Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
Abstract
A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).
- Inventors:
- Issue Date:
- Research Org.:
- SIEMENS ENERGY, INC., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1330364
- Patent Number(s):
- 9,476,355
- Application Number:
- 13/408,147
- Assignee:
- SIEMENS ENERGY, INC. (Orlando, FL)
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2012 Feb 29
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS
Citation Formats
Little, David A., McQuiggan, Gerard, and Wasdell, David L. Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section. United States: N. p., 2016.
Web.
Little, David A., McQuiggan, Gerard, & Wasdell, David L. Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section. United States.
Little, David A., McQuiggan, Gerard, and Wasdell, David L. Tue .
"Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section". United States. https://www.osti.gov/servlets/purl/1330364.
@article{osti_1330364,
title = {Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section},
author = {Little, David A. and McQuiggan, Gerard and Wasdell, David L.},
abstractNote = {A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2016},
month = {10}
}
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Works referenced in this record:
Turbine engine sequenced combustion
patent, September 2006
- Little, David
- US Patent Document 7,107,773
Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010
- Bancalari, Eduardo; Wilson, Jody; Little, David A.
- US Patent Document 7,721,547