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1. 发明专利

BE600698A Dispositif déviateur de jet 未知
公开(公告)号：BE600698A
公开(公告)日：1961-08-28
申请号：BE600698
申请日：1961-02-27
申请人： SNECMA
发明人： MOREL MAX ANDRE JACQUES , BAUGER LOUIS JULES , BARDIN ANDRE ANATOLE AUGUSTIN
IPC分类号： F02K1/32 , F02K1/72 , F02K

2. 发明专利

GB866018A A suspension device for jet propulsion units 未知
公开(公告)号：GB866018A
公开(公告)日：1961-04-26
申请号：GB3471757
申请日：1957-11-07
申请人： SNECMA
发明人： JUMELLE LOUIS FRANCOIS , MOREL MAX ANDRE JACQUES , LEGRAND PAUL JOSEPH , EICHHOLTZ KONRAD AUGUST WERNER
IPC分类号： B64D27/26 , F02C7/20 , F16C11/06
摘要： 866,018. Engine mountings for aircraft. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTIONS DE MOTEURS D'AVIATION. Nov. 7, 1957 [Nov. 12, 1956], No. 34717/57. Class 4. [Also in Groups XXV and XXVI] A jet propulsion unit is carried in an aircraft nacelle by a plurality of supports disposed in the vicinity of the centre of gravity of the unit, at least one support comprising a trunnion bolted to the nacelle which is engaged by a bearing having a part-spherical surface coacting with a corresponding surface on the jet propulsion unit casing and at least one of the supports being adapted to permit the junction between the support and the casing to move longitudinally with respect to the casing, all of the joints being arranged to withstand streams tangential to the casing. The jet propulsion unit, Fig. 1, is suspended by two lateral pivotal supports 1 at the extremities of a horizontal diameter close to the centre of gravity of the unit and a third support 2 of the pivotal socket type located at the upper or lower part of the unit in the transverse plane passing through the supports 1. Each support 1 is mounted in a housing 5, Fig. 2, provided in the casing. A bushing 3 provides a spherical seat for a bearing 4 which is biased by a spring 9 to a position in which the bore is coaxial with the bushing so as to facilitate the insertion of the tunnion 8. The upper 1 or lower support 2, Fig. 3, comprises a pivotal bearing 10 housed in a bushing 11 which is provided with two flats so that it may slide between guides 13 fixed in a support 14. To facilitate the installation of the engines, the trunnion may be retained in position by a spring loaded ball in the support engaging a groove in the trunnion. The ball is released when the engine is installed and the support bolted in position. In another modification, Fig. 6 (not shown), the trunnion is located axially relative to the bearing by means of a knob which engages the inner periphery of the bearing and is held in position by a bolt. The unit is prevented from rotating about the horizontal axis passing through the supports 1 by an adjustable link 28. In a modified form of mounting, Fig. 8 (not shown), the upper support is an anchored pivotal socket and the lateral supports sliding sockets. In a further modification, Fig. 11 (not shown), the supports at the extremities of the diameter are arranged in a vertical plane and the remaining support in a horizontal plane through the engine axis. One of these supports may be dispensed with.

