Swirling midframe flow for gas turbine engine having advanced transitions

Montgomery, Matthew D.; Charron, Richard C.; Rodriguez, Jose L.; Kusters, Bernhard W.; Morrison, Jay A.; Beeck, Alexander R.

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A01 - agriculture
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Title: Swirling midframe flow for gas turbine engine having advanced transitions

Abstract

A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.

Inventors:: Montgomery, Matthew D.; Charron, Richard C.; Rodriguez, Jose L.; Kusters, Bernhard W.; Morrison, Jay A.; Beeck, Alexander R.

Issue Date:: 2016-12-27

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

Sponsoring Org.:: USDOE

OSTI Identifier:: 1337663

Patent Number(s):: 9528706

Application Number:: 14/105,313

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

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F04 - POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS F04D - NON-POSITIVE-DISPLACEMENT PUMPS

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS

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F - MECHANICAL ENGINEERING F04 - POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS F04D - NON-POSITIVE-DISPLACEMENT PUMPS
F04D29/542 - {Bladed diffusers
F04D29/545 - {Ducts}
F04D29/547 - {having a special shape in order to influence fluid flow}

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/02 - characterised by the air-flow or gas-flow configuration
F23R3/04 - Air inlet arrangements
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

Show less

DOE Contract Number:: FC26-05NT42644

Resource Type:: Patent

Resource Relation:: Patent File Date: 2013 Dec 13

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING

Citation Formats


                    Montgomery, Matthew D., Charron, Richard C., Rodriguez, Jose L., Kusters, Bernhard W., Morrison, Jay A., and Beeck, Alexander R. Swirling midframe flow for gas turbine engine having advanced transitions.  United States: N. p., 2016. 
        Web.

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                    Montgomery, Matthew D., Charron, Richard C., Rodriguez, Jose L., Kusters, Bernhard W., Morrison, Jay A., & Beeck, Alexander R. Swirling midframe flow for gas turbine engine having advanced transitions.  United States.

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                    Montgomery, Matthew D., Charron, Richard C., Rodriguez, Jose L., Kusters, Bernhard W., Morrison, Jay A., and Beeck, Alexander R. Tue .  
        "Swirling midframe flow for gas turbine engine having advanced transitions".  United States.  https://www.osti.gov/servlets/purl/1337663.

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@article{osti_1337663,

  title        = {Swirling midframe flow for gas turbine engine having advanced transitions},

  author       = {Montgomery, Matthew D. and Charron, Richard C. and Rodriguez, Jose L. and Kusters, Bernhard W. and Morrison, Jay A. and Beeck, Alexander R.},

  abstractNote = {A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2016},

  month        = {12}

}

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Works referenced in this record:

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patent, October 1958

Hall, James R.; Singelmann, Dietrich E.
US Patent Document 2857740
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Turbine engine with combustor premix system
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Gas turbine engine cooling airflow modulator
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Hull, Peter R.
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Gas turbine engine operating process
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Multi-zone diffuser for turbomachine
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Moussa, Zaher Milad
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Roberts, Douglas Allan; Leblanc, Andre; Kacker, Suresh Chandra
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Turbine engine having turbine cooled with diverted compressor intermediate pressure air
patent, November 2003

Liu, Xiaoliu
US Patent Document 6,647,730
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patent, April 2006

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patent, November 2010

Commaret, Patrice Andre; Hernandez, Didier Hippolyte; Locatelli, David
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Cooling structure for outer surface of a gas turbine case
patent, December 2011

Shteyman, Yevgeniy; Tsai, Frank; Marshall, James F.
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Similar Records

Title: Swirling midframe flow for gas turbine engine having advanced transitions

Abstract

Citation Formats

Turbojet Aircraft Engine with Thrust Augmentation patent, October 1958

Gas Turbine Power Plants Having Axial-Flow Compressors Incorporating Contrarotating Rotors patent, August 1970

Turbine engine with combustor premix system patent, February 1984

Gas turbine engine cooling airflow modulator patent, July 1984

Turbojet with contrarotating wheels patent, August 1984

Gas turbine engine operating process patent, July 1989

Multi-zone diffuser for turbomachine patent, August 1994

Gas turbine engine cooling supply circuit patent, September 1996

Deswirler system for centrifugal compressor patent, August 2001

Discrete passage diffuser patent, July 2003

Turbine engine having turbine cooled with diverted compressor intermediate pressure air patent, November 2003

Hybrid vane island diffuser patent, April 2006

System for ventilating a combustion chamber wall in a turbomachine patent, November 2010

Cooling structure for outer surface of a gas turbine case patent, December 2011

Turbine cooling air from a centrifugal compressor patent, January 2012

Diffuser-nozzle assembly for a turbomachine patent, March 2012

Assembly for directing combustion gas patent, October 2012

Combustion transition duct providing stage 1 tangential turning for turbine engines patent-application, January 2007

Modular Transvane Assembly patent-application, April 2010

Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method patent-application, May 2010

Assembly for directing combustion gas patent-application, August 2011

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

Turbojet Aircraft Engine with Thrust Augmentation
patent, October 1958

Gas Turbine Power Plants Having Axial-Flow Compressors Incorporating Contrarotating Rotors
patent, August 1970

Turbine engine with combustor premix system
patent, February 1984

Gas turbine engine cooling airflow modulator
patent, July 1984

Turbojet with contrarotating wheels
patent, August 1984

Gas turbine engine operating process
patent, July 1989

Multi-zone diffuser for turbomachine
patent, August 1994

Gas turbine engine cooling supply circuit
patent, September 1996

Deswirler system for centrifugal compressor
patent, August 2001

Discrete passage diffuser
patent, July 2003

Turbine engine having turbine cooled with diverted compressor intermediate pressure air
patent, November 2003

Hybrid vane island diffuser
patent, April 2006

System for ventilating a combustion chamber wall in a turbomachine
patent, November 2010

Cooling structure for outer surface of a gas turbine case
patent, December 2011

Turbine cooling air from a centrifugal compressor
patent, January 2012

Diffuser-nozzle assembly for a turbomachine
patent, March 2012

Assembly for directing combustion gas
patent, October 2012

Combustion transition duct providing stage 1 tangential turning for turbine engines
patent-application, January 2007

Modular Transvane Assembly
patent-application, April 2010

Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method
patent-application, May 2010

Assembly for directing combustion gas
patent-application, August 2011

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