Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine

Little, David A.; Schilp, Reinhard; Ross, Christopher W.

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Title: 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:: Little, David A.; Schilp, Reinhard; Ross, Christopher W.

Issue Date:: Tue Mar 22 00:00:00 EDT 2016

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

Sponsoring Org.:: USDOE

OSTI Identifier:: 1243329

Patent Number(s):: 9291063

Application Number:: 13/408,287

Assignee:: SIEMENS ENERGY, INC. (Orlando, FL)

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES

F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS

Show more

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 F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C3/14 - characterised by the arrangement of the combustion chamber in the plant
F02C3/145 - {the combustion chamber being in the reverse flow-type}

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}

Show less

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.

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                    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.

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                    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.

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@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         = {Tue Mar 22 00:00:00 EDT 2016},

  month        = {Tue Mar 22 00:00:00 EDT 2016}

}

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Works referenced in this record:

Rotating turbine stator
patent, June 1984

Jen, Hsianmin
US Patent Document 4,455,121
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/4455121

Part load blade tip clearance control
patent, November 2005

Little, David A.
US Patent Document 6,968,696
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Blade tip clearance control
patent, August 2006

Chehab, Abdullatif M.; Little, David A.
US Patent Document 7,086,233
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/7086233

Blade tip clearance control
patent, August 2006

Little, David A.; McQuiggan, Gerry
US Patent Document 7,096,673
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/7096673

Turbine engine sequenced combustion
patent, September 2006

Little, David A.
US Patent Document 7,107,773
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Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010

Bancalari, Eduardo; Wilson, Jody W.; Little, David A.
US Patent Document 7,721,547
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Structural Attachment System for Transition Duct Outlet
patent-application, July 2010

Charron, Richard
US Patent Application 12/357607; 20100180605
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/20100180605

Assembly for directing combustion gas
patent-application, August 2011

Charron, Richard; Nordlund, Raymond; Morrison, Jay
US Patent Application 13/096041; 20110203282
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Tangential Combustor with Vaneless Turbine for Use on Gas Turbine Engines
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Toqan, Majed; Gregory, Brent Allen; Yamane, Ryan Sadao
09/01/2011, vp
US Patent Application 12/786882; 20110209482
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Compressed air plenum for a gas turbine engine
patent-application, February 2012

Charron, Richard
US Patent Application 12/852707; 20120031068
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/20120031068

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Similar Records

Title: Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine

Abstract

Citation Formats

Rotating turbine stator patent, June 1984

Part load blade tip clearance control patent, November 2005

Blade tip clearance control patent, August 2006

Blade tip clearance control patent, August 2006

Turbine engine sequenced combustion patent, September 2006

Combustion transition duct providing stage 1 tangential turning for turbine engines patent, May 2010

Structural Attachment System for Transition Duct Outlet patent-application, July 2010

Assembly for directing combustion gas patent-application, August 2011

Tangential Combustor with Vaneless Turbine for Use on Gas Turbine Engines patent-application,

Compressed air plenum for a gas turbine engine patent-application, February 2012

Rotating turbine stator
patent, June 1984

Part load blade tip clearance control
patent, November 2005

Blade tip clearance control
patent, August 2006

Blade tip clearance control
patent, August 2006

Turbine engine sequenced combustion
patent, September 2006

Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010

Structural Attachment System for Transition Duct Outlet
patent-application, July 2010

Assembly for directing combustion gas
patent-application, August 2011

Tangential Combustor with Vaneless Turbine for Use on Gas Turbine Engines
patent-application,

Compressed air plenum for a gas turbine engine
patent-application, February 2012