Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

The electrical power generation system including a micro-turbine alternator. The micro-turbine alternator including a combustor, at least one turbine configured to be driven by an exhaust from the combustor, at least one compressor operably connected to the combustor to provide a compressed airflow to the combustor, one or more shafts connecting the at least one turbine to the at least one compressor such that rotation of the at least one turbine drives rotation of the at least one compressor, and a recuperator configured to transfer heat from the exhaust exiting the at least one turbine to the compressed airflow from the at least one compressor entering the combustor.

Various embodiments relate to combined heat and power (CHP) systems. A CHP system can include a turbine system, a turbocharger system, and a refrigeration system. The refrigeration system can receive combustion products from the turbine system and compressed air from the turbocharger system. The refrigeration system can cool the combustion products and the compressed air to generate a cooled combustion product mixture that is provided to the turbine system.

Various embodiments relate to combined heat and power (CHP) systems. A CHP system can include a turbine system, a turbocharger system, and a refrigeration system. The refrigeration system can receive combustion products from the turbine system and compressed air from the turbocharger system. The refrigeration system can cool the combustion products and the compressed air to generate a cooled combustion product mixture that is provided to the turbine system.

An exhaust energy recovery system (EERS) and associated methods for an engine are disclosed. An embodiment of an EERS, for example, includes an inlet duct that is configured to divert exhaust gas from an exhaust duct of the engine into the recovery system and an outlet duct configured to return the exhaust gas to the exhaust duct downstream of the inlet duct. The recovery system is configured to heat components or fluids associated with engine to operating temperatures. The recovery system may be part of a mobile power system that is mounted to a single trailer and includes an engine and a power unit such as a high pressure pump or generator mounted to the trailer. Methods of operating and purging recovery systems are also disclosed.

An exhaust energy recovery system (EERS) and associated methods for an engine are disclosed. An embodiment of an EERS, for example, includes an inlet duct that is configured to divert exhaust gas from an exhaust duct of the engine into the recovery system and an outlet duct configured to return the exhaust gas to the exhaust duct downstream of the inlet duct. The recovery system is configured to heat components or fluids associated with engine to operating temperatures. The recovery system may be part of a mobile power system that is mounted to a single trailer and includes an engine and a power unit such as a high pressure pump or generator mounted to the trailer. Methods of operating and purging recovery systems are also disclosed.

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 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 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 hybrid airbreathing rocket engine module (70) comprises an air intake arrangement (62) configured to receive air and a heat exchanger arrangement (63) configured to cool air from the air intake arrangement (62); a compressor (64) configured to compress air from the heat exchanger arrangement (63); and one or more thrust chambers (65). The air intake arrangement (62), the compressor (64), the heat exchanger arrangement (63), and the one or more thrust chambers (65) are arranged generally along an axis (69) of the engine module (70). The heat exchanger arrangement (63) is arranged between the compressor (64) and the one or more thrust chambers (65).