A jet engine which includes: a fan provided with a plurality of stages of rotor blades; a compressor which compresses air which is sent from the fan; a combustor which generates combustion gas by using compressed air generated by the compressor; a turbine which generates a driving force from the combustion gas; and a nozzle which discharges the combustion gas, the jet engine further includes: a variable guide vane which is disposed upstream of the rotor blades of a second and later stage of the rotor blades of the fan and which adjusts an inlet angle of air flow against the second and later stage of the rotor blades; a fluid resistance adjusting device which adjusts a fluid resistance at the nozzle; and a controller which controls the variable guide vane such that the inlet angle at the time of cruise flight is smaller than the inlet angle at the time of acceleration and controls the fluid resistance adjusting device such that increase in the fluid resistance, due to an increase in a volume flow at an outlet of the fan corresponding to a reduction in the inlet angle, is suppressed.

Turnbuckle linkages are disclosed herein. A turnbuckle linkage includes a hollow rod including an inner portion, a first outer portion, and a second outer portion between the first outer portion and the inner portion, the inner portion including a first thickness, the second outer portion including a second thickness less than the first thickness, and the first outer portion including a conical thickness that varies from the second thickness to a third thickness less than the second thickness, the first outer portion and the second outer portion including first threads, a threadless rod to be partially positioned in the hollow rod, and a conical nut including second threads to engage the first threads, the conical nut to couple the hollow rod and the threadless rod.

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.

An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.

An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.

A method of operating a turbine engine that includes actuating a starter motor of the turbine engine such that a motoring speed of the turbine engine increases, and actuating a plurality of variable stator vanes of the turbine engine such that the plurality of variable stator vanes are at least partially open to control the motoring speed of the turbine engine.

An airflow control system control system for a gas turbine system according to an embodiment includes: an airflow generation system including a plurality of air moving systems for selective attachment to a rotatable shaft of a gas turbine system, the airflow generation system drawing in an excess flow of air through an air intake section; and a mixing area for receiving an exhaust gas stream of the gas turbine system; the airflow generation system: directing a first portion and a second portion of the excess flow of air generated by the airflow generation system into the mixing area to reduce a temperature of the exhaust gas stream; and directing a third portion of the excess flow of air generated by the airflow generation system into a discharge chamber of a compressor component of the gas turbine system.