A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

A gas turbine engine including: a rotor mounted for rotation about an axis defining proximal and distal directions; a compressor coupled to the rotor; a turbine coupled to the rotor and disposed distally from the compressor; a combustion chamber; a gas turbine exhaust; and a recuperator comprising: an annular heat exchanger comprising: an axial intake disposed at a distal end of the heat exchanger and an axial exhaust disposed at a proximal end of the heat exchanger; and a radial intake disposed at a proximal end of an inner radius of the heat exchanger and a radial exhaust disposed at a distal end of the inner radius of the heat exchanger, wherein the heat exchanger defines a first flow path between the axial intake and the axial exhaust and a second flow path between the radial intake and the radial exhaust .

A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

A system comprises a gas turbine engine. The gas turbine engine has a flow diffuser system, a combustor, a modified compressor section, and a turbine coupled to a shaft. The system includes a low pressure intercooled compressor, a high pressure intercooled compressor, a recuperator, and a compressed air storage tank. The compressed air storage tank is in selective fluid communication with the low pressure intercooled compressor via the high pressure intercooled compressor, and the recuperator. The high pressure intercooled compressor is configured to selectively receive compressed air from the low pressure intercooled compressor and is further configured to selectively compress the compressed air to a highly compressed air for storage in the compressed air storage tank. Each of the compressed air storage tank and the low pressure intercooled compressor is selectively and fluidly coupled to the gas turbine engine.

A heat exchanger for a gas turbine engine comprising a compressor, a combustor and a turbine. The heat exchanger comprising alternating hot and cold channels. Compressed air from the compressor flows through the cold channels and exhaust gas from the turbine flows through the hot channels. Each cold channel comprises first and second opposing surfaces conveying compressed air along a first path. Each cold channel comprises rows of vortex generators and pin fins extending from the first or second surfaces along the first path. The rows extend substantially perpendicular to the first path. Each hot channel is defined by a first and second opposing surfaces conveying exhaust gas along a second path substantially perpendicular to the first path. Each hot channel comprises rows of vortex generators and pin fins extending from the first or second surfaces along the second path. The rows extend substantially perpendicularly to the second path.

The present disclosure relates to systems and methods that provide power generation using predominantly CO.sub.2 as a working fluid. In particular, the present disclosure provides for the use of a portion of the heat of compression from a CO.sub.2 compressor as the additive heating necessary to increase the overall efficiency of a power production system and method.

The present disclosure relates to systems and methods that provide power generation using predominantly CO.sub.2 as a working fluid. In particular, the present disclosure provides for the use of a portion of the heat of compression from a CO.sub.2 compressor as the additive heating necessary to increase the overall efficiency of a power production system and method.