GB761435A - Improvements in or relating to gas turbine engines - Google Patents

Abstract

761,435. Gas turbine plant. BRISTOL AEROPLANE CO., Ltd. Jan. 29, 1954 [Feb. 17, 1953], No. 4469/53. Class 110 (3). In a gas turbine engine having hollow inlet guide vanes in the air intake of the engine, means (other than hollow rotor shafting of the engine) are provided to convey air tapped from a compressor of the engine to the interior of the guide vanes, thereby heating them, and then into heat exchange relation with a part of the engine requiring cooling. In the engine shown, the intake 14 of the air compressor 37 is disposed between the compressor and the turbine 38. Air tapped from the compressor is led through the duct 11 to an annular manifold 12a, the wall 14a of which constitutes the outer wall of the air intake. Hollow air intake guide vanes 16 are mounted in a ring 13 and communicate with the manifold 12a through apertures 15a. The inner ends of the vanes are mounted in an annular manifold 18 and the air passes therefrom through apertures 19 into two pipes 20 which communicate at their downstream ends with an annular chamber 36. Air issues from the chamber 36 through apertures 139, some air flowing over the upstream face 35 of the turbine rotor disc 24, and the remaining air passing through passages 25 into a recess 28 from which it passes through passages 29 and over the faces 39 and 40 of the rotor discs 24 and 30. Some air also flows from the recess 28 across the downstream face of the rotor disc 30. The air streams after flowing across the rotor faces enter the main gas stream flowing through the turbine. Specification 579,856 is referred to.