A multi-tube combustor and a gas turbine having the same are provided. The multi-tube combustor includes a nozzle casing configured to receive compressed air from a compressor section and to receive fuel from outside, a liner coupled to the nozzle casing and defining a combustion chamber in which a mixture of fuel ejected from the nozzle casing and the compressed air is combusted, a transition piece connected to the liner and configured to supply the combustion gas generated in the combustion chamber defined by the liner to a turbine section, a plurality of fuel nozzles disposed in a nozzle tube provided inside the nozzle casing, each fuel nozzle having a cavity, a plurality of compressed air supply tubes connected to the plurality of fuel nozzles and configured to supply the compressed air to the plurality of fuel nozzles, a center body having a first end connected to a nozzle base of the nozzle casing, extended to enter the cavity of the fuel nozzle, and having a second end having a fuel ejection hole through which the fuel is ejected, and an on/off valve provided on the plurality of compressed air supply tubes to open and close the compressed air supply tubes. The fuel and the compressed air are mixed inside the plurality of fuel nozzles, and the plurality of fuel nozzles are divided into a plurality of fuel nozzle groups, and a mixture of the fuel and the compressed air is ejected from one or more selected fuel nozzle groups of the plurality of fuel nozzle groups according to a combustion load condition or during a ramp-up process.

A drone includes a frame and a fuselage. The fuselage is coupled to the frame extending away from the frame. The fuselage has a front panel and a bottom panel, and the front panel is positioned at an angle between the bottom surface of the frame and the bottom panel of the fuselage. A first wing is opposite a second wing and are coupled to the frame. The first and second wings extend outwardly from opposite sides of the frame. A first and second mounting member are coupled to the frame and extend outwardly from opposite sides of the frame. A plurality of power generator systems are included and each system is coupled to the first or second mounting member. Each power generator system comprises a power source coupled to a propeller.

A drone includes a frame and a fuselage. The fuselage is coupled to the frame extending away from the frame. The fuselage has a front panel and a bottom panel, and the front panel is positioned at an angle between the bottom surface of the frame and the bottom panel of the fuselage. A first wing is opposite a second wing and are coupled to the frame. The first and second wings extend outwardly from opposite sides of the frame. A first and second mounting member are coupled to the frame and extend outwardly from opposite sides of the frame. A plurality of power generator systems are included and each system is coupled to the first or second mounting member. Each power generator system comprises a power source coupled to a propeller.

A gas turbine combustor that mixes fuel with compressed air guided from a compressor to burn the fuel mixed with the compressed air to generate a combustion gas and supplies the generated combustion gas to a turbine is provided with: an inner cylinder forming a combustion chamber thereinside; an outer cylinder that covers the inner cylinder and forms, between the outer cylinder and the inner cylinder, a cylindrical outer peripheral flow path through which the compressed air flows; an end cover closing the end of the outer cylinder on an opposite side from a side the turbine is located; and a turn guide provided at the end on the end cover side of the inner cylinder, protruding from the outer peripheral surface of the inner cylinder toward the outer cylinder and smoothly connected to the inner peripheral surface of the inner cylinder.

An assembly for a gas turbine having a combustion chamber, a swirler, a combustion zone in the combustion chamber, and an air feed. In a transition region from the air feed to the swirler that is flowed through by the air, a plenum is formed and the assembly adjoining the plenum has the swirler, the combustion chamber, and a cover closing the combustion chamber. The assembly has an air conduction channel designed to conduct part of the air flow flowing into the assembly into the combustion chamber, so that the air flow leading through the air feed is divided into a main flow leading through the swirler into the combustion zone and a bypass flow leading past the combustion zone.

An assembly for a gas turbine having a combustion chamber, a swirler, a combustion zone in the combustion chamber, and an air feed. In a transition region from the air feed to the swirler that is flowed through by the air, a plenum is formed and the assembly adjoining the plenum has the swirler, the combustion chamber, and a cover closing the combustion chamber. The assembly has an air conduction channel designed to conduct part of the air flow flowing into the assembly into the combustion chamber, so that the air flow leading through the air feed is divided into a main flow leading through the swirler into the combustion zone and a bypass flow leading past the combustion zone.

A combustor includes: a nozzle main body having a shaft body and a swirl vane; a first fuel flow path configured to supply fuel to a first fuel injection hole defined in the nozzle main body; a second fuel flow path configured to supply fuel to a second fuel injection hole defined in the nozzle main body on a radial outer side of the first fuel injection hole; a first regulating valve provided in the first fuel flow path and configured to regulate a flow rate of the fuel in the first fuel flow path; a temperature sensor-configured to detect a temperature on a downstream side of the swirl vane; and a control device configured to control the first regulating valve so that the flow rate of the fuel in the first fuel flow path is lowered when the temperature detected by the temperature sensor satisfies a predetermined condition.

There is provided a burner for a gas turbine engine, the burner comprising a radially inner pilot fuel flow passage surrounded by a radially outer main fuel flow passage. The main fuel flow passage is interposed between concentrically arranged radially inner and radially outer air flow passages. The inner and outer air flow passages are in fluid communication with one another via at least one diverting passage at an upstream end of the burner. The burner further comprises at least one control duct connectable to a reduced pressure/vacuum source for selectively reducing the air pressure in the vicinity of the diverting passage such that air flow is selectively diverted from the inner air flow passage to the outer flow passage via the diverting passage.

There is provided a burner for a gas turbine engine, the burner comprising a radially inner pilot fuel flow passage surrounded by a radially outer main fuel flow passage. The main fuel flow passage is interposed between concentrically arranged radially inner and radially outer air flow passages. The inner and outer air flow passages are in fluid communication with one another via at least one diverting passage at an upstream end of the burner. The burner further comprises at least one control duct connectable to a reduced pressure/vacuum source for selectively reducing the air pressure in the vicinity of the diverting passage such that air flow is selectively diverted from the inner air flow passage to the outer flow passage via the diverting passage.

A system has: a combustor; a plenum surrounding the combustor; a transfer tube having an inlet fluidly connected to the plenum and at least two outlets, a first flow passageway defined between the inlet and a first outlet, a second flow passageway defined between the inlet and a second outlet, the second flow passageway connected to a discharge region outside of the plenum; a flow valve disposed within the second flow passageway and operable between an open position and a closed position, in the open position the flow valve fluidly connects the plenum with the discharge region, in the closed position the flow valve blocking fluid communication between the plenum and the discharge region; and a controller communicatively coupled to the flow valve to control operation thereof by: causing the flow valve to open for a time period; and subsequent to the time period, causing the flow valve to close.