Combustor support structure
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United States of America Patent
Stats
-
Jan 1, 1980
Grant Date -
N/A
app pub date -
Jun 8, 1978
filing date -
Jun 8, 1978
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A combustor assembly for a gas turbine engine includes a tubular, multi-layered porous metal wall with pores therethrough for distribution of compressor discharge air into a combustion chamber and wherein a rigid combustor support ring is connected to one end of the wall to receive an inlet diffuser member including an ovate inlet and a circular outlet connected to the support ring for axially directing primary air flow into the combustion chamber; and the diffuser member including a flow divider on one outer surface thereof including means for fixedly securing the inlet diffuser member with respect to a wall of a gas turbine engine and wherein coacting means are provided between the inlet diffuser member and the rigid combustor support ring of the combustor to radially connect it in place at one end thereof and wherein further coacting means are provided between the inner engine wall and a portion of the porous sleeve for axially indexing of the combustor assembly.
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