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Title: Self-regulating fuel staging port for turbine combustor

Patent ·
OSTI ID:1143661
; ;

A port (60) for axially staging fuel and air into a combustion gas flow path 28 of a turbine combustor (10A). A port enclosure (63) forms an air path through a combustor wall (30). Fuel injectors (64) in the enclosure provide convergent fuel streams (72) that oppose each other, thus converting velocity pressure to static pressure. This forms a flow stagnation zone (74) that acts as a valve on airflow (40, 41) through the port, in which the air outflow (41) is inversely proportion to the fuel flow (25). The fuel flow rate is controlled (65) in proportion to engine load. At high loads, more fuel and less air flow through the port, making more air available to the premixing assemblies (36).

Research Organization:
Siemens Energy, Inc., Orlando, FL (USA)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42644
Assignee:
Siemens Energy, Inc. (Orlando, FL)
Patent Number(s):
8,769,955
Application Number:
12/791,975
OSTI ID:
1143661
Country of Publication:
United States
Language:
English

References (19)

Combustion liner air valve patent January 1976
Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones patent August 1976
Hybrid combustor with staged injection of pre-mixed fuel patent September 1978
Staged lean premix low nox hot wall gas turbine combustor with improved turndown capability patent March 1990
Staged low NOx premix gas turbine combustor patent May 1990
Combustor liner with air staging for NOx control patent July 1990
Dilution pole combustor and method patent August 1993
Combustor cap assembly for a combustor casing of a gas turbine patent October 1994
Low emission combustor having tangential lean direct injection patent January 1996
Premixing dry low NOx emissions combustor with lean direct injection of gas fuel patent April 2000
Apparatus and method for replacement of combustor basket swirlers patent July 2002
Device in a burner for gas turbines patent August 2003
Gas-turbine engine combustor patent April 2004
Turbine combustor transition piece having dilution holes patent May 2008
Augmenter swirler pilot patent October 2008
Vortex combustor for low NOx emissions when burning lean premixed high hydrogen content fuel patent October 2009
Axially staged combustion system for a gas turbine engine patent December 2009
Low emissions gas turbine combustor patent-application January 2009
Fuel Nozzle Assembly for Use in a Combustor of a Gas Turbine Engine patent-application March 2011

Cited By (2)

System for cooling a fuel injector extending into a combustion gas flow field and method for manufacture patent January 2017
Trapped vortex fuel injector and method for manufacture patent December 2016

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33 ADVANCED PROPULSION SYSTEMS