A process for regasifying a fluid and producing electrical energy includes subjecting a working fluid to 1) high-pressure pumping, 2) heating in a recovery unit to obtain a heated flow, the heating step comprising a low-temperature heat recovery step 2a) and a high-temperature heat recovery step 2b), 3) further heating to obtain a further heated flow, 4) expanding in a turbine, with production of electrical energy, to obtain an expanded flow, 5) cooling in a recovery unit by heat exchange, in a step 5a) with the flow of step 2b) and in a step 5b) with the flow of step 2a) to obtain a cooled flow, 6) expanding with production of mechanical energy, and 7) condensing the flow of working fluid. After step 5), a portion of the flow of working fluid is not subjected to step 6) and is subjected to a recompressing step.

A process for regasifying a fluid and producing electrical energy includes subjecting a working fluid to 1) high-pressure pumping, 2) heating in a recovery unit to obtain a heated flow, the heating step comprising a low-temperature heat recovery step 2a) and a high-temperature heat recovery step 2b), 3) further heating to obtain a further heated flow, 4) expanding in a turbine, with production of electrical energy, to obtain an expanded flow, 5) cooling in a recovery unit by heat exchange, in a step 5a) with the flow of step 2b) and in a step 5b) with the flow of step 2a) to obtain a cooled flow, 6) expanding with production of mechanical energy, and 7) condensing the flow of working fluid. After step 5), a portion of the flow of working fluid is not subjected to step 6) and is subjected to a recompressing step.

A method for starting a turbine engine in cold weather, including a starting system intended for rotating a drive shaft of the turbine engine. The method includes the following steps: a pre-starting step in which a first starting signal is generated to control the drive shaft in a first direction of rotation about a longitudinal axis and in a second opposite direction of rotation in an alternating manner; and a starting step in which a second starting signal is transmitted to the starting system in order for the latter to drive the drive shaft of the turbine engine in a normal direction of rotation and in which the drive shaft is rotated until a rotation speed that causes the turbine engine to start.

A method for starting a turbine engine in cold weather, including a starting system intended for rotating a drive shaft of the turbine engine. The method includes the following steps: a pre-starting step in which a first starting signal is generated to control the drive shaft in a first direction of rotation about a longitudinal axis and in a second opposite direction of rotation in an alternating manner; and a starting step in which a second starting signal is transmitted to the starting system in order for the latter to drive the drive shaft of the turbine engine in a normal direction of rotation and in which the drive shaft is rotated until a rotation speed that causes the turbine engine to start.

A compact heat exchanger is disclosed for re-circulating bleed air from a combustor into an inlet and/or exhaust of a gas turbine engine. In an embodiment, the heat exchanger may comprise a plurality of airfoils with internal passages that receive bleed air. The bleed air may be forced through outlets in one or a plurality of concentric passages from the internal passage of each airfoil to an internal cavity of each airfoil, and out of micro-holes within a trailing surface of the airfoil. This enables bleed air to be mixed with gas flowing through the airfoils, in close proximity to the compressor or turbine of the gas turbine engine, while providing acoustic noise suppression and low thermal mixing stratification.

A system for warming a power generation system including a boiler and a mixer fluidly coupled to the boiler, a turbine first section operable to receive steam from the boiler at a first temperature. The turbine supplies steam at a second temperature to a first heat exchanger operably connected to receive the heated steam at the second temperature from the output of at least the first section of the turbine and transfer heat to at least one of water and steam in the boiler or the mixer, feedwater for the boiler, and a thermal energy storage system. The system further includes a control unit configured to receive the monitored operating characteristic and control the amount of steam directed through the turbine.

A system for warming a power generation system including a boiler and a mixer fluidly coupled to the boiler, a turbine first section operable to receive steam from the boiler at a first temperature. The turbine supplies steam at a second temperature to a first heat exchanger operably connected to receive the heated steam at the second temperature from the output of at least the first section of the turbine and transfer heat to at least one of water and steam in the boiler or the mixer, feedwater for the boiler, and a thermal energy storage system. The system further includes a control unit configured to receive the monitored operating characteristic and control the amount of steam directed through the turbine.

A heating system for heating a component in a liquid distribution system of an aircraft engine. The liquid distribution system feeds a liquid to the component. The heating system includes an acoustic generator disposed in communication with the component via a liquid passage of the liquid distribution system. The liquid passage defines a length between the acoustic generator and the component. The acoustic generator generates a resonant frequency selected as a function of the length of the liquid passage to generate a standing wave in the liquid within the liquid passage. The standing wave transmitting energy to the component to heat the component.

An integral cooling system for a turbine casing and guide vanes in an aeroengine is provided, belonging to the field of research on flow and heat exchange of a turbine casing in an aeroengine. An inner guide ring and multiple of guide vanes are mounted on the turbine casing; the cooling system includes an electromagnetic pump, a heat exchanger, an expansion joint and a cooling pipeline; an annular cavity is provided in the turbine casing, the cooling pipeline is mounted on the inner wall of the annular cavity and periodically and uniformly distributed along the circumferential direction of the turbine casing, and the cooling pipeline is filled with cooling liquid; a mounting cavity is further provided in the turbine casing, and the mounting cavity communicates with the annular cavity; the electromagnetic pump, the expansion joint and the heat exchanger are all mounted in the mounting cavity.

An integral cooling system for a turbine casing and guide vanes in an aeroengine is provided, belonging to the field of research on flow and heat exchange of a turbine casing in an aeroengine. An inner guide ring and multiple of guide vanes are mounted on the turbine casing; the cooling system includes an electromagnetic pump, a heat exchanger, an expansion joint and a cooling pipeline; an annular cavity is provided in the turbine casing, the cooling pipeline is mounted on the inner wall of the annular cavity and periodically and uniformly distributed along the circumferential direction of the turbine casing, and the cooling pipeline is filled with cooling liquid; a mounting cavity is further provided in the turbine casing, and the mounting cavity communicates with the annular cavity; the electromagnetic pump, the expansion joint and the heat exchanger are all mounted in the mounting cavity.