Patent References 2578481 2592060 2608057 2615300 2709338 Gas turbine engine having an improved transition duct support Combustor liner joints Gas turbine engine Combustion chamber assembly with hollow support strut for carrying cooling air Thermoelastic connection of the injector tube and the flame tube of a gas turbine InventorsAssigneeApplicationNo. 493141 filed on 06/21/1995US Classes:60/39.37, Plural combustion products generators in ring coaxial with turbine60/799Having expansible connectionExaminersPrimary: Thorpe, Timothy S.Assistant: Kim, Ted Attorney, Agent or FirmForeign Patent References
International ClassF02C 003/00Foreign Application Priority Data1994-09-15 GBAbstractA combustion chamber assembly comprises a plurality of tubular combustion chambers which have their axes arranged generally radially. A transition duct is provided for each of the tubular combustion chambers. Each transition duct has a circular upstream end arranged coaxially with the downstream end of the respective tubular combustion chamber. An annular resilient member mounts the upstream end of the respective transition duct on a tubular portion of a respective support structure. The inner end of the annular member is formed integrally with the upstream end of the transition duct and the outer end of the annular member is secured to a flange on the tubular portion of the support structure by a bolted connection. The annular member has a plurality of circumferentially extending slots to allow thermally induced articulation and to maintain the upstream end of the transition duct coaxial with the support member. | |