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).
- 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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