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
Abstract
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:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1461514
- Patent Number(s):
- 10,012,098
- Application Number:
- 13/407,987
- Assignee:
- Siemens Energy, Inc. (Orlando, FL) NETL
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2012 Feb 29
- Country of Publication:
- United States
- Language:
- English
Citation Formats
Rodriguez, Jose L. 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. United States: N. p., 2018.
Web.
Rodriguez, Jose L. 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. United States.
Rodriguez, Jose L. Tue .
"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". United States. https://www.osti.gov/servlets/purl/1461514.
@article{osti_1461514,
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},
author = {Rodriguez, Jose L.},
abstractNote = {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).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2018},
month = {7}
}
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