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Title: Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine

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).
Inventors:
; ;
Issue Date:
OSTI Identifier:
1243329
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
Patent Number(s):
9,291,063
Application Number:
13/408,287
Contract Number:
FC26-05NT42644
Resource Relation:
Patent File Date: 2012 Feb 29
Research Org:
SIEMENS ENERGY, INC., Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS
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