Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine
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United States of America Patent
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Mar 22, 2016
Grant Date -
Aug 29, 2013
app pub date -
Feb 29, 2012
filing date -
Feb 29, 2012
priority date (Note) -
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Abstract
A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
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