Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section

Rodriguez, Jose L.

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Title: Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section

Abstract

A midframe portion (113) of a gas turbine engine (110) is provided, including a compressor section (112) with a last stage blade (124). The compressor section (112) is configured to introduce a radial velocity component into an air flow (111) such that the air flow is discharged from the compressor section (112) at a mixed direction based on a combined longitudinal velocity component and radial velocity component. The midframe portion (113) further includes a manifold (121) to directly couple the air flow from an outlet of the compressor section (112) to an inlet of a respective combustor head (118) of the gas turbine engine (110).

Inventors:: Rodriguez, Jose L.

Issue Date:: 2018-07-03

Research Org.:: Siemens Energy, Inc., Orlando, FL (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1461514

Patent Number(s):: 10012098

Application Number:: 13/407,987

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

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F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D9/041 - {using blades

F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C3/14 - characterised by the arrangement of the combustion chamber in the plant

F - MECHANICAL ENGINEERING F04 - POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS F04D - NON-POSITIVE-DISPLACEMENT PUMPS
F04D29/44 - Fluid-guiding means, e.g. diffusers
F04D29/54 - Fluid-guiding means, e.g. diffusers

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

Citation Formats


                    Rodriguez, Jose L. Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section.  United States: N. p., 2018. 
        Web.

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                    Rodriguez, Jose L. Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section.  United States.

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                    Rodriguez, Jose L. Tue .  
        "Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section".  United States.  https://www.osti.gov/servlets/purl/1461514.

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@article{osti_1461514,

  title        = {Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section},

  author       = {Rodriguez, Jose L.},

  abstractNote = {A midframe portion (113) of a gas turbine engine (110) is provided, including a compressor section (112) with a last stage blade (124). The compressor section (112) is configured to introduce a radial velocity component into an air flow (111) such that the air flow is discharged from the compressor section (112) at a mixed direction based on a combined longitudinal velocity component and radial velocity component. The midframe portion (113) further includes a manifold (121) to directly couple the air flow from an outlet of the compressor section (112) to an inlet of a respective combustor head (118) of the gas turbine engine (110).},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2018},

  month        = {7}

}

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Similar Records

Title: Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section

Abstract

Citation Formats

Turbine patent, March 1946

Arrangement of Jet Propulsion Engine Elements patent, July 1948

Combustion Gas Turbine Arrangement patent, June 1949

Gas turbine power plant patent, September 1951

Gas Turbine Engine with Resonating Combustion Chambers patent, April 1952

Boundary Layer Energizing Means for Annular Diffusers patent, April 1952

Gas Turbine Power Plant with Diverse Combustion and Diluent Air Paths patent, January 1953

Combustion Means for Jet Propulsion Units patent, February 1953

Gas Turbine Engine patent, August 1953

Gas Turbine patent, December 1953

Radiator Matrix Design patent, January 1961

Combustion Section for a Gas Turbine Engine patent, February 1962

Gas Turbine Engine patent, July 1962

Gas Turbine Engine patent, May 1963

Compressors for Gas Turbine Engines patent, December 1970

Gas turbine engine structure patent, June 1973

Turbomachinery and Method of Manufacturing Diffusers Therefor patent, August 1974

Premixed combustor patent, April 1978

Small diameter gas turbine engine patent, May 1993

Gas generating apparatus patent, June 1994

Turbine engine with cooled P3 air to impeller rear cavity patent, March 2000

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

Diffuser for Gas Turbine System patent-application, November 2011

Turbine
patent, March 1946

Arrangement of Jet Propulsion Engine Elements
patent, July 1948

Combustion Gas Turbine Arrangement
patent, June 1949

Gas turbine power plant
patent, September 1951

Gas Turbine Engine with Resonating Combustion Chambers
patent, April 1952

Boundary Layer Energizing Means for Annular Diffusers
patent, April 1952

Gas Turbine Power Plant with Diverse Combustion and Diluent Air Paths
patent, January 1953

Combustion Means for Jet Propulsion Units
patent, February 1953

Gas Turbine Engine
patent, August 1953

Gas Turbine
patent, December 1953

Radiator Matrix Design
patent, January 1961

Combustion Section for a Gas Turbine Engine
patent, February 1962

Gas Turbine Engine
patent, July 1962

Gas Turbine Engine
patent, May 1963

Compressors for Gas Turbine Engines
patent, December 1970

Gas turbine engine structure
patent, June 1973

Turbomachinery and Method of Manufacturing Diffusers Therefor
patent, August 1974

Premixed combustor
patent, April 1978

Small diameter gas turbine engine
patent, May 1993

Gas generating apparatus
patent, June 1994

Turbine engine with cooled P3 air to impeller rear cavity
patent, March 2000

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

Diffuser for Gas Turbine System
patent-application, November 2011