Abstract: Aspects of the disclosure are directed to a system for a thrust reverser of an aircraft comprising: a primary sleeve, and a secondary sleeve, wherein a first stroke associated with the primary sleeve is different from a second stroke associated with the secondary sleeve, and wherein the primary sleeve traverses a first distance associated with the first stroke at the outset of a deployment of the thrust reverser and a second distance associated with the first stroke at a later stage of the deployment.

Abstract: A method of controlling a supply of a fuel to a combustor of a gas turbine having a compressor upstream of the combustor is provided. The method includes: supplying the fuel to the combustor; obtaining a property value of at least one physical property (PT8, PT7, Tinlet, THBOV) of air used for burning the fuel in the combustor; estimating a heat input (HIengmodel) of the fuel supplied to the combustor based on the property value; measuring a Caloric Value (LCVmea) of the fuel upstream of the combustor; adjusting the estimated heat input (HIengmodel) based on the measured Caloric Value (LCVmea); and controlling a fuel valve regulating the supply of the fuel to the combustor based on the adjusted estimated heat input (HIexpected) and a demanded heat input (FFDEM).

Abstract: An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position.

Abstract: A shroud retention system may generally include a shroud hanger and first and second hooked components extending from an outer hanger wall of the hanger. The first hooked component may include a first wall extending from the outer hanger wall and a first rail extending from the first wall. The second hooked component may include a second wall extending from the outer hanger wall and a second rail extending from the second wall. In addition, the system may also include a shroud segment having a shroud wall configured to be positioned radially between the outer hanger wall and the first and second rails. Moreover, the system may include a retention spring positioned within a radial space defined between the outer hanger wall and the first and second rails that is configured to apply a radial spring force against the shroud segment.

Abstract: A pipe arrangement for a turbomachine is provided having a fluid pipe for guiding fluids and a coupling element for coupling the fluid pipe to a temperature affected component. The coupling element is configured to provide a first connection between the coupling element and the component by a first end of the coupling element. The coupling element provides also a second connection between the coupling element and a first surface section of the fluid pipe by a second end of the coupling element. Furthermore, the coupling element has a sleeve portion surrounding a second surface section of the fluid pipe and being spaced apart to the second surface section of the fluid pipe. A fluid inlet or outlet arrangement is also provided having such a pipe arrangement and also a gas turbine engine having such a pipe arrangement.

Abstract: A combustor arrangement includes a combustion chamber with a front panel, and a premix burner of the multi-cone type, which is connected to the front panel through an elongated mixing zone in an axially moveable fashion by a sealed sliding joint. A wide range of axial variation of the burner with a minimized influence of the leakage air flow on the oxidation process within the flame is achieved by positioning the sealed sliding joint upstream of the mixing zone.

Abstract: A gas turbine engine comprises a main fan that delivers air into a bypass duct and into a core engine. A heat exchanger is positioned within the bypass duct and receives a fluid to be cooled from a component associated with the gas turbine engine. A heat exchanger fan is positioned to draw air across the heat exchanger and a control for the heat exchanger fan. The control is programmed to stop operation of the fan during certain conditions, and to drive the heat exchanger fan under other conditions. A method of forming a heat exchanger is also disclosed.

Abstract: Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.

Abstract: A seasonal process that captures stores and uses water in an ambient temperature-dependent manner to improve the efficiency of a natural gas power plant, comprising: (a) providing a natural gas power plant, the natural gas power plant having a flue gas stream, a cooling tower, and a gas turbine; (b) providing a water collection system; (c) providing a water storage facility; wherein the flue gas stream comprises uncondensed water vapor; wherein the water collection system is operably connected to the flue gas stream and the flue gas stream is directed to flow, at least in part, into the water collection system; wherein the water collection system is operably connected to the water storage facility; wherein the water storage facility is operably connected to the cooling tower and the water storage facility is operably connected to the gas turbine; wherein the process comprises the following steps of condensing flue gas water or using water that has been condensed from the flue gas stream based on outdoor ambie

Abstract: According to one embodiment of the present invention, a sealing arrangement includes a turbine static structure with an inner case and a seal ring each having contact surfaces. The sealing arrangement also has a bearing compartment with a contact surface. A piston seal is positioned between the inner case, the seal ring, and the bearing compartment and is configured to contact the contact surfaces.

Abstract: A fluid transport system for a gas turbine engine includes a plenum configured to provide a fluid, an airfoil having an internal cavity, and a transfer tube arranged to transfer the fluid between the plenum and the internal cavity of the airfoil. The transfer tube includes an inlet, an outlet, a cavity extending from the inlet to the outlet, and at least one partition wall dividing the cavity into multiple flow passages.

