skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: Transition duct with late injection in turbine system

Patent ·
OSTI ID:1215539
; ; ; ;

A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber.

Research Organization:
General Electric Co., Schenectady, NY (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42643
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
9,133,722
Application Number:
13/459,516
OSTI ID:
1215539
Resource Relation:
Patent File Date: 2012 Apr 30
Country of Publication:
United States
Language:
English

References (36)

Aft mounting system for combustion transition duct members patent December 1983
Profile matched diffuser patent January 1992
Leaf seals patent June 1992
Gas turbine vane assembly seal and support system patent September 1992
Turbine nozzle seal arrangement patent October 1993
Integral aft frame mount for a gas turbine combustor transition piece patent May 1995
Rolling contact mounting arrangement for a ceramic combustor patent October 1995
Gas turbine diffuser patent January 1997
Transition piece external frame support patent June 1998
Catalytic combustor with lean direct injection of gas fuel for low emissions combustion and methods of operation patent October 1998
Mixing ducts for a gas-turbine annular combustion chamber patent November 1998
Gas-path leakage seal for a turbine patent August 1999
Interstage van seal apparatus patent June 2000
Tangentially aligned pre-mixing combustion chamber for a gas turbine patent March 2001
Seal patent March 2001
Leaf seal for inner and outer casings of a turbine patent August 2002
Seal between static turbine parts patent August 2002
Three degrees of freedom aft mounting system for gas turbine transition duct patent September 2002
Integrated duct diffuser patent October 2002
Supplemental seal for the chordal hinge seal in a gas turbine patent March 2003
Apparatus for forming a combustion mixture in a gas turbine engine patent May 2003
Leaf seal support for inner band of a turbine nozzle in a gas turbine engine patent November 2003
Transition duct mounting system patent December 2003
Transition piece outlet structure enabling to reduce the temperature, and a transition piece, a combustor and a gas turbine providing the above output structure patent August 2004
Multi-axial pivoting combustor liner in gas turbine engine patent March 2006
Combustor attachment with rotational joint patent April 2006
Diffuser for gas turbine engine patent February 2007
Support system for transition ducts patent September 2009
Methods and apparatuses for assembling a gas turbine engine patent December 2009
Secondary fuel delivery system patent February 2010
Combustion transition duct providing stage 1 tangential turning for turbine engines patent May 2010
Transition with a linear flow path with exhaust mouths for use in a gas turbine engine patent-application February 2010
Transition with a linear flow path for use in a gas turbine engine patent-application February 2010
Canted Outlet for Transition in a Gas Turbine Engine patent-application February 2010
Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method patent-application May 2010
Structural Attachment System for Transition Duct Outlet patent-application July 2010

Similar Records

Related Subjects

33 ADVANCED PROPULSION SYSTEMS