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
ApplicationNo. 493141 filed on 06/21/1995
US Classes:60/39.37, Plural combustion products generators in ring coaxial with turbine60/799Having expansible connection
ExaminersPrimary: Thorpe, Timothy S.
Assistant: Kim, Ted
Attorney, Agent or Firm
Foreign Patent References
International ClassF02C 003/00
Foreign Application Priority Data1994-09-15 GB
AbstractA 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.