GB812404A - Internal combustion turbine units - Google Patents

Abstract

812,404. Gas-turbine plant. NAPIER & SON Ltd., D. Aug. 9, 1955 [Aug. 18, 1954; July 28, 1955], Nos. 24007/54 and 21792/55. Class 110 (3). [Also in Group XII] In a gas-turbine plant comprising a rotary compressor supplying air to an annular series of combustion chambers feeding a turbine driving the compressor which is coaxial with and spaced from the turbine, each of the combustion chambers comprises a rigid stress-taking outer wall rigidly secured at its ends respectively to the compressor and turbine casings and is rigidly secured to or integral with at least one common annular plate-like structure not forming part of and removable from the turbine and compressor casings. In the arrangement shown, Fig. 1, the compressor casing A includes ducts A<SP>1</SP> leading to the combustion chambers which discharge through ducts B<SP>1</SP> in the turbine casing B to the turbine nozzle ring. The combustion chamber assembly comprises a series of circumferentially spaced stress-taking tubular walls E attached, as by welding, to annular plate-like structures formed by end plates C, D. A bridging wall E<SP>1</SP> may be welded to each pair of adjacent tubular walls E. A bridging wall E<SP>1</SP> may be provided inside the circle on which the axes of the combustion chambers lie. The plates C, D are of annular form and are bolted at the periphery to the casings A and B. The plate C has an axially extending flange C<SP>1</SP> provided with circumferential grooves to form a fluid-tight sliding seal with the compressor casing A. In a modification, Fig. 4, the combustion chamber assembly comprises an inner wall K and an outer wall L which are formed with longitudinal recesses L<SP>1</SP>, K<SP>1</SP> which co-operate to form tubular combustion chambers N. The walls K and L may be recessed at K4, L4 to form interconnecting passages between the chambers N and are provided at their ends with flanges K<SP>3</SP>, L<SP>3</SP>, each of which forms an annular plate-like structure by means of which they are attached to the compressor and turbine casings. In a further modification of this arrangement, the outer wall is made in three sections connected together by longitudinal flanges. Bridgepieces may be welded to the walls of adjacent recesses. The combustion chambers may be parallel or inclined to the axis of the compressorturbine rotor.