Gas flow path for a gas turbine engine

Montgomery, Matthew D.; Charron, Richard C.; Snyder, Gary D.; Pankey, William W.; Mayer, Clinton A.; Hettinger, Benjamin G.

Title: Gas flow path for a gas turbine engine

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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:: Montgomery, Matthew D.; Charron, Richard C.; Snyder, Gary D.; Pankey, William W.; Mayer, Clinton A.; Hettinger, Benjamin G.

Issue Date:: 2017-03-14

Research Org.:: SIEMENS ENERGY, INC. Orlando, FL (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1346959

Patent Number(s):: 9593853

Application Number:: 14/185,352

Assignee:: SIEMENS ENERGY, INC.

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES

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F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/425 - {Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes}
F23R3/46 - Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings
F23R2900/00017 - Assembling combustion chamber liners or subparts
F23R3/60 - Support structures

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D9/023 - {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R2900/03342 - Arrangement of silo-type combustion chambers

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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.

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                    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.

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                    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.

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@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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