Rtx Corporation

United Technologies Corporation

Raytheon Technologies Corporation

Nathan L Messersmith

Dmitriy B Sidelkovskiy

Michael G McCaffrey

Daniel Bernard Kupratis

Michael Winter

Pitchaiah Vijay Chakka

Steven H Zysman

Eric A Grover

Sean P Zamora

Jeffery A Lovett

Brian F Hilbert

Gary L Lidstone

Christopher W Robak

John Benjamin Hinkey

Gerald R Berg

Charles M Willard

Jack T Blozy

Miquel A Velazquez

An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.

After-fan system with electrical motor for gas turbine engines

A variable area nozzle assembly includes a fixed center plug, a fixed outer nozzle, and an inner nozzle. The fixed center plug includes a seal. The inner nozzle is disposed between the fixed center plug and the fixed outer nozzle. The inner nozzle includes an inner nozzle body. The inner nozzle body forms a primary duct between the inner nozzle and the fixed outer nozzle. The inner nozzle body forms a secondary duct and a gap. The gap is a nozzle outlet of the secondary duct. The secondary duct is disposed between the inner nozzle body and the fixed center plug upstream of the seal. The inner nozzle body forms a plurality of apertures. The inner nozzle body is translatable between a first position and a second position. In the first position, the primary duct has a first cross-sectional area and the plurality of apertures are isolated from the gap by the seal. In the second position, the primary duct has a second cross-sectional area and the plurality of apertures are connected in fluid communication with the gap.

Variable area nozzle assembly for an aircraft propulsion system

A variable area nozzle assembly includes a fixed center plug, a fixed outer nozzle, and an inner nozzle. The fixed center plug includes a plug body and a protrusion. The fixed outer nozzle extends about the fixed center plug. The inner nozzle extends about the fixed center plug. The inner nozzle is disposed between the fixed center plug and the fixed outer nozzle. The inner nozzle forms a primary duct between the inner nozzle and the fixed outer nozzle. The primary duct includes an exit plane. The inner nozzle body forms a secondary duct and a gap. The gap is a nozzle outlet of the secondary duct. The gap includes a gap inlet and a gap outlet. The gap inlet is disposed upstream of the protrusion. The gap outlet is disposed downstream of the protrusion. The inner nozzle body is translatable between a first position and a second position. In the first position, the primary duct has a first area at the exit plane and the inner nozzle body is disposed at the protrusion. In the second position, the primary duct has a second area at the exit plane and the inner nozzle body is spaced from the protrusion.

A nacelle assembly of a gas turbine engine includes an annular structure defining a central axis, and having a radially inward surface and a radially outward surface, the radially inward surface at least partially defining a bypass duct. An aft portion of the radially inward surface at least partially defines an axially extending convergent-divergent exit nozzle. A secondary nozzle flap is radially spaced from the aft portion of the radially inward surface. The secondary nozzle flap and the aft portion of the radially inward surface define a secondary bypass duct therebetween. The secondary nozzle flap is operably connected to the annular structure such that the secondary nozzle flap is selectably movable relative to the aft portion of the radially inward surface, thereby changing a cross-sectional area of a secondary bypass duct exit.

High bypass ratio engine bypass duct nozzle with controlled nozzle area

A hydrostatic seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a seal housing. The seal further includes a shoe operatively coupled to the base and extending axially from a forward end to an aft end. The seal yet further includes a plurality of teeth extending radially from a sealing surface of the shoe, one of the teeth being a longest tooth that extends furthest radially from the sealing surface, the axial distance from the forward end of the shoe to the longest tooth being greater than a radial distance from a radial tooth tip to the sealing surface.

Hydrostatic seal with aft tooth

A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.

Variable area exhaust mixer for a gas turbine engine

A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and connected in fluid communication with the distribution manifold. Each fluid injector assembly includes a first tube, a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold, a fuel valve positioned at least partially within the first tube and located downstream of the air valve, an igniter extending into the first tube downstream of the fuel valve, and an outlet in fluid communication with the first tube and connected in fluid communication with the exhaust nozzle. The outlet has a different geometry than the first tube.

Combustion nozzle fluidic injection assembly

An exhaust nozzle assembly provides fluidic thrust vectoring of the primary stream to enhance aircraft maneuverability. The exhaust nozzle assembly includes a cooling air passage that supplies cooling air to a plurality of cooling holes that generate an insulating layer of air. A vector slot injects cooling airflow into the exhaust passage normal to the primary stream. A cover plate partially blocks the vector slot to direct cooling airflow into the exhaust passage that in turn directs portions of the primary stream.

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South Windsor, CT, United States of America

Nathan L Messersmith