Abstract: A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section includes at least one first opening and at least one second opening. The compressor assembly is located in the compressor section to define with the compressor section a compressor apparatus to compress air. The at least one combustor assembly is coupled to the combustor section to define with the combustor section a combustor apparatus. The turbine assembly is located in the turbine section to define with the turbine section a turbine apparatus.

Abstract: A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section includes at least one first opening and at least one second opening. The compressor assembly is located in the compressor section to define with the compressor section a compressor apparatus to compress air. The at least one combustor assembly is coupled to the combustor section to define with the combustor section a combustor apparatus. The turbine assembly is located in the turbine section to define with the turbine section a turbine apparatus.

Abstract: Hybrid combustion power systems comprising multiple direct energy conversion devices are disclosed, which devices (12, 14, 16) are preferably combined with a Rankine cycle containing a steam turbine (114), where combustion air (A) may be continuously preheated by an optional air heater (58), then by the waste heat of a low temperature direct energy conversion device (16) such as an alkali metal thermoelectric converter (AMTEC), and finally by the waste heat of a high temperature direct energy conversion device (12) such as an AMTEC, where the AMTECs include electrolyte (36) may include a condenser located in substantially the same geometrical plane as the AMTEC electrolyte (36) and thermally insulated from the electrolyte.

Abstract: A combustion turbine having a compressed air cooling circuit that is connected to a nitrogen source. Compressed air is provided to the cooling circuit upon start-up and gradually switched to nitrogen cooling, as the nitrogen becomes available. Transition from compressed air to nitrogen cooling is supplied to the hottest components first in accordance with a pre-selected control scheme. Upon shutdown of the plant, the process is reversed.

Abstract: Hybrid combustion power systems comprising multiple direct energy conversion devices are disclosed, which devices (12,14,16) are preferably combined with a Rankine cycle containing a steam turbine (114), where combustion air (A) may be continuously preheated by an optional air heater (58), then by the waste heat of a low temperature direct energy conversion device (16) such as an alkali metal thermoelectric converter (AMTEC), and finally by the waste heat of a high temperature direct energy conversion device (12) such as an AMTEC, where the AMTECs include electrolyte (36) may include a condenser located in substantially the same geometrical plane as the AMTEC electrolyte (36) and thermally insulated from the electrolyte.

Abstract: A flow balanced gas turbine power plant is provided which includes a primary power plant and a secondary power plant. The primary power plant has a primary compressor assembly, a primary combustor assembly, a primary turbine assembly, and a primary generator. The secondary power plant has a secondary combustor assembly, a secondary turbine assembly, and a secondary generator. A flow path extends through the primary compressor assembly, primary combustor assembly and primary turbine assembly. Another flow path extends through the primary compressor assembly, secondary combustor assembly and secondary turbine assembly. The primary compressor assembly provides compressed air to both the primary combustor assembly and the secondary combustor assembly.