United Technologies Corporation

Edward B Pero

Leonard D Aceto

Thomas P Mortimer

Donald N Burr

Thomas C Franz

Paul S Danilowicz

Keven G Van Duyn

A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a first pivot on the door between the first and second ends. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage about a second pivot to in turn move the nozzle door about the first pivot between a plurality of positions, such as stowed, intermediate, and thrust reverse positions to influence bypass airflow through a fan bypass passage. A lip extends from the nozzle door between the first pivot and one of the first end and second end.

Variable area fan nozzle and thrust reverser

A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow through a fan bypass passage. A linkage connects the nozzle doors and an actuator. A louver section coupled with the linkage moves in unison with the nozzle doors between a plurality of louver positions to direct a portion of the bypass airflow in a selected direction.

Variable area fan nozzle thrust reverser

An example nacelle assembly for a gas turbine engine includes a nacelle defined about an axis and defining a boundary of a fan bypass flow path. A fan variable area nozzle includes a plurality of inserts movably mounted to said nacelle. Each of the multiple of inserts is located at a circumferential position about the nacelle. The multiple of inserts are each independently moveable into the fan bypass flow path relative the nacelle to selectively vary a fan nozzle exit area.

Gas turbine engine fan variable area nozzle with swivable insert system

A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a first pivot on the door between the first and second ends. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage about a second pivot to in turn move the nozzle door about the first pivot between a plurality of positions, such as stowed, intermediate, and thrust reverse positions to influence bypass airflow through a fan bypass passage. The fan bypass passage has a radially outward side defined by a nacelle in at least one position. At least a portion of the nozzle door is radially outward of the nacelle and includes a lip extending from the nozzle door between the first pivot and one of the first end and second end.

A turbofan engine () includes a fan variable area nozzle (FVAN) () which effectively changes the physical area and geometry within a fan bypass flow path () to manipulate the pressure ratio of the bypass flow. The FVAN generally includes a multitude of aerodynamically shaped inserts () circumferentially located about the core nacelle (). The FVAN at a fully stowed position (takeoff/landing) takes up a minimum of area within the fan bypass flow path to effectively maximize the fan nozzle exit area () while in the fully deployed position (cruise) takes up a maximum of area within the bypass flow path to effectively minimize the fan nozzle exit area. By separately adjusting each of the multiple of inserts relative the other inserts the FVAN provides an asymmetrical fan nozzle exit area to selectively vector the fan bypass flow.

Gas turbine engine fan variable area nozzle with swivalable insert system

A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a pivot between the first end and the second end. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage to in turn move the nozzle door about the pivot between a plurality of positions, such as a stowed position, an intermediate position, and a thrust reverse position, to influence a bypass airflow through a fan bypass passage.

A support arrangement for a rotor shaft (10) includes a bearing (28) radially interposed between the shaft and a support frame (26). The bearing has a durable support (100) and a destructible support (104). The destructible support is nested within a circumferentially extending channel (78) having three-dimensionally curved surfaces (82, 84). An adjacent oil seal (44) has similar three-dimensionally curved surfaces (52, 54) In the event that the rotor becomes unbalanced during operation, the destructible support disengages from its housing (76) and glides radially within the channel to restrain the rotor longitudinally while precluding the transmission of imbalance forces from the rotor to the frame. The curved character of the seal surfaces preserves the integrity of the seal so that loss of oil will not prevent continued, low speed operation of the rotor. An optional, temporarily operable damper (148) attenuates especially severe vibrations immediately following the onset of the imbalance. A recentering system (164), also optional, applies a modest restorative force to recenter the disabled rotor and alter its natural frequency thereby inhibiting resonant oscillations at low rotational frequencies.

Rotor support for a turbine engine

A heat management system is provided for a gas turbine engine (10) having first and second oil cooling loops (14, 16). The system distributes excess fuel flow from a main fuel pump (44) among a plurality of upstream locations (58, 60, 68) for managing the transfer of heat between the oil loops (14, 16) and the flowing fuel. A diverter valve (62) regulates the distribution of the bypass fuel responsive to engine heat generation, oil temperature, and/or fuel temperature. A passive fuel distribution configuration using one or more fuel flow restrictors (72, 74, 76) is also disclosed.

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Somers, CT, United States of America

Edward B Pero