran Aircraft Engines | Turbojet engine rear part comprising a nozzle having flaps comprising levers that are movable by means of upstream and downstream bearing walls |
Also Published As
Publication number | Publication date |
---|---|
DE2318607C3 (en) | 1978-03-16 |
FR2180440B1 (en) | 1976-06-11 |
DE2318607B2 (en) | 1977-08-04 |
DE2318607A1 (en) | 1973-11-08 |
US3807637A (en) | 1974-04-30 |
FR2180440A1 (en) | 1973-11-30 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PCNP | Patent ceased through non-payment of renewal fee |