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81. 发明专利

FR2648869A1 Turbojet thrust reverser with doors equipped with a stream profile plate 未知
公开(公告)号：FR2648869A1
公开(公告)日：1990-12-28
申请号：FR9007437
申请日：1990-06-14
申请人： HISPANO SUIZA SA
发明人： DUBOIS CLAUDE ACHILLE GERMAIN
IPC分类号： F02K1/70 , F02K1/64
摘要： A by-pass turbojet thrust reverser includes tilting doors 7 which, in the closed position, are incorporated into the outer wall of the annular passage of the by-pass flow and is capable, in the open position, of diverting the said by-pass flow. A plate 20 forming a door flap is associated in the front of the door 7, on the radially internal side. Connection means with a connecting rod 22, 23, 30 cause the said plate 20 to pivot in order to bring it into a position which, in direct jet, is coincident with the theoretical aerodynamic delimiting surface 14 of the profile of the by-stream and, in thrust reversal mode, into an optimum position providing the reversal performance.

82. 发明专利

DE3379798D1 TRANSLATING JET ENGINE NOZZLE PLUG 未知
公开(公告)号：DE3379798D1
公开(公告)日：1989-06-08
申请号：DE3379798
申请日：1983-10-27
申请人： BOEING CO
发明人： THORNOCK RUSSEL
IPC分类号： F02K1/08 , F02K1/64

83. 发明专利

DE2645349B2 未知
公开(公告)号：DE2645349B2
公开(公告)日：1978-05-18
申请号：DE2645349
申请日：1976-10-07
申请人： ROLLS-ROYCE LTD., LONDON
发明人： SMITH, THOMAS ERIC, ILKESTON, DERBY (GROSSBRITANNIEN)
IPC分类号： B64D33/00 , F02K1/64 , B64C15/06
摘要： Gas turbine engine power plants sometimes are provided with thrust reversing equipment, the outlet of which is close to the power plant air intake. Such arrangements create re-ingestion problems. There is described herein an apparatus which either maintains the upstream portion of reversed flow in a given position with respect to the plane of the air intake or alternatively destroys the reversed flow entirely.

84. 发明专利

GB1388406A GAS TURBINE DUCTED FAN ENGINES 未知
公开(公告)号：GB1388406A
公开(公告)日：1975-03-26
申请号：GB5818571
申请日：1971-12-15
申请人： ROLLS ROYCE
IPC分类号： B64D27/16 , F02K1/64 , B64C15/06 , F02K1/20
摘要： 1388406 Deflecting propulsion jets ROLLSROYCE (1971) Ltd 9 Jan 1973 [15 Dec 1971] 58185/71 Heading B7G In a ducted fan engine comprising a core engine 12 driving a front fan 14 enclosed within a cowl 18, the cowl is attached to the core engine by airflow straightener vanes, some of which are adjustable about axes 30 to blank off the duet. A movable portion 22 of the cowl is linked to the adjustable vanes and when displaced exposes an annular aperture 52 through which the fan air is diverted by a cascade of vanes 26. The cowl comprises front and rear fixed portions 20, 24 and the forwardly movable portion 22. Each duct-closing vane 28 is connected by a lever to a ring 32 which is rotated within the cowl by a bellcrank lever 44 actuated through rod 42 and a further bellcrank 40 which co-operates via pin 38 with a channel-section arcuate track 36 mounted on the inner surface of portion 22. Translational movement of portion 22 by a screw and nut mechanism 48, 50 exposes the annular aperture 52 containing deflector vans 26 with subsequent rotation to a duct-closing position of vanes 28. In a further embodiment (Fig. 6, not shown) the cowl is formed by a fixed aft portion and a translatable forward portion.

85. 发明专利

DE1526815A1 未知
公开(公告)号：DE1526815A1
公开(公告)日：1971-01-28
申请号：DE1526815
申请日：1965-11-20
申请人： GEN ELECTRIC
发明人： JOSEPH FISHER LEE , FERGUSON DIBBLE CHARLES GORDON
IPC分类号： F01D5/02 , F02C7/20 , F02K1/64 , F02K3/06 , B64B1/24

86. 发明专利

GB1197711A Improvements in Turbofan Type Engine. 未知
公开(公告)号：GB1197711A
公开(公告)日：1970-07-08
申请号：GB4822865
申请日：1965-11-12
申请人： GEN ELECTRIC
IPC分类号： F01D5/02 , F02C7/20 , F02K1/64 , F02K3/06
摘要： 1,197,711. Gas turbine ducted fan engines. GENERAL ELECTRIC CO. Nov. 12, 1965 [Dec. 2, 1964 (2)], No.48228/65. Heading F1J. A front fan jet engine has an air inlet, an axial-flow compressor, a combustion chamber or chambers, a turbine driven by gases from the combustion chamber(s) for driving the compressor and an exhaust nozzle, the air inlet being divided into inner and outer concentric annular passages by a flow splitter and the compressor comprising a first wheel secured to a shaft and having a plurality of compressor blades rotatable in the inner passage and a second wheel secured to the shaft downstream of the first and having a plurality of compressor blades rotatable in the inner and outer passages. The compressor 10 shown in Fig. 2 comprises a first wheel 64 from the hub 65 of which project a plurality of radially extending rotor blades 66. A hub fairing 67 provides a smooth entry into the wheel 64 and the peripheral surface 68 of the hub 65 between the blades 66 forms a smooth continuation of the fairing 67. The wheel 64 is connected by a cylindrical spacer 69 to a second wheel 70 having a hub 72 from which project a plurality of rotor blades 74, the peripheral surface 73 of the hub 72 between the blades 74 continuing the smooth inner flow path boundary wall of the compressor. A casing surrounds the wheels 64, 70 to define an annular flow passage 14 and includes a first plurality of stator vanes 78 intermediate the wheels 64, 70 and a second plurality of stator vanes 80 downstream of the wheel 70. Shrouds 84, 85 are provided at the inner ends of the stator vanes 78, 80, respectively, and are shaped to form a continuation of the peripheral surfaces 68, 73, respectively. Each blade 74 comprises an inner portion 74a and an outer portion 74b separated by a shroud member 88 which forms part of a contoured flowsplitter 90 dividing the annular flow passage 14 into an inner annulus 14a and an outer annulus 14b. In addition to the shroud member 88, the flow-splitter 90 comprises a forwardly-extending portion 92, having a first section 92a affixed to the stator vanes 78 and second section 92b affixed to the rotor blades 66 extending forwardly of the first, and a rearwardlyextending member 94 affixed to the stator vanes 80. The outer annulus 14b is designed to pass approximately the same mass flow in a single rotor stage comprising rotor blade means 74b as the inner annulus 14a , wherein the inner portion of a second rotor stage comprising rotor blade means 74a is supercharged by a first rotor stage comprising rotor blade means 66. The outer wall 94a of the member 94 and the rear portion of the outer surface 88a of the member 88 are sloped to provide, in combination with a sloping portion 18b of the inner surface 18 of the casing, a convergent flow passage such that the slope of the blade tips 74c of the outer portions 74b of the rotor blades 74 is minimized.

