Discloses is a turbine power generation system having an emergency operation means and an emergency operation method therefor that are capable of controlling excess heat accumulated during emergency operation, and recycling the accumulated heat. A turbine power generation system includes: an inlet sensor part including a thermometer, a pressure gauge, and a flowmeter that are installed between the heater and the inlet valve and; an emergency discharge part including a branch pipe connected to the steam, and a heat control means installed on the branch pipe. Accordingly, the system and the method are capable of reducing a heat overload during an emergency operation by transferring a heat amount exchanged in the heat storage device to the heat consuming facility, minimizing thermal consumption by recycling the same, and preventing various problems caused by stopping an operation of the turbine power generation system.

To solve the problems of compressor wheel blade flow separation causing surge type noises when an exhaust gas recirculation (EGR) duct introduces into the compressor exhaust gases to be returned to the engine, the exhaust gas is fed into an annular volume, defined between inner and outer walls or an annular transition cavity shaped as a radially expanded, axially flattened cylindrical space in the compressor inlet, so that the generally unidirectional radial flow from an EGR duct is re-directed and organized as it is turned from generally radial to generally axial, merging with the general inlet flow and presenting the compressor wheel with airflow of “circumferentially uniform” flow velocity.

Steering rod for connecting an actuator to a turbocharger drive member, comprising an elongated main body (2), which extends between a first end (5) equipped with a first through-hole (7), and a second end (6) equipped with a second through-hole (8), and two bushings (3), (4) immovably mounted in the through-holes (7), (8), wherein the bushings (3), (4) are made of a material which has a greater resistance to mechanical wear than the material delimiting the through-holes (7), (8), and wherein each bushing (3) (4) has an outer surface that is in contact with an inner part of the through-hole (7), (8) and has a radial recess (9), the second material tightening the bushing (3), (4) preventing it from rotating and filling the recess (9) preventing the bushing (3), (4) from being extracted from the second through-hole (7), (8).

A compressed air conduit can have a cross-sectional area, and a valve, the valve having at least one arm being deployable laterally into the cross-sectional area of the conduit to restrict flow within the conduit.

A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture. A sync-ring is concentrically located about the engine axis, disposed in an annular first duct in direct communication with each passage, and engaged to each one of the plurality of blocker doors for simultaneous operation. The sync-ring is aero-dynamically shaped to reduce surrounding airflow resistance.

A heat exchanger for use in a gas turbine engine has a central body including an inlet manifold and at least one tube providing an outlet manifold, and a plurality of tubes communicating holes in an outer periphery of the inlet manifold to holes in an outer periphery of the outlet manifold, and passages for cooling air to pass across the tubes. A gas turbine engine is also disclosed.

An object is to provide an engine system including an intake bypass device whereby it is possible to expand the operation range of a compressor without causing the output of a turbine to become insufficient. An engine system includes an intake bypass device including a bypass channel connecting a downstream side of a compressor of a turbocharger in an intake channel and an upstream side of a turbine of the turbocharger in an exhaust channel, a bypass valve disposed in the bypass channel and configured to control a flow of compressed intake air in the bypass channel, and a heating unit for heating the compressed intake air flowing through the bypass channel.

A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.

In an adjusting device for an exhaust gas turbocharger with a first adjusting member and a second adjusting member for operating a valve element for varying the flow cross-section of a bypass duct of a flow-through exhaust gas guide portion of a turbine of an exhaust gas turbocharger, the first adjusting member and the second adjusting member are connected so as to be pivotable relative to one another by a pin-shaped connecting element with a locking element establishing a pivot joint of the first adjusting member and the second adjusting member with a predetermined axial engagement force.

A bleed valve assembly includes a flow duct with an inlet and an outlet disposed downstream from the inlet. The outlet is smaller in cross-sectional area than a region of the flow duct disposed between the inlet and the outlet. A piston housing is disposed inside the flow duct between the inlet and the outlet so as to form an annular flow passage between the flow duct and the piston housing. The piston housing is axially aligned with a center axis of the flow duct. At least one rib extends between the flow duct and the piston housing. A sleeve piston is disposed inside the piston housing and is configured to extend downstream of the piston housing in a closed position. The sleeve piston comprises an outer wall that is at least the same in cross-sectional area as the outlet of the flow duct.