GB1219665A - Improvements in or relating to gas turbine engines - Google Patents

Abstract

1,219,665. Gas turbine engines - combustion equipment. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. June 27, 1968 [June 28, 1967], No.30789/68. Heading F1G and F1L. A gas turbine engine assembly comprises an annular combustion chamber having an annular flame tube, the outer wall of the flame tube comprising an upstream portion and a downstream portion, the latter being arranged for axial sliding motion on the former, the turbine stator assembly being releasably connected on one hand to the upstream portion by engine structure, and on the other hand to the downstream portion by means of a releasable connection surrounding the downstream portion. The engine shown comprises an annular combustion section 34, a turbine inlet nozzle guide vane assembly 5, 6 and a turbine rotor 7, 8, the combustion equipment comprising an inner wall 40 and an outer wall formed of two semi-cylindrical parts 9a, 9b, having flanges 10a, 10b which are secured together by bolts 11. Disposed within the annular chamber formed between the walls 40, 9a, 9b is an annular flame tube the inner wall of which is formed of sections 1e, 1f, 1g, 1h, 1i, 1k and the outer wall of which is formed of sections 2e, 2f, 2g, 2h, 16, the sections 1e, 2e defining an annular dome 52 through which project fuel burners 22. The sections of the inner wall are secured together by means of ring members 46e ... which are formed with air inlet opening 41e .... The sections 2e, 2f, 2g, 2h of the outer wall are likewise secured together by means of ring members 47e ... which are formed with air inlet openings 48e .... A ring member 47h is secured at the downstream end of the section 2h and the downstream section 16 is mounted thereon so that it may be moved axially to the position indicated in broken lines at 16x to permit assembly and dismantling. The inner wall 40 is secured to the turbine inlet nozzle structure 5, 6 by a wall member 50 and the flame tube wall section 1k is mounted with freedom for axial expansion on a part 62 secured to the member 50. The flame tube wall section 16 is formed with a radial flange portion 17b which is clamped between flange 15 of the combustion equipment outer wall assembly 9a, 9b and flange members 18, 19 of the turbine stator casing 13, the flanges 15, 18, 19 being secured together by bolts 35. A radial flange 14 at the upstream end of the outer wall assembly 9a, 9b is secured by bolts 36 to a radial flange 33a of an inlet diffuser member 12, a cylindrical flange 33b of the member 12 being formed with circumferentiallyspaced slots 30 in which key members 23, 24 are received. The key members 24 are formed on support struts 32 which are secured at their inner ends to the annular dome 52 of the annular flame tube. The key members 23 are formed on fuel burner support members 21, the members being inter-connected by fuel manifolds 20a, 20b, fuel passing therefrom through passages 63, 64 to discharge from the burners 70. A swirl vane assembly 69 is associated with each burner.