Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine
Abstract
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:
- Research Org.:
- SIEMENS ENERGY, INC., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1243329
- Patent Number(s):
- 9,291,063
- Application Number:
- 13/408,287
- 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., Schilp, Reinhard, and Ross, Christopher W. Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine. United States: N. p., 2016.
Web.
Little, David A., Schilp, Reinhard, & Ross, Christopher W. Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine. United States.
Little, David A., Schilp, Reinhard, and Ross, Christopher W. Tue .
"Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine". United States. https://www.osti.gov/servlets/purl/1243329.
@article{osti_1243329,
title = {Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine},
author = {Little, David A. and Schilp, Reinhard and Ross, Christopher W.},
abstractNote = {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).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2016},
month = {3}
}
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