The invention is directed to a process to obtain a compressed gas starting from a starting gas having a lower pressure by performing the following steps: (i) increasing the pressure and temperature of a gas having an intermediate pressure by means of indirect heat exchange against a fluid having a higher temperature to obtain a gas high in pressure and temperature, (ii) obtaining part of the gas high in temperature and pressure as the compressed gas, (iii) using another part of the gas high in temperature and pressure as a driving gas to increase the pressure of the starting gas in one or more stages to obtain the gas having an intermediate pressure for use in step (i). The invention is also directed to a configuration wherein the process can be performed and directed to a process to generate energy using the process.

A gas turbine engine recuperator recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine.

A gas turbine engine recuperator recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine.

A heat exchange system includes a tubular fan air inlet portion and a tubular cooled air outlet portion connected to a first end of a tubular mid portion. The heat exchange system further includes a tubular hot air inlet portion and a tubular recycled fan air outlet portion connected a second end of the mid portion. Still further, the heat exchange system includes an integrally-formed, compliant heat exchanger tube extending between the hot air inlet portion and the cooled air outlet portion within the mid portion to define a heat exchanger first flow passage within the heat exchanger tube and a second flow passage outside of the heat exchanger tube but within the tubular mid portion. Methods for fabricating such heat exchange systems are also provided.

A heat exchange system includes a tubular fan air inlet portion and a tubular cooled air outlet portion connected to a first end of a tubular mid portion. The heat exchange system further includes a tubular hot air inlet portion and a tubular recycled fan air outlet portion connected a second end of the mid portion. Still further, the heat exchange system includes an integrally-formed, compliant heat exchanger tube extending between the hot air inlet portion and the cooled air outlet portion within the mid portion to define a heat exchanger first flow passage within the heat exchanger tube and a second flow passage outside of the heat exchanger tube but within the tubular mid portion. Methods for fabricating such heat exchange systems are also provided.

In a gas turbine and a control method thereof, and a combined cycle plant, the gas turbine includes a compressor that compresses air, a combustor that mixes and combusts compressed air compressed by the compressor and fuel, a turbine that obtains rotational power using combustion gas generated by the combustor, a compressed air cooling heat exchanger that cools the compressed air to produce air for heat exchange, air temperature adjusting heat exchangers that exchange heat between the air and the compressed air, a heat exchange amount adjusting device that adjusts a heat exchange amount of each of the compressed air cooling heat exchanger and the air temperature adjusting heat exchangers, and a control device that controls the heat exchange amount adjusting device, in which the control device controls the heat exchange amount adjusting device based on a temperature of the air to be taken into the compressor.

In a gas turbine and a control method thereof, and a combined cycle plant, the gas turbine includes a compressor that compresses air, a combustor that mixes and combusts compressed air compressed by the compressor and fuel, a turbine that obtains rotational power using combustion gas generated by the combustor, a compressed air cooling heat exchanger that cools the compressed air to produce air for heat exchange, air temperature adjusting heat exchangers that exchange heat between the air and the compressed air, a heat exchange amount adjusting device that adjusts a heat exchange amount of each of the compressed air cooling heat exchanger and the air temperature adjusting heat exchangers, and a control device that controls the heat exchange amount adjusting device, in which the control device controls the heat exchange amount adjusting device based on a temperature of the air to be taken into the compressor.

A system may include a turbine and a recuperative heat exchanger system. The recuperative heat exchanger system is configured to receive exhaust gases from the turbine. The recuperative heat exchanger system may include a precool section to cool the exhaust gases, a major heating section to receive the cooled the exhaust gases, and a minor heating section to receive the cooled the exhaust gases.

The present invention is a system, method and computer program for operating a land-or marine-based multi-spool gas turbine system for generating electrical power to supply a load, wherein the system comprises a multi-spool gas turbine engine, and the method comprises controlling the rotational speeds of the at least two generators independently of each other so as to directly control the rotational speeds of the shafts of the spools, the at last two generators being operable to generate electrical current to supply the load, and regulating the amount of heat generated the first heat generating equipment. A computer program to perform the method is also disclosed.

The present invention is a system, method and computer program for operating a land-or marine-based multi-spool gas turbine system for generating electrical power to supply a load, wherein the system comprises a multi-spool gas turbine engine, and the method comprises controlling the rotational speeds of the at least two generators independently of each other so as to directly control the rotational speeds of the shafts of the spools, the at last two generators being operable to generate electrical current to supply the load, and regulating the amount of heat generated the first heat generating equipment. A computer program to perform the method is also disclosed.