GB866969A - Gas turbine engines - Google Patents

Abstract

866,969. Generating combustion products under pressure. BEST, G. C. Dec. 14, 1959, No. 42409/59. Class 51 (1). [Also in Group XXVI] A gas turbine engine includes a compressor 21, Fig. 1, an annular combustion chamber having inner and outer walls 49 and 45 respectively and a closed end 47, an annular flame tube 34 having inner and outer walls 36 and 35 respectively and a closed end 37, the combustion chamber and annular flame tube forming a duct defined by the spaced walls 35, 45, the closed ends 37, 47, and the walls 36, 49, for delivering air from the compressor to the flame tube. Some of the air enters the flame tube through apertures 39, the remainder flowing round the closed end of the tube and entering the flame tube through apertures 40. The combustion products pass through a turbine 22 and thence along a further duct around the closed end 47 of the combustion chamber and along the outside of the outer wall 45 of the combustion chamber to exhaust apertures 54. The walls 45, 49 are corrugated longitudinally to facilitate heat transfer from the exhaust gases in the further duct to the air in the first mentioned duct. In a further embodiment, Fig. 3, a second turbine 103 is provided for useful power output. In this case heat insulating material 94 is provided between the walls 90 of a shroud and the inner wall 82 of the combustion chamber and only the outer wall 83 of the combustion chamber has corrugations.