Gas turbine combustor transition

Title: Gas turbine combustor transition

Full Record
Other Related Research

Abstract

A method of converting a steam cooled transition to an air cooled transition in a gas turbine having a compressor in fluid communication with a combustor, a turbine section in fluid communication with the combustor, the transition disposed in a combustor shell and having a cooling circuit connecting a steam outlet and a steam inlet and wherein hot gas flows from the combustor through the transition and to the turbine section, includes forming an air outlet in the transition in fluid communication with the cooling circuit and providing for an air inlet in the transition in fluid communication with the cooling circuit.

Inventors:

Coslow, Billy Joe ^[1]; Whidden, Graydon Lane ^[2]

Winter Park, FL
Great Blue, CT

Publication Date:: 1999-01-01

Research Org.:: Westinghouse Electric Corp., Pittsburgh, PA (United States)

OSTI Identifier:: 872296

Patent Number(s):: US 5906093

Assignee:: Siemens Westinghouse Power Corporation (Orlando, FL)

DOE Contract Number:: FC21-95MC32267

Resource Type:: Patent

Country of Publication:: United States

Language:: English

Subject:: gas; turbine; combustor; transition; method; converting; steam; cooled; air; compressor; fluid; communication; section; disposed; shell; cooling; circuit; connecting; outlet; inlet; hot; flows; forming; providing; turbine section; gas flows; gas flow; gas turbine; fluid communication; hot gas; air inlet; cooling circuit; steam cooled; air outlet; air cooled; steam outlet; turbine combustor; cooled transition; /60/

Citation Formats


                    Coslow, Billy Joe, and Whidden, Graydon Lane. Gas turbine combustor transition.  United States: N. p., 1999. 
        Web.

Copy to clipboard


                    Coslow, Billy Joe, & Whidden, Graydon Lane. Gas turbine combustor transition.  United States.

Copy to clipboard


                    Coslow, Billy Joe, and Whidden, Graydon Lane. Fri .  
        "Gas turbine combustor transition".  United States.  https://www.osti.gov/servlets/purl/872296.

Copy to clipboard


                    
@article{osti_872296,

  title        = {Gas turbine combustor transition},

  author       = {Coslow, Billy Joe and Whidden, Graydon Lane},

  abstractNote = {A method of converting a steam cooled transition to an air cooled transition in a gas turbine having a compressor in fluid communication with a combustor, a turbine section in fluid communication with the combustor, the transition disposed in a combustor shell and having a cooling circuit connecting a steam outlet and a steam inlet and wherein hot gas flows from the combustor through the transition and to the turbine section, includes forming an air outlet in the transition in fluid communication with the cooling circuit and providing for an air inlet in the transition in fluid communication with the cooling circuit.},

  doi          = {},

  url          = {https://www.osti.gov/biblio/872296},
  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {1999},

  month        = {1}

}

Copy to clipboard

Patent:

View Patent

Save / Share:

Export Metadata

Save to My Library

Similar records in OSTI.GOV collections:

Gas turbine combustor transition

Patent Coslow, B J ; Whidden, G L

A method is described for converting a steam cooled transition to an air cooled transition in a gas turbine having a compressor in fluid communication with a combustor, a turbine section in fluid communication with the combustor, the transition disposed in a combustor shell and having a cooling circuit connecting a steam outlet and a steam inlet and wherein hot gas flows from the combustor through the transition and to the turbine section, includes forming an air outlet in the transition in fluid communication with the cooling circuit and providing for an air inlet in the transition in fluid communicationmore » with the cooling circuit. 7 figs.« less
Gas turbine cooling system

Patent Bancalari, Eduardo E

A gas turbine engine (10) having a closed-loop cooling circuit (39) for transferring heat from the hot turbine section (16) to the compressed air (24) produced by the compressor section (12). The closed-loop cooling system (39) includes a heat exchanger (40) disposed in the flow path of the compressed air (24) between the outlet of the compressor section (12) and the inlet of the combustor (14). A cooling fluid (50) may be driven by a pump (52) located outside of the engine casing (53) or a pump (54) mounted on the rotor shaft (17). The cooling circuit (39) may includemore »« less
Full Text Available
Gas turbine annular combustor with radial dilution air injection

Patent Shekelton, J R ; Johnson, D C

This patent describes a radial flow gas turbine. It comprises: a rotor including turbine blades and a nozzle adjacent the turbine blades, the nozzle being adapted to direct hot gases at the turbine blades to cause rotation of the rotor; an annular combustor about the rotor and having a combustor outlet leading to the nozzle, the annular combustor having spaced inner and outer walls connected by a generally radially extending wall, the annular combustor including a combustion annulus defined by the inner, outer and radially extending walls upstream of the outlet; a dilution air annulus disposed downstream of the combustionmore »« less
Annular combustor for a turbine engine without film cooling

Patent Shekleton, J R ; Lafferty, M K

This patent describes a gas turbine engine. It comprises a rotary compressor; a turbine wheel coupled to the compressor to drive the same; an annular nozzle in proximity to the turbine wheel and having a plurality of vanes disposed to direct gases of combustion at the turbine wheel, the vanes having leading edges remote from the turbine wheel and trailing edges adjacent the turbine wheel; an annular combustor having a radially outer wall, a radially inner wall spaced therefrom and a radially extending wall interconnecting the inner and outer walls remote from the nozzle, the inner and outer walls, atmore »« less
Swirling midframe flow for gas turbine engine having advanced transitions

Patent Montgomery, Matthew D. ; Charron, Richard C. ; Rodriguez, Jose L. ; ...

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) configuredmore »« less
Full Text Available

Similar Records