Patent GB-969806-A (GB)
Title: Improvements relating to the installation of jet engines in engine bays
Inventor: CHILVERS ERNEST EDWARD
IPC: B64D27/26
Filed: 1962-05-16
Abstract: 969,806. Gas turbine jet engines. ROLLS-ROYCE Ltd. May 16, 1962, No. 18948/62. Heading F1G. An installation comprises a jet engine installed in an engine bay, the engine and the engine bay being respectively provided with relatively movable members which are in engagement with each other, the relatively movable members being relatively movable between an inoperative position in which the engine may be installed in or may be removed from the engine bay, and an operative position in which the engine is supported by the relatively movable members in the engine bay there being means for effecting relative movement of the relatively movable members between, and for retaining them as required in, the operative and the inoperative positions. The invention is described with reference to the installation of a vertical lift gas turbine jet engine 11 within an engine bay 10. The engine casing 12 is provided with three bearing members 17 in each of which is mounted a trunnion pin 18. Each trunnion pin is formed integrally with a cup-shaped member 20, the three cup members being mounted in a common yoke member 21. A further cup member 22 is mounted within each cup member 20, the member 22 being urged outwardly by means of a spring 23. Each cup member 22 has a part-cylindrical concave surface 24 within which is mounted a partcylindrical plate 25 which forms part of a guide member 26, each of which comprises a pair of spaced plates 27 between which are mounted two spaced-apart rollers 28, the plates 27 being spaced apart by the plates 25. Each plate 25 is pivotally connected to its associated trunnion pin 18. As shown in Fig. 2 the engine is supported within the engine bay 10 by means of engine support members 33 each of which is of channel section and is mounted for pivotal movement at 34. The rollers 28 engage within the grooves of the support members 33, the lower roller 28 bearing against the lower side of the yoke member 21 thereby supporting the engine 11. A bracket member 35 is secured within the engine bay, the bracket having an abutment portion 36 against which bears the upper side of the yoke member 21. The further channelsection member 30 is secured within the engine bay and the support member 33 may be swung about the pivot 34 to the position indicated in broken lines, the channel sections 33 and 30 then being aligned to form a track, and the engine may then be lowered out of the engine bay, the rollers 28 moving along the tracks 33, 30. The support members 33 are moved by means of screw jacks 38 and links 37. A duct assembly 43, 44, 45 is provided through which air under pressure may be supplied to the turbine for the rotation thereof at starting. The part 43 is secured to the engine and the part 45 to the engine bay, the part 44 being an intermediate part carried by the part 45, and supported therefrom by means of a spring 47. The parts are arranged to couple together automatically when the engine is installed in the bay. A similar coupling device is provided for the duct assembly 52, 53 which constitutes an air bleed duct. Specification 950,909 is referred to.