Gas turbine combustor liner with asymmetric dilution holes machined from a single piece form
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United States of America Patent
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Apr 29, 2003
Grant Date -
Dec 12, 2002
app pub date -
Jun 11, 2001
filing date -
Jun 11, 2001
priority date (Note) -
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Abstract
An annular gas turbine engine combustor liner has a single piece annular shell circumscribed about a first axis of revolution. The shell has a hot side and a cold side, an annular dilution hole section, and a plurality of asymmetrical cylindrical dilution holes extending through the section. Pockets are circumferentially interdigitated between the dilution holes and extend into the shell from the cold side such that the pockets form dilution hole bosses between the pockets through which the dilution holes extend. Each of the dilution holes is circumscribed about a second axis of revolution which is not parallel to the first axis of revolution. The liner may further include forward and aft annular cooling nuggets located forward and aft of the dilution hole section and having annular film cooling slots which are open in the axially aftwardly direction. The shell is machined from a single piece integrally formed near net shape form such as a forging, a casting, or more particularly a spin or centrifugal casting. The invention includes a method for making the annular gas turbine engine combustor liner by forming a single piece integrally formed near net shape form and machining it to produce the shell and the above features in the shell.
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