Abstract: An interface (10) is provided between a combustor basket (12) and a transition (14) of a gas turbine engine (16). The interface (10) includes a tongue (18) formed in one of the combustor basket (12) and the transition (14), and a groove (20) formed in another of the combustor basket (12) and the transition (14). The tongue (18) is received within the groove (20) to define the interface (10). A sealing arrangement is also provided and includes an annular combustion outlet (12??) and an annular transition inlet (14??), with a labyrinth seal (72??) positioned between an end (68??) of the annular combustion outlet and an end (70??) of the annular transition inlet to form a labyrinth path (34??) there between. An inner diameter (24??) of the annular combustion outlet (12??) is axially aligned with an inner diameter (22??) of the annular transition outlet (14??).

Abstract: A starting process for a gas turbine (28) that holds the turbine speed of rotation at an ignition speed setting during an ignition window (58), with the ignition speed setting being based on ambient air conditions to achieve a specified combustor air mass flow rate (52). 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 (46). Completion of ignition may be determined by a reduction (68) in a blade path temperature spread (66). 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.

Abstract: An ignition system for a combustor of a gas turbine engine is disclosed. The ignition system may include multiple igniters to reduce the likelihood of system failure. In at least one embodiment, the ignition system may be formed from a first igniter formed from an outer electrode containing at least one central electrode at a distal end of the outer electrode and may include a second igniter. The second igniter may be formed from a central electrode positioned within the outer electrode forming the first igniter. During operation, the igniters may spark to ignite the fuel mixture within the combustor.

Abstract: A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.

Abstract: An interface (10) is provided between a combustor basket (12) and a transition (14) of a gas turbine engine (16). The interface (10) includes a tongue (18) formed in one of the combustor basket (12) and the transition (14), and a groove (20) formed in another of the combustor basket (12) and the transition (14). The tongue (18) is received within the groove (20) to define the interface (10). A sealing arrangement is also provided and includes an annular combustion outlet (12??) and an annular transition inlet (14??), with a labyrinth seal (72??) positioned between an end (68??) of the annular combustion outlet and an end (70??) of the annular transition inlet to form a labyrinth path (34??) there between. An inner diameter (24??) of the annular combustion outlet (12??) is axially aligned with an inner diameter (22??) of the annular transition outlet (14??).

Abstract: A starting process for a gas turbine (28) that holds the turbine speed of rotation at an ignition speed setting during an ignition window (58), with the ignition speed setting being based on ambient air conditions to achieve a specified combustor air mass flow rate (52). 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 (46). Completion of ignition may be determined by a reduction (68) in a blade path temperature spread (66). 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.

Abstract: A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.