Abstract: Several embodiments include a system and method for providing thrust recovery in an aircraft engine. The system and method enables a wider range of safe operation for aircraft where the aircraft engine is rapidly reactivated from a substantially deactivated state. The method thereby reduces noise output and fuel usage during descent and shortens runway lengths and occupancy time required for landing. Thrust recovery is provided via the use of stored bleed air being re-injected back into the aircraft engine. An onboard air storage tank and a system of valves facilitating this method are disclosed.

Abstract: Aspects of the disclosure are directed to a thrust reverser of an aircraft, comprising: a wall having a first surface that partially forms a flow channel associated with an air flow, a blocker door having a second surface that partially forms the flow channel, and a dielectric elastomeric device that is configured to selectively expand and contract within a cavity formed between the wall and the blocker door where the cavity is substantially radially adjacent to the flow channel when the thrust reverser is in a stowed state.

Abstract: A system for supplying a turbomachine with fluid, the supply system including a low-pressure pumping unit intended to increase the pressure of the fluid flowing toward a downstream circuit. The downstream circuit divides at an inlet node, situated between the low-pressure pumping unit and the high-pressure volumetric pump, into a circuit supplying an injection system and a variable geometries supply circuit. The circuit supplying the injection system includes a high-pressure volumetric pump. The variable geometries supply circuit is configured to convey the fluid toward variable geometry from the inlet node to an outlet node connecting the variable geometries supply circuit to the upstream circuit between two pumps of the low-pressure pumping unit.

Abstract: A liner portion has an exhaust liner portion with an inner face extending to an outward extending flange. Cooling grooves formed in the flange have a radially outward inlet point and a radially inner outlet point. A flow area at the inlet point is smaller than the flow area at the outlet point.

Abstract: A method for controlling a position actuation system component in a gas turbine engine based on a modified proportional and integral control loop is provided. The method includes determining an error value between a demand signal for the position actuation system component and a position signal for the position actuation system component. The method also includes determining an integral gain scaler as a function of a scheduling parameter value and determining an integral gain based on the determined error value and the determined integral gain scaler. Additionally the method includes determining a proportional gain scaler as a function of the scheduling parameter value and determining a proportional gain based on the determined error value and the determined proportional portion gain scaler. The method adds the determined integral gain with the determined proportional gain to determine a null current value for the position actuation system component.

Abstract: A heat exchanger apparatus including a surface cooler and a passive automatic retraction and extension system coupled to the surface cooler. The surface cooler having disposed therein one or more fluid flow channels configured for the passage therethrough of a heat transfer fluid to be cooled. The heat transfer fluid in a heat transfer relation on an interior side of said one or more fluid flow channels. The surface cooler including a plurality of fins projecting from an outer surface thereof. The passive automatic retraction and extension system including a thermal actuation component responsive to a change in temperature of at least one of the heat transfer fluid and a cooling fluid flow so as to actuate a change in a geometry of the surface cooler. Further disclosed is an engine including the heat exchanger apparatus.

Abstract: A tile for attaching to a wall of a gas turbine engine. The tile has a main body. The tile also has a bridging structure that projects outwardly from the main body and has a hole configured to receive an elongate fastener so that the tile can be attached to the wall of the gas turbine engine by passing the elongate fastener through a hole in the wall of the gas turbine engine and the hole in the bridging structure.

Abstract: A nozzle includes a nozzle body defining a longitudinal axis. The nozzle body includes an air passage having a radial swirler and a converging conical cross-section. A fuel circuit is radially outboard from the air passage with respect to the longitudinal axis. The fuel circuit extends from a fuel circuit inlet to a fuel circuit annular outlet. The fuel circuit includes a plurality of helical passages to mitigate gravitational effects at low fuel flow rates. Each helical passage of the fuel circuit opens tangentially with respect to the fuel circuit annular outlet into an outlet of the air passage.

Abstract: An engine for propelling an aircraft includes an annular fuel cell arrangement having at least one fuel cell, at least one electric motor couplable to the fuel cell arrangement, at least one fan couplable to the electric motor and a cowling having an inlet and an outlet nozzle. The fuel cell arrangement is arranged inside the cowling, the at least one fan is arranged between the inlet and the fuel cell arrangement inside the cowling, the electric motor is operable under consumption of electric power delivered by the fuel cell arrangement and the at least one fan is designed to produce a thrust force by creating an accelerated airflow at the outlet nozzle. The engine is extremely efficient and comprises a distinct low noise.