United Technologies Corporation

Raytheon Technologies Corporation

Robert H Bush

Sean P Zamora

Felix Izquierdo

Alex J Simpson

John R Buey

Timothy A Swanson

Daniel Bernard Kupratis

Donald William Peters

Christopher J Hanlon

Curtis C Cowan

Timothy J McAlice

Walter A Ledwith

William F Schneider

Benjamin Bellows

Sean Danby

Harry Culver

A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

Gas turbine engine and an airflow control system

A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.

Translating outer cowl flow modulation device and method

A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass. The flow control translates axially between an open position and a closed position to vary and control airflow through the second bypass passage.

Flow control device for a three stream turbofan engine

A mechanism included in a convergent-divergent nozzle connected to an aft portion of a gas turbine engine, which mechanism includes a convergent flap configured to be kinematically connected to the aft portion of the gas turbine engine, a divergent flap pivotally connected to the convergent flap and configured to be kinematically connected to the aft portion of the gas turbine engine, at least one actuator configured to be connected to the aft portion of the gas turbine engine and to mechanically prescribe the position of the convergent flap and the divergent flap by moving through one or more positions, and at least one biasing apparatus. The biasing apparatus is configured to position at least one of the convergent flap and the divergent flap independent of the positions of the actuator by substantially balancing a force on the at least one of the convergent flap and the divergent flap produced by a gas pressure on the nozzle.

Nozzle-area ratio float bias

A mechanism included in a convergent-divergent nozzle connected to an aftward portion of a gas turbine engine, which mechanism includes at least one actuator configured to be connected to the aftward portion of the engine and to move through one or more positions, a first link pivotally connected to the at least one actuator, a convergent flap pivotally connected to the first link, a divergent flap rotatably connected to the convergent flap and configured to be kinematically connected to an annular ring connected to the at least one actuator, and at least one track configured to extend from the aftward portion of the engine and to movably and pivotally receive the pivotal connection between the convergent flap and the first link.

Rollertrack pivoting axi-nozzle

An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member positioned intermediate adjacent ones of the flaps. The bridge member includes a bridge bracket and a sealing element joined to the bridge bracket. The sealing element has an upper surface. The bridge bracket has a lower surface which diverges from the upper surface of the sealing element. In a preferred embodiment of the present invention, the bridge bracket has a shape which allows variable slot size depending on nozzle throat jet area.

Axial divergent section slot nozzle

Growing community of inventors

Glastonbury, CT, United States of America

Robert H Bush