A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

A counter rotating axial air moving device structure is disclosed. The rear rotor includes a rear hub and rear blades, and a pitch angle of each of the rear blades increases gradually in a direction away from the rear hub. The front rotor, the rear rotor and the stator component are stacked with each other. The ratio of the thickness to the diameter is equal to or greater than about 0.25 and equal to or less than about 0.8. Therefore, a better performance curve is obtained, and the vibration and noise are avoided.

A gas turbine engine includes a compressor section and a turbine section. A first spool is rotatable with a first turbine of the turbine section and a first compressor of the compressor section. Additionally, a second spool is rotatable with a second turbine of the turbine section and a second compressor of the compressor section. An electric machine is positioned at least partially inward of the core air flowpath of the gas turbine engine along a radial direction of the gas turbine engine. Additionally, the exemplary gas turbine engine includes a gear assembly mechanically coupled to both the first spool and the second spool, such that the first and second spools may each drive the electric machine.

A gas turbine engine includes a compressor section and a turbine section. A first spool is rotatable with a first turbine of the turbine section and a first compressor of the compressor section. Additionally, a second spool is rotatable with a second turbine of the turbine section and a second compressor of the compressor section. An electric machine is positioned at least partially inward of the core air flowpath of the gas turbine engine along a radial direction of the gas turbine engine. Additionally, the exemplary gas turbine engine includes a gear assembly mechanically coupled to both the first spool and the second spool, such that the first and second spools may each drive the electric machine.

A disclosed gas turbine engine includes a gas generator section for generating a gas stream flow and a propulsor section for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The propulsor section includes a fan driven by a power turbine through a speed reduction device at a second rotational speed lower than a first rotational speed of the power turbine. An Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is between 0.05 and 0.13 during operation of the gas turbine engine.

A disclosed gas turbine engine includes a gas generator section for generating a gas stream flow and a propulsor section for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The propulsor section includes a fan driven by a power turbine through a speed reduction device at a second rotational speed lower than a first rotational speed of the power turbine. An Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is between 0.05 and 0.13 during operation of the gas turbine engine.

A fan logic evaluation device and method thereof for improving the logic evaluation of a fan. Specifically, a fan logic evaluation device is provided by first installing a fan, which corresponds to a set of parameters, in a wind tunnel device. A computer then performs a logic evaluation to convert the set of parameters into an evaluated pressure-flow curve and a measured pressure-flow curve by measuring the fan's operating conditions with the wind tunnel device. The computer further performs a logic modification to correct the logic evaluation to obtain a logic evaluation modification. The logic evaluation is then replaced by the logic evaluation modification. Finally, the above process is repeated with the same fan or a different fan.

A counter-rotating fan, comprising two impellers and a motor. The motor is used for driving the two impellers to rotate. The two impellers are axially spaced apart from each other, and are divided into a first-stage impeller and a second-stage impeller. When the counter-rotating fan operates, airflow is blown to the direction of the second-stage impeller by means of the first-stage impeller. At least one impeller has turns of blades arranged in the radial direction of the impeller. Blades of each turn are spaced apart from each other around a hub of the impeller, and a spacer ring is connected between two adjacent turns of blades. The counter-rotating fan is stable in rotation and good in cooling effect, it is not easy to deform, and the wind is strong in the center.

A counter-rotating fan, comprising two impellers and a motor. The motor is used for driving the two impellers to rotate. The two impellers are axially spaced apart from each other, and are divided into a first-stage impeller and a second-stage impeller. When the counter-rotating fan operates, airflow is blown to the direction of the second-stage impeller by means of the first-stage impeller. At least one impeller has turns of blades arranged in the radial direction of the impeller. Blades of each turn are spaced apart from each other around a hub of the impeller, and a spacer ring is connected between two adjacent turns of blades. The counter-rotating fan is stable in rotation and good in cooling effect, it is not easy to deform, and the wind is strong in the center.

An aircraft having a frame assembly that supports a compressor having an outer shell that defines front and rear nozzle ports with rotatable nozzles for selectable vertical or horizontal thrust. The inner shell and the outer shell define an intake gap therebetween such as an annulus. A first fan unit within the inner shell and is configured to exhaust air through the front nozzle ports. A second fan unit within the outer shell intakes air through the intake gap and exhausts air through the rear nozzle ports. The fan units are preferably connected to one another via a drive shaft that is surrounded by a streamlining tube. The fan units each include a plurality of fans having stators therebetween. The stators have a plurality of stator arms with a wing structure pivotally attached to the trailing edge for angling air flow from a front to a rear fan.