Flame tubes for combustion chambers for gas turbine engines
Реферат: 1314666 Gas turbine engine combustion equipment UNITED AIRCRAFT CORP 2 Sept 1971 [30 Oct 1970J 40928/71 Heading F1L The invention relates to combustion equipment of a gas turbine engine and to a flame tube construction thereof. The flame tube 20 shown is of annular form and is disposed between air casing walls 16, 17 the flame tube comprising segments 20a, 206, 20c, 20d, 20e also an end member 22. Each segment is formed of inner and outer walls 40, 42 the inner wall being formed with longitudinally extending ribs 46 whereby in the assembly cooling air passages 44 are defined between the walls. The outer wall 42 of an upstream segment extends downstream as at 52 and the inner wall 40 of the adjacent downstream segment extends upstream as at 54 the segments being inter-connected by welding at the over-lapping parts. The length of the segments increases towards the downstream end of the flame tube as the combustion temperature decreases.
Wall element for combustion chambers
Номер патента: GB1138679A. Автор: Jacques Emile Jules Caruel,Armand Jean-Baptiste Lacroix. Владелец: Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA. Дата публикации: 1969-01-01.