3. 发明专利

DE1052253B 未知
公开(公告)号：DE1052253B
公开(公告)日：1959-03-05
申请号：DES0055825
申请日：1957-11-09
申请人： SNECMA
发明人： JUMELLE LOUIS FRANCOIS , MOREL MAX ANDRE JACQUES , LEGRAND PAUL JOSEPH , EICHHOLTZ KONRAD AUGUST WERNER
IPC分类号： B64D27/26 , F02C7/20 , F16C11/06
摘要： 866,018. Engine mountings for aircraft. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTIONS DE MOTEURS D'AVIATION. Nov. 7, 1957 [Nov. 12, 1956], No. 34717/57. Class 4. [Also in Groups XXV and XXVI] A jet propulsion unit is carried in an aircraft nacelle by a plurality of supports disposed in the vicinity of the centre of gravity of the unit, at least one support comprising a trunnion bolted to the nacelle which is engaged by a bearing having a part-spherical surface coacting with a corresponding surface on the jet propulsion unit casing and at least one of the supports being adapted to permit the junction between the support and the casing to move longitudinally with respect to the casing, all of the joints being arranged to withstand streams tangential to the casing. The jet propulsion unit, Fig. 1, is suspended by two lateral pivotal supports 1 at the extremities of a horizontal diameter close to the centre of gravity of the unit and a third support 2 of the pivotal socket type located at the upper or lower part of the unit in the transverse plane passing through the supports 1. Each support 1 is mounted in a housing 5, Fig. 2, provided in the casing. A bushing 3 provides a spherical seat for a bearing 4 which is biased by a spring 9 to a position in which the bore is coaxial with the bushing so as to facilitate the insertion of the tunnion 8. The upper 1 or lower support 2, Fig. 3, comprises a pivotal bearing 10 housed in a bushing 11 which is provided with two flats so that it may slide between guides 13 fixed in a support 14. To facilitate the installation of the engines, the trunnion may be retained in position by a spring loaded ball in the support engaging a groove in the trunnion. The ball is released when the engine is installed and the support bolted in position. In another modification, Fig. 6 (not shown), the trunnion is located axially relative to the bearing by means of a knob which engages the inner periphery of the bearing and is held in position by a bolt. The unit is prevented from rotating about the horizontal axis passing through the supports 1 by an adjustable link 28. In a modified form of mounting, Fig. 8 (not shown), the upper support is an anchored pivotal socket and the lateral supports sliding sockets. In a further modification, Fig. 11 (not shown), the supports at the extremities of the diameter are arranged in a vertical plane and the remaining support in a horizontal plane through the engine axis. One of these supports may be dispensed with.

4. 发明专利

FR80178E 未知
公开(公告)号：FR80178E
公开(公告)日：1963-03-22
申请号：FR869707
申请日：1961-08-01
申请人： SNECMA
发明人： MOREL MAX ANDRE JACQUES
IPC分类号： F02K1/64

5. 发明专利

GB965992A Jet-deflecting device 未知
公开(公告)号：GB965992A
公开(公告)日：1964-08-06
申请号：GB2862662
申请日：1962-07-25
申请人： SNECMA
发明人： MOREL MAX ANDRE JACQUES
IPC分类号： F02K1/64
摘要： 965,992. Deflecting propulsion jets. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. July 25, 1962 [Aug. 1, 1961], No. 28626/62. Addition to 925,010. Heading B7G. [Also in Division F1] In a gas turbine engine, cold air from fan V driven by turbine T, normally issues rearwardly from an annular duct 9, but on movement of a fairing 7 and vanes 1, 2 and on inflation of an annular body 17, 18 the cold air flow is deflected. The body 17, 18 is clamped between an annular cup 16 and a wall 11 and is inflated from the low pressure compressor of the gas turbine engine. The speed of inflation can be regulated at will, to vary the progressive action of the braking effect produced by the deflected air.

6. 发明专利

GB925010A Improvements in or relating to turbo-fan units 未知
公开(公告)号：GB925010A
公开(公告)日：1963-05-01
申请号：GB734661
申请日：1961-02-28
申请人： SNECMA
发明人： MOREL MAX ANDRE JACQUES , BAUGER LOUIS JULES , BARDIN ANDRE ANATOLE AUGUSTIN
IPC分类号： F02K1/32 , F02K1/72
摘要： 925,010. Jet propulsion plant. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Feb. 28, 1961 [March 7, 1960], No. 7346/61. Class 110 (3). [Also in Group XXXIII] Cool air from a fan V driven by a gas turbine engine T is deflected by annular vanes 1 carried by rods 2 fixed to a ring 3 guided by rollers 5 in slides 6 and moved by jacks 4 to shift the vanes 1 from within a cowling 8 to the operative position shown; a cowling 7 on rods 2 and cowling 8 form an annular nozzle 9 in the inoperative position of vanes 1, Fig. 2; air or gas from slots 12 prevents the cool air jet from entering the open part of nozzle 9 in the operative position of vanes 1. As the cowling 7 is moved rearwardly from the Fig. 2 position the cross-sectional area of the annular discharge nozzle of the fan is progressively decreased. In Figs. 3, 4, not shown, the vanes are fixed and are uncovered by a movable cowling.

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