An example gas turbine engine includes a propulsor assembly consisting of a fan module and a fan drive turbine module, an epicyclic gear train, a high spool and a low spool. A weight of the propulsor assembly is less than 40% of a total weight of a gas turbine engine. The high spool includes an outer shaft, a high pressure turbine and a high pressure compressor. The low spool includes an inner shaft, a low pressure turbine and a low pressure compressor. The inner shaft drives the propulsor through the gear train to drive the propulsor. A weight of the propulsor is greater than a weight of the low pressure turbine.

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a rotor hub and an array of blades circumferentially spaced about the rotor hub, a geared architecture, a compressor section and a turbine section. Each blade includes pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, adjacent blades in the array of blades including a first blade and a second blade, a facing pressure side of the first blade and a facing suction side of the second blade defining a channel having a width that varies in a chordwise direction between the facing pressure and suction sides at a given span position of the first and second blades. The width at each pressure side location of the first blade along the channel is defined as a minimum distance from the respective pressure side location to a location along the suction side of the second blade, and the width of the channel converges in the chordwise direction to establish a throat.

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a rotor hub and an array of blades circumferentially spaced about the rotor hub, a geared architecture, a compressor section and a turbine section. Each blade includes pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, adjacent blades in the array of blades including a first blade and a second blade, a facing pressure side of the first blade and a facing suction side of the second blade defining a channel having a width that varies in a chordwise direction between the facing pressure and suction sides at a given span position of the first and second blades. The width at each pressure side location of the first blade along the channel is defined as a minimum distance from the respective pressure side location to a location along the suction side of the second blade, and the width of the channel converges in the chordwise direction to establish a throat.

In some examples, a system including a gas turbine engine, the engine including a high-pressure (HP) shaft; HP compressor; HP turbine, second shaft; second compressor; second turbine, the second turbine being coupled to the second compressor via the second shaft (e.g., LP shaft); and a generator coupled to the LP shaft. The generator is configured to generate electrical power from rotation of the LP shaft, and increase electrical power generated by the generator to increase a torque applied to the LP shaft by the generator, e.g., in combination with reduction in engine thrust, or in response to the detection of a stall and/or surge of the engine. The increase in torque applied to the second shaft is configured to increase a rate at which a rotational speed of the second shaft decreases, e.g., in combination with the reduction in engine thrust or during the stall/surge of the engine.

A power generation system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; an airflow generation system coupled to an expander shaft downstream of the gas turbine system for drawing in a flow of ambient air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; a flow directing system for directing the flow of ambient air generated by the airflow generation system to the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

A power generation system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; an airflow generation system coupled to an expander shaft downstream of the gas turbine system for drawing in a flow of ambient air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; a flow directing system for directing the flow of ambient air generated by the airflow generation system to the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

A disclosed gas turbine engine includes a first fan section including a plurality of fan blades rotatable about an axis, a compressor in fluid communication with the first fan section, a combustor in fluid communication with the compressor and a first turbine section in fluid communication with the combustor. The first turbine section includes a low pressure turbine that drives the first fan section. A second fan section is supported between the first fan section and the compressor and is driven by a second turbine section disposed between the second fan section and the compressor for driving the second fan section.

A disclosed gas turbine engine includes a first fan section including a plurality of fan blades rotatable about an axis, a compressor in fluid communication with the first fan section, a combustor in fluid communication with the compressor and a first turbine section in fluid communication with the combustor. The first turbine section includes a low pressure turbine that drives the first fan section. A second fan section is supported between the first fan section and the compressor and is driven by a second turbine section disposed between the second fan section and the compressor for driving the second fan section.

The gas turbine power generation system of the present invention repeats either the supply or absorption of power, in addition to generating power. The gas turbine power generation system is provided with a first rotation shaft, a compressor, a combustor, a first turbine upon which combustion gasses impinge, thereby causing the first turbine to rotate, and driving the first rotation shaft, a rotating electrical machine connected to the first rotation shaft, a speed adjustment mechanism for controlling the speed of the compressor by adjusting an air volume, a frequency converter for converting a frequency of power, the frequency converter being connected between the rotating electrical machine and a power system via a power line, and a controller for obtaining a request for an output from the gas turbine power generation system and controlling the combustor on the basis of the request. With respect to the frequency converter, the controller performs frequency converter control for changing the rotational speed of the rotating electrical machine on the basis of the request. The rotating electrical machine supplies or absorbs power in accordance with the change in the rotational speed. With respect to the speed adjustment mechanism, the controller performs speed adjustment mechanism control for setting the rotational speed to a reference value.

The gas turbine power generation system of the present invention repeats either the supply or absorption of power, in addition to generating power. The gas turbine power generation system is provided with a first rotation shaft, a compressor, a combustor, a first turbine upon which combustion gasses impinge, thereby causing the first turbine to rotate, and driving the first rotation shaft, a rotating electrical machine connected to the first rotation shaft, a speed adjustment mechanism for controlling the speed of the compressor by adjusting an air volume, a frequency converter for converting a frequency of power, the frequency converter being connected between the rotating electrical machine and a power system via a power line, and a controller for obtaining a request for an output from the gas turbine power generation system and controlling the combustor on the basis of the request. With respect to the frequency converter, the controller performs frequency converter control for changing the rotational speed of the rotating electrical machine on the basis of the request. The rotating electrical machine supplies or absorbs power in accordance with the change in the rotational speed. With respect to the speed adjustment mechanism, the controller performs speed adjustment mechanism control for setting the rotational speed to a reference value.