Gas flow path for a gas turbine engine
Abstract
A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.
- Inventors:
- Issue Date:
- Research Org.:
- SIEMENS ENERGY, INC. Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1346959
- Patent Number(s):
- 9,593,853
- Application Number:
- 14/185,352
- Assignee:
- SIEMENS ENERGY, INC.
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2014 Feb 20
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING
Citation Formats
Montgomery, Matthew D., Charron, Richard C., Snyder, Gary D., Pankey, William W., Mayer, Clinton A., and Hettinger, Benjamin G. Gas flow path for a gas turbine engine. United States: N. p., 2017.
Web.
Montgomery, Matthew D., Charron, Richard C., Snyder, Gary D., Pankey, William W., Mayer, Clinton A., & Hettinger, Benjamin G. Gas flow path for a gas turbine engine. United States.
Montgomery, Matthew D., Charron, Richard C., Snyder, Gary D., Pankey, William W., Mayer, Clinton A., and Hettinger, Benjamin G. Tue .
"Gas flow path for a gas turbine engine". United States. https://www.osti.gov/servlets/purl/1346959.
@article{osti_1346959,
title = {Gas flow path for a gas turbine engine},
author = {Montgomery, Matthew D. and Charron, Richard C. and Snyder, Gary D. and Pankey, William W. and Mayer, Clinton A. and Hettinger, Benjamin G.},
abstractNote = {A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2017},
month = {3}
}
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