87. 发明专利

GB1116779A Gas turbine jet propulsion engine 未知
公开(公告)号：GB1116779A
公开(公告)日：1968-06-12
申请号：GB5252066
申请日：1966-11-23
申请人： ROLLS ROYCE
发明人： WRIGLEY BRIAN
IPC分类号： F02K1/56 , F02K1/64 , F02K1/72
摘要： 1,116,779. Deflecting propulsive gases. ROLLS-ROYCE Ltd. 23 Nov., 1966, No. 52520/66. Heading B7G. [Also in Division F1] A gas turbine jet propulsion engine comprises a main flow duct in which are disposed compressor means, combustion equipment, turbine means and an exhaust duct, a second annular flow duct which surrounds the main duct and is adapted to receive air under pressure from a rotor stage of the engine, the turbine means being drivingly connected to the rotor stage. Thrust spoiling means are. located in the exhaust duct and are movable between an inoperative position in which the flow of jet gases through the exhaust duct is substantially unaffected, and a thrust spoiling position in which the pressure in the exhaust duct is reduced so as to increase the speed of rotation of the rotor stage. A thrust reverser is provided at the downstream end of the second flow duct. The engine shown comprises a fan 14, a main duct 11 in which are disposed a compressor 15, combustion equipment 15a, turbine 16 and jet pipe 17, and a fan duct 12 surrounding the main duct, the fan supplying air to the main duct and to the fan duct. The downstream end portion 28 of the inner casing 18 is axially movable by means of actuators 29 between the positions shown in. full lines and in broken lines. In the latter position an opening 32 is formed in the duct wall and the turbine exhaust gases discharge laterally through the opening, this being a thrust spoiling arrangement, The pressure downstream of the turbine is thereby reduced so that the speed of the turbine and thus of the fan 14 driven thereby is increased. A thrust reversing device 24 is disposed at the downstream end of the outer casing 19 and is moved from the retracted position shown in full lines to the operative position shown in broken lines by means of actuators 25 simultaneously with the movement of the casing portion 28 to the thrust spoiling position. Thus the flow of air through the fan duct 12 is increased when the thrust reverser is operative so increasing the braking effect.

88. 发明专利

BE683498A 未知
公开(公告)号：BE683498A
公开(公告)日：1966-12-01
申请号：BE683498D
申请日：1966-06-30
IPC分类号： F02K1/64

89. 发明专利

DE970090C 未知
公开(公告)号：DE970090C
公开(公告)日：1958-08-21
申请号：DES0026672
申请日：1952-01-01
申请人： SNECMA
发明人： KADOSCH MARCEL , FOLL JEAN LE , MAUNOURY FRANCOIS MARIE LOUIS , BERTIN JEAN
IPC分类号： F01D5/14 , F01D17/12 , F02C7/04 , F02K1/28 , F02K1/32 , F02K1/64 , F02K7/02 , F02K7/04 , F02K7/067

90. 发明专利

GB767513A Method of and means for the control of a flow, and their various applications 未知
公开(公告)号：GB767513A
公开(公告)日：1957-02-06
申请号：GB3444153
申请日：1953-12-10
申请人： SNECMA
发明人： BERTIN JEAN HENRI , KADOSCH MARCEL , GELIN PAUL
IPC分类号： F01D5/14 , F01D17/12 , F02C7/04 , F02K1/28 , F02K1/32 , F02K1/64 , F02K7/02 , F02K7/04 , F02K7/067
摘要： 767,513. Controlling Jet propelled aircraft. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Dec. 10, 1953 [Dec. 12, 1952], No. 34441/53. Class 4. [Also in Group XXVI] A jet propulsion nozzle is provided with means for varying the area of the nozzle by gaseous restriction and a device for deflecting the jet. The jet propulsion nozzle 1 is extended by a convex surface 20 which is curved towards the exterior at 20a and by a set of annular vanes 21. A movable obstacle 22 is moved into the dotted line position when it is desired to deflect the jet. The area of the jet is controlled by an auxiliary jet of air from the slot 10. To supply ambient air to the rear of the auxiliary jet the convex surface 20 is spaced from the outlet end of the nozzle. The amount of restriction of the jet is controlled by varying the pressure or flow or both of the auxiliary fluid by means of a valve 8. Specifications 660,144 [Group XXIX], 691,948 and 745,630 [Group XXVI], are referred to.

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