United Technologies Corporation

Raytheon Technologies Corporation

Hamilton Sundstrand Corporation

Rtx Corporation

Rohr, Inc.

Michael D Greenberg

Donald E Army

Mark F Zelesky

Robert B Goodman

Zhijun Zheng

John M Dehais

Myles R Kelly

Jason Husband

Jesse W Clauson

David Gelwan

Mark B Gossner

Nancy Poisson

Nathan A Shirk

Keith E Charette

James R Kennedy

Marc J Muldoon

Neil J Terwilliger

Christopher McAuliffe

Todd A Davis

Kevin W Schlichting

Lance L Smith

Pantcho P Stoyanov

William Abdel-Messeh

Scott W Simpson

Ricardo Trindade

Benjamin Joseph Zimmerman

Martin Richard Amari

Adam G Smedresman

Christopher D Ramsey

Jose A Lopes

Donald E Army, Jr

Douglas E Duke

Dorel M Moisei

Eric Herbst

Andrew J Lutz

Scot A Webb

W Samuel Krotzer, Jr

Aaron T Frost

Kevin J Pallos

Kenneth J Sawyer

David Baszak

Peter J Dowd

Dennis P Cronin

Thomas Gresham

Stephen N Koren, Jr

Ryan Spence

William T Kelly

Joseph DeLorme

Bobby J McLarty

Stephen N Koren

Joseph De Lorme

Bobby J Mc Larty

A hybrid electric engine of an aircraft includes a compressor, a turbine operably connected to the compressor via a variable gear ratio gearbox and a combustor configured to drive the turbine via a flow of combustion products. An electric motor is operably connected to the variable gear ratio rear box and configured to input rotational energy into the gearbox. The input of rotational energy into the gearbox from the electric motor changes a rotational speed of one of the compressor or the turbine relative to the other of the compressor or the turbine.

Hybrid electric multiple shaft core

An assembly is provided for rotational equipment. This assembly includes a metal seal carrier and a carbon seal element. The metal seal carrier includes a receptacle and a cylindrical carrier surface forming an outer peripheral boundary of the receptacle. The carbon seal element is seated in the receptacle. The carbon seal element includes a cylindrical element surface that is brazed to the cylindrical carrier surface.

Seal element bonded to seal carrier for a turbine engine

A mounting assembly is provided. The mounting assembly includes a first flange; a second flange; a first asymmetric spacer; a second asymmetric spacer; and a bolt configured to pass through a void of the first asymmetric spacer starting at a first end, through at least one first opening of the first flange, through at least one second opening of the second flange, through a void of the second asymmetric spacer starting at a second end, and to be coupled to a nut, such that, in response to the nut being fastened to the bolt, the bolt bends due to a non-vertical slope of the first asymmetric spacer and a non-vertical slope of the second asymmetric spacer.

Asymmetric spacer to improve flange strength

A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor.

System and method for controlling dual starter air valve

An engine system of an aircraft includes a gas turbine engine comprising at least one spool and at least one electric machine operably coupled with the at least one spool. A controller is configured to detect if the at least one spool of the gas turbine engine is in or is approaching an overspeed condition and apply a load to the at least one spool via the at least one electric machine.

Turbine over-speed brake for hybrid electric gas turbine engine

A variable vane assembly includes a variable vane; a trunnion arranged on one end of the variable vane; a bushing mated to the trunnion to define an interface between the trunnion and the bushing; and a surface modification on at least one of the trunnion and the bushing at the interface, whereby frictional heating at the interface during operation of the assembly is reduced.

Low friction, wear resistant variable vane bushing

An anti-icing system of a nacelle inlet of an engine of an aircraft includes first and second direct acting valves and first and second control valve assemblies fluidly connected to the nacelle inlet. The first direct acting valve includes a first inlet, outlet, valve chamber, and piston. The first piston is positioned in the first direct acting valve. The first control valve assembly is fluidly connected to the first valve. The second direct acting valve includes a second inlet, outlet, valve chamber, and piston. The second piston is positioned in the second direct acting valve. The second direct acting valve is fluidly connected to the first direct acting valve in a series configuration. The second control valve assembly is fluidly connected to the second valve chamber.

Method of regulating air pressure in anti-icing system

An anti-ice system includes a duct that extends from a hot air bleed source to an anti-ice manifold and a direct-acting valve coupled to the duct. The duct may be configured to route hot air from the hot air bleed source to the anti-ice manifold at a regulated pressure and the direct-acting valve may include an inlet portion, a reference chamber, a force-type torque motor, an outlet portion, and a modulating sleeve. The inlet portion may be configured to be in hot air receiving communication with hot air from the hot air bleed source, the reference chamber may be configured to be in hot air receiving communication with the inlet portion, the force-type torque motor may be configured to control a reference pressure of hot air in the reference chamber, and the outlet portion may be configured in hot air receiving communication with the inlet portion via the modulating sleeve.

Direct-acting valve

A bleed air valve comprises a housing that includes an inlet, an outlet, and a center portion to selectively provide a pneumatic flow path between the inlet and the outlet. A piston moves along a center guide in response to forces applied to the piston, where the piston is spring biased to an open position. The valve also comprises a pressure regulator valve that comprises a spring loaded poppet valve that includes a pressure regulator inlet that receives an inlet pressure which is regulated based upon force applied to a pressure regulator piston. A valve spring applies a force to the piston first surface to spring bias the bleed air valve to the open position. A solenoid valve receives a command signal and in response provides compressed air to a solenoid valve outlet that is in fluid communication with the pressure regulator inlet.

Passive stability bleed valve with adjustable reference pressure regulator and remote override capability

A system is provided comprising: a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source; a manual override operably connected to the starter air valve, the manual override is operable to open the starter air valve a select percentage by moving the manual override to a detent engaged position, wherein the select percentage is operable to allow enough airflow to achieve the maximum allowed motoring speed of the gas turbine engine; and a pressure regulating bleed valve in fluid communication with the starter air valve, the pressure regulating bleed valve operable to bleed a portion of the compressed air flow to regulate a motoring speed of the gas turbine engine in response to detection of the manual override in a detent engaged position.

Gas turbine start system to enable rotor thermal stabilization with backup bleed bypass cooling mode

According to an aspect, a system includes a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source. The system also includes a variable-position electromechanical device operable to adjust positioning of the starter air valve and a discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device.

Starter air valve system with dual electromechanical controls

A bleed air valve comprises a piston that moves along a guide, where the piston includes a first surface and an opposing second surface. A pressure divider network includes a divider network inlet having an inlet cross sectional area in fluid communication with a fluid passage, a divider network outlet having an outlet cross sectional area in fluid communication with ambient pressure, and a network chamber in fluid communication with the divider network inlet and the divider network outlet. The network chamber has a pressure value between pressure at the divider network inlet and pressure at the divider network outlet. A shuttle valve includes a shuttle inlet and a shuttle outlet, where the shuttle outlet is in fluid communication with the first surface. An electromechanical valve receives a command signal and in response provides compressed air to an electromechanical valve output that is in fluid communication with the shuttle inlet.

Ducted gas turbine engine stability bleed valve with passive and active shutoff

A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between first end and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between the first end and center portion, the first piston comprising: a first cupped portion configured to form a first chamber with the housing proximate the first end; and a second piston located within the housing between the second end and center portion, the second piston comprising: a third cupped portion configured to form a third chamber with the housing proximate the second end; wherein the pistons are configured to regulate airflow through the fluid passage by adjusting at least one of a first pressure within the first chamber and a third pressure within the third chamber.

Dual inline starter air valve

Growing community of inventors

Bloomfield, CT, United States of America

Michael D Greenberg