A solar power generating system for generating electricity and providing heat includes; at least one generator for generating the electricity; a heating element for heating a heat transfer fluid; a turbocharger having at least one turbocharger turbine and at least one turbocharger compressor, wherein the at least one turbocharger compressor is adapted to receive and pressurize the heat transfer fluid, and the at least one turbocharger turbine is coupled to the at least one turbocharger compressor, wherein the at least one turbocharger compressor receiving and expanding a heated compressed heat transfer fluid coming from the heating element to drive the at least one turbocharger compressor and; a control unit configured to control the solar power generating system by comparing thermophysical properties obtained from more than one sensors placed in the solar power generating system with predetermined data in the control unit.

A solar power generating system for generating electricity and providing heat includes; at least one generator for generating the electricity; a heating element for heating a heat transfer fluid; a turbocharger having at least one turbocharger turbine and at least one turbocharger compressor, wherein the at least one turbocharger compressor is adapted to receive and pressurize the heat transfer fluid, and the at least one turbocharger turbine is coupled to the at least one turbocharger compressor, wherein the at least one turbocharger compressor receiving and expanding a heated compressed heat transfer fluid coming from the heating element to drive the at least one turbocharger compressor and; a control unit configured to control the solar power generating system by comparing thermophysical properties obtained from more than one sensors placed in the solar power generating system with predetermined data in the control unit.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support one or more of the drive shaft, the carrier, or the output shaft.

An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support one or more of the drive shaft, the carrier, or the output shaft.

An air start unit for starting and servicing jet engines in aircraft and other flying machines, wherein at least one compressor is provided for generating air and a power supply for supplying electrical power consumers. The air start unit drives the compressor with at least one electric motor, with the electric motor drawing the electrical energy for operation from a high-voltage battery. The electric motors then in turn drive the compressor, which generates compressed air from ambient air for the purpose of starting and servicing the jet engines in aircraft and other flying machines. With an appropriate battery capacity, the air start unit can also supply power consumer of these aircraft and other flying machines via the power supply.

An air start unit for starting and servicing jet engines in aircraft and other flying machines, wherein at least one compressor is provided for generating air and a power supply for supplying electrical power consumers. The air start unit drives the compressor with at least one electric motor, with the electric motor drawing the electrical energy for operation from a high-voltage battery. The electric motors then in turn drive the compressor, which generates compressed air from ambient air for the purpose of starting and servicing the jet engines in aircraft and other flying machines. With an appropriate battery capacity, the air start unit can also supply power consumer of these aircraft and other flying machines via the power supply.

A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.