GB797874A - Variable configuration discharge nozzles for propulsive jets - Google Patents
Variable configuration discharge nozzles for propulsive jetsInfo
- Publication number
- GB797874A GB797874A GB609855A GB609855A GB797874A GB 797874 A GB797874 A GB 797874A GB 609855 A GB609855 A GB 609855A GB 609855 A GB609855 A GB 609855A GB 797874 A GB797874 A GB 797874A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzle
- wall elements
- ring
- spigots
- linkage
- 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
- F02K1/10—Varying effective area of jet pipe or nozzle by distorting the jet pipe or nozzle
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Excavating Of Shafts Or Tunnels (AREA)
Abstract
797,874. Jet propulsion nozzles. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Feb. 20, 1956 [March 1, 1955], No. 6098/55. Class 110 (3). A variable area jet propulsion nozzle defined by number of wall elements extending longitudinally in the direction of fluid flow and flexible in a radial plane containing the longitudinal axis of the nozzle has means to vary the nozzle flow area in one or more planes consisting of connecting members extending between successive pairs of adjacent wall members or bands attached to the wall members to locate each in the radial direction, the circumferential length or disposition of which may be varied. The nozzle, Fig. 1, consists of an outer row of peripherally consecutive wall elements 1 and a similar inner row of wall elements 2. The upstream ends 3 of the wall elements of a row are of arcuate section and abut each other to form a ring. The abutments of the outer ring are staggered with respect to the abutments of the inner ring. The rings are in radial abutment with one another or with an intermediate ring and are spigotted and rigidly attached to a recess in the downstream end of the duct 4. For the remainder of their length the wall elements are of arcuate cross-section with outwardly projecting flanges 5. The flanges 5 of the inner ring members carry sealing strips 6. At a number of intermediate transverse planes A, B, C, E, F each wall element has a partspherical spigot 7 which forms a common pivot for a pair of crossed links 8. The ends of the links 8 associated with each adjacent pair of spigots are jointed by pins 9 to form a linkage of lattice or lazy-tongs form. Pivoting of the links 8 alters the peripheral length of the linkage and so varies the diameter of the nozzle. Each linkage is activated by one or more hydraulic jacks connected to the pins 9. By appropriate adjustment of the degree and sense of variation of the diameters of the linkages the nozzle may be modified from the convergent arrangement shown to a convergent-divergent arrangement. In the plane D the nozzle diameter remains constant. The supporting ring 11 to which the wall elements are rigidly attached is supported in mounting blocks 13 by opposed spigots 12. The wall elements may be attached to the ring 11 by spherical spigots, in which case the ring 11 is made in two parts fastened together and recessed to form the spherical seatings for the spigots. The moment of inertia of the wall elements may be reduced at 14. The hydraulic jacks 10 for actuating the linkage consist of a central cylinder block 15 with an integral piston 16, a double-ended piston 17 and two end cylinder blocks 18 united by tie bars. The cylinder block 15 and piston 17 have bosses 20, 21 to which are attached the pins 9. Connections 22, 23 are supplied with pressure fluid to vary the position of the jack. Adjustable stops limiting the outward and inward movements of the jack may be provided. The connections 22, 23 of the jacks may be connected to common manifolds to give a particular nozzle configuration when fluid is supplied to one or other of the manifolds.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB609855A GB797874A (en) | 1955-03-01 | 1955-03-01 | Variable configuration discharge nozzles for propulsive jets |
FR1147529D FR1147529A (en) | 1955-03-01 | 1956-02-29 | Improvements to the discharge nozzles of thruster jets |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB609855A GB797874A (en) | 1955-03-01 | 1955-03-01 | Variable configuration discharge nozzles for propulsive jets |
Publications (1)
Publication Number | Publication Date |
---|---|
GB797874A true GB797874A (en) | 1958-07-09 |
Family
ID=9808336
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB609855A Expired GB797874A (en) | 1955-03-01 | 1955-03-01 | Variable configuration discharge nozzles for propulsive jets |
Country Status (2)
Country | Link |
---|---|
FR (1) | FR1147529A (en) |
GB (1) | GB797874A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3759447A (en) * | 1970-06-08 | 1973-09-18 | Messerschmitt Boelkow Blohm | Flexible tubing for the conducting of hot jet engine gases |
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 |
EP2500581A3 (en) * | 2011-03-18 | 2014-06-11 | Daejoo Machinery Co., Ltd. | Variable throat device for air compressor |
-
1955
- 1955-03-01 GB GB609855A patent/GB797874A/en not_active Expired
-
1956
- 1956-02-29 FR FR1147529D patent/FR1147529A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3759447A (en) * | 1970-06-08 | 1973-09-18 | Messerschmitt Boelkow Blohm | Flexible tubing for the conducting of hot jet engine gases |
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 |
EP2500581A3 (en) * | 2011-03-18 | 2014-06-11 | Daejoo Machinery Co., Ltd. | Variable throat device for air compressor |
Also Published As
Publication number | Publication date |
---|---|
FR1147529A (en) | 1957-11-26 |
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