Patent GB-829753-A (GB)
Title: Aircraft
Inventor: DAVIDSON IVOR MACAULAY
IPC: B64D27/18
Filed: 1957-02-04
Abstract: 829,753. Gas-turbine jet-propulsion plant. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Jan. 17, 1958 [Feb. 4, 1957], No. 3749/57. Class 110 (3). [Also in Group XXXIII] Figs. 5a and 5b together show a cross - section through the upper half of a gas turbine by - pass engine installed in a tube 31. The by-pass compressor has a rotor 41 attached to an intake bullet 8 and to a shaft 81 mounted in bearings 82, 83, 84. Bearing 82 is supported on fixed structure attached to struts 46 on the stator casing 43. Part of the compressor delivery passes into a by-pass duct defined by walls 31, 91 and part passes to a high pressure compressor comprising a stator 50 and a rotor 53 supported in bearing 79, 80. The high-pressure compressor delivery passes to an annular combustion chamber 54, and discharges through a first turbine, the rotor 61 of which drives compressor rotor 53 through shaft 65, and a second turbine the rotor 72 of which drives compressor rotor 41 through shaft 81. The bearings 80 and 83 are supported on fixed structure having three radial struts 69 and 70 (one shown), with feet 70a located in longitudinal slots 31c in tube 31, so that when a fairing 10 is removed, a strap 90, normally attaching casing 43 to tube 31 through flanges 43a, 31b can be removed and the engine withdrawn, feet 70a sliding in slots 31c. The by-pass and turbine exhausts mix and discharge through a tube 24 to a fish-tail nozzle 101. To prevent overheating of the aircraft wing (see Group XXXIII), surrounding the engine, a heat insulating liner 92 is spaced from tube 24 by spacers 93, and extends from a station within the by-pass duc tto the nozzle, so that relatively cool by-pass air alone flows through the annular space between tube 24 and liner 92. A further annular space 27 is defined by tubes 24 and 25 and ambient air from a ram air inlet is conducted through this space. To accommodate flexing of the wing, a resilient ring may be placed between flanges 43a, 31b and the struts 70 may be in two parts connected by a damping device, or may have resilient feet. Thirteen such engines are mounted side by side in the wing, each having its own lubricating system, but other auxiliaries are common to all or groups of the engines. Fuel and ignition lines are carried via disengageable connections on casing 43, through struts 46, and along stator 50 to the combustion system. Compressed-air for starting may be led to compressor or turbine rotor blades by the same route, as may control lines for angular adjustable blades. Air tapped from a compressor of each engine is led by a common manifold to air turbines driving the auxiliaries. One or two engines may have cartridge starters, the compressed-air delivered by these engines to the manifold serving to start the remaining engines. Compressed-air may alternatively be supplied from a ground source for starting all the engines. The fuel supplies of the engines are controlled all together or in groups, apart from a separate shut-off cock for each engine. Fig. 7 is a cross-section of a fish-tail nozzle 101 which has part of its upper wall 106 pivotable by a jack 107 to vary its cross-sectional area. A flap 7 is mounted as in Specifications 787,011- 5, and is adjustable by a jack 105 to vary the direction of efflux of the stream. Flaps may also be pivoted to the downstream end of wall 91 to vary the by-pass duet area. Specifications 749,009, 790,193, 790,194, 790,298, 805,418, 812,751, 823,591, 823,592 and 823,593 also are referred to.