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Title: 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:
; ; ; ; ;
Publication 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. NETL
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. doi:. 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 = {Tue Mar 14 00:00:00 EDT 2017},
month = {Tue Mar 14 00:00:00 EDT 2017}
}

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