PRE-DIFFUSER WITH HIGH CANT ANGLE
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United States of America Patent
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Issued Date -
Feb 16, 2017
app pub date -
Aug 14, 2015
filing date -
Aug 14, 2015
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Abstract
A gas turbine engine is provided. The engine includes a combustor configured at a combustor angle relative to an engine axis and a pre-diffuser configured to supply air to the combustor and configured at a diffuser angle relative to the engine axis, wherein the diffuser angle is greater than the combustor angle. A method of manufacturing a gas turbine engine includes installing a combustor at a combustor angle relative to an engine axis and installing a pre-diffuser at a diffuser angle relative to the engine axis, wherein the diffuser angle is greater than the combustor angle. A gas turbine engine includes a pre-diffuser configured at an angle of between 8° and 10° relative to an engine axis.
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