Gary Victor Hildebrandt

US Patent:

20070101724, May 10, 2007

Filed:

Nov 10, 2005

Appl. No.:

11/272226

Inventors:

Satish Gadde - Orlando FL, US
Damien Teehan - St. Cloud FL, US
Jatinder Singh - Orlando FL, US
Gary Hildebrandt - Oviedo FL, US
Danny Kozachuk - Oviedo FL, US
Joseph Kollar - Orlando FL, US

International Classification:

F02C 9/26

US Classification:

060773000, 060039281

Abstract:

A method of controlling fuel flow to a combustor () of a gas turbine engine () during startup of the engine includes determining a relationship between Cand valve position for a flow control valve (e.g., ) in a fuel supply () to the combustor as a function of at least one real time parameter of fuel () in the fuel supply. The method also includes determining a value of the at least one parameter of the fuel before initiating a flow of the fuel to the combustor, and then calculating a first actual Cvalue for the flow control valve at a target flow rate using the determined value of the parameter. The method then includes positioning the flow control valve to a first position corresponding to the actual Cvalue based upon the determined relationship between Cand valve position, and initiating the flow of fuel to the combustor through the flow control valve.

US Patent:

20110094241, Apr 28, 2011

Filed:

Oct 7, 2010

Appl. No.:

12/899837

Inventors:

Shervin Rodd - Chuluota FL, US
Adam M. Foust - Orlando FL, US
Gary V. Hildebrandt - Oviedo FL, US
Damien G. Teehan - St. Cloud FL, US

International Classification:

F02C 7/26

US Classification:

60778

Abstract:

A starting process for a gas turbine () that holds the turbine speed of rotation at an ignition speed setting during an ignition window (), with the ignition speed setting being based on ambient air conditions to achieve a specified combustor air mass flow rate (). A fuel flow rate may be set based on the fuel type and temperature to achieve a particular air/fuel ratio in a combustor. The fuel flow rate may be adjusted during the ignition window and thereafter based on a combustor inlet air temperature (). Completion of ignition may be determined by a reduction () in a blade path temperature spread (). After ignition, fuel flow is increased to accelerate the turbine to full speed. At any point, the fuel flow may be reduced, or its increase may be slowed, to avoid exceeding a temperature limit in the turbine.