Patent GB-1206029-A (GB)
Title: Engine mountings for jet engines
Inventor: KOPP GERHARD
IPC: B64D27/26
Filed: 1968-06-20
Abstract: 1,206,029. Mounting of aircraft jet engines. MESSERSCHMITT - BOLKOW - BLOHM G.m.b.H. 20 June, 1968 [18 July, 1967], No. 29585/68. Heading B7G. [Also in Division Fl] The invention relates to the mounting of a jet engine on an aircraft, the engine being mounted by means of support struts located in two transverse planes along the length of the engine, there being at least one thrust pin disposed either above or below the engine centre line, the thrust pin being provided with means for retaining it in its normal engine supporting position after the engine has been removed. The support struts are provided with means for retaining them in the same position on the engine after disconnection from the aircraft as when they carry the engine. In Fig. 1, two jet engines 10, 11 are disposed side by side, each engine being supported adjacent its air intake 12 or 13 by two support struts 20, 30, the strut 20 being disposed normal to the Y-axis and the strut 30 being disposed normal to the Z-axis. Each engine is supported adjacent its rearward end at the forward end of the jet nozzle 14, 15 by two support struts 40, one at each side of the engine, the struts being disposed normal to the Y-axis. In the same transverse plane as the struts 40 is disposed a thrust pin 50 in the Z-axis and indicated as being below the engine axis X. The mounting of struts 20, 30 on the engine 10 and on the aircraft structure 90 is shown in Fig. 9. The strut 20 is supported at its upper end from the structure 90 by means of a partspherical mounting 35, see Fig. 12, and at its lower end by means of a part-spherical mounting 25, see Figs. 10, 11, means 22 being provided to lock the bolt 21. The lower end of the strut 20 is located between a pair of flanges 19 integral with the engine casing, the bolt 21 passing through the flanges 19 and the part-spherical bearing 25. The strut 30 is mounted at its righthand end between the flanges 19 of the engine casing in a part-spherical bearing 94 and at its left-hand end in a part-spherical bearing 93, a locking means similar to that shown in Figs. 10, 11 being provided at the bearing 93. The assembly of a thrust pin 50 is shown in Fig. 2, the engine casing being indicated at 10 and the aircraft structure at 70. A bush 17 is secured within a recess 16 of the engine casing and a part-spherical bearing 18 is mounted in the bush. A housing 52 is secured to the structure 70, the housing having a frusto-conical surface 53. A thrust pin 51 is entered into the housing until a frusto-conical surface on the pin engages the corresponding surface on the housing, the upper end of the pin engaging within the partspherical bearing 18 with freedom for axial movement therein. A ring member 58 comprising three arcuate segments held together by a spring 71 is engaged between the lower end of the pin 51 and the housing 52, the interengaging surfaces being frusto-conical. Three pins 72 project radially from the ring member 58 into bores in the thrust pin 51. The ring member 58 and so the thrust pin 51 is retained by means of a screwed ring member 73 which is locked by means of a ring member 74 with projections 75. The ring member 73 and the lower end of the pin 51 are shaped to retain a ball 81 therebetween, whereby the ring member may be used to extract the pin. The pin 51 is also centred and retained by means of spring clips 55, 56. A second embodiment of the thrust pin 150 is shown in Fig. 3. A housing 152 is secured in the aircraft structure 170, the pin and the housing being formed with co-operating frusto-conical surfaces 153 as in the previous embodiment. The lower end of the pin engages the axial bore within a part-spherical bearing member 118 which engages a correspondinglyshaped bush 117 secured to the engine casings 10, 11. A bolt member 177 extends through the pin 151 being engaged at its lower end with a nut 119 which is secured to the part-spherical member 118. A ring member 158 mounted at the upper end of the bolt 177 is urged downwardly into contact with the pin 151 by means of a screwed ring 173, the ring 173 also being utilized to withdraw the pin 151 as in the previous embodiment. Locking means are provided to prevent inadvertent turning of the head 186 of the bolt.