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Title: Radial inlet guide vanes for a combustor

Patent ·
OSTI ID:1083208
; ; ;

A combustor may include an interior flow path therethrough, a number of fuel nozzles in communication with the interior flow path, and an inlet guide vane system positioned about the interior flow path to create a swirled flow therein. The inlet guide vane system may include a number of windows positioned circumferentially around the fuel nozzles. The inlet guide vane system may also include a number of inlet guide vanes positioned circumferentially around the fuel nozzles and adjacent to the windows to create a swirled flow within the interior flow path.

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):
8,371,101
Application Number:
12/559,522
OSTI ID:
1083208
Country of Publication:
United States
Language:
English

References (11)

Method and Means Relating to High Capacity Forced Draft Gas Burner Art patent June 1959
Gas turbine combustor swirl vane arrangement patent March 1995
Gas turbine combustor patent February 1996
Perfected combustion system with low polluting emissions for gas turbines patent August 1997
Combustor with two stage primary fuel tube with concentric members and flow regulating patent November 1999
Gas turbine combustion chamber with defined fuel input for the improvement of the homogeneity of the fuel-air mixture patent August 2006
Rotary ramjet turbo-generator patent March 2010
Mixer assembly patent August 2010
Partial premix dual circuit fuel injector patent-application November 2002
Mixer assembly for combustor of a gas turbine engine having a main mixer with improved fuel penetration patent-application February 2007
Methods and Systems to Facilitate Reducing Combustion Systems patent-application December 2009

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