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Title: Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section

A midframe portion (113) of a gas turbine engine (110) is provided, including a compressor section (112) with a last stage blade (124). The compressor section (112) is configured to introduce a radial velocity component into an air flow (111) such that the air flow is discharged from the compressor section (112) at a mixed direction based on a combined longitudinal velocity component and radial velocity component. The midframe portion (113) further includes a manifold (121) to directly couple the air flow from an outlet of the compressor section (112) to an inlet of a respective combustor head (118) of the gas turbine engine (110).
Inventors:
Issue Date:
OSTI Identifier:
1461514
Assignee:
Siemens Energy, Inc. (Orlando, FL) NETL
Patent Number(s):
10,012,098
Application Number:
13/407,987
